The Guardian Ring Open the visualizer

Parts

Every assembly, named

The complete component reference behind the visualizer: what each assembly is, what is inside it, and how light, data, power and heat connect it to the rest of the spacecraft.

Personal educational project based on cited public sources. Not an official publication of my employer or of the agencies or companies discussed. Models are schematic; estimates and assumptions are identified.

System diagrams Spacecraft · ABI · TIRS-2

Spacecraft support systems

GOES-R: the bus supports the instrument

Power, attitude control and thermal transport connect different assemblies. These selected GOES-R connections keep the spacecraft functions separate from the instrument’s internal electronics.

  • Light
  • Data / control
  • Electrical power
  • Heat
  • Mechanical motion

From the solar wing to protected feeds

  1. Solar cells, strings and circuits

    Convert and collect solar power

  2. Array power
  3. Slip Ring Assembly (SRA)

    Electrical power crosses the rotating solar-wing interface

  4. Wing interface
  5. Power Regulation Unit (PRU)

    Regulates flow from arrays and batteries to loads

  6. Regulated supply
  7. Power Distribution Modules (PDMs)

    Switched feeds and current sensors serve instruments and other loads

    Fuse Board Assemblies (FBAs)

    Overcurrent protection limits fault propagation

Stored energy and bidirectional conversion

  1. Lithium-ion cell banks

    Parallel cells form banks that are connected in series

  2. Charge / discharge
  3. Battery Charger/Discharger (BCD) modules

    Buck/boost conversion manages power to and from the batteries

  4. Battery / bus
  5. Power Regulation Unit (PRU)

    Regulates flow from arrays and batteries to loads

Measurements become actuator commands

  1. Star trackers

    Provide celestial attitude-reference measurements

    Inertial Measurement Units (IMUs)

    Gyros and accelerometers supply inertial measurements

  2. Measurements
  3. On Board Computer (OBC)

    Runs flight software and gathers/routes commands and data

  4. Commands
  5. Remote Interface Units (RIUs) and SPP Interface Unit (SIU)

    Route subsystem commands and collect requested telemetry

  6. Actuator interface
  7. Reaction Wheel Assemblies (RWAs)

    Primary attitude-control actuators in the named GOES-R design

The star trackers and IMUs measure the spacecraft state. Reaction wheels supply the attitude-control actuation.

A deliberate path from mounted equipment to space

  1. Conductive equipment mounts

    Selected boxes use conductive bonds to equipment panels

  2. Conducted heat
  3. Equipment panels

    Structural equipment mounts with embedded heat pipes

  4. Spread / emit heat
  5. Optical solar reflectors and radiator heat pipes

    Limit solar absorption, spread heat, and emit thermal energy

MLI and low-conductivity supports limit unwanted exchange. Conductive mounts and radiator hardware provide selected paths for heat to leave.

Selected functional connections. Arrows describe a connection or processing step, not a separate housing for every block. Drawing arrangement is schematic. Component buttons open the reviewed evidence; component names link to the assembly catalog.

Civil instrument architecture

ABI: optics, mechanisms and electronics

ABI is one instrument delivered through several coordinated physical units. The Sensor Unit includes optics, mechanisms and its own electronics; the Electronics Unit is a common chassis of cards; cooler controls mount separately. These civil groupings organize the representative cutaway.

Physical assembly view / ABI civil example

One instrument, coordinated units

Enclosures contain several functions. Shared electronics do not require the whole instrument to occupy one housing.

Sensor assembly

  • Optical bench, telescope and scan mechanisms
  • Focal-plane modules and ROICs
  • Sensor Unit Electronics: Video Processors, conversion circuitry and P&TC

Optics, mechanisms, detectors and sensor-side electronics work together. In ABI, the Sensor Unit contains the Video Processors and Peripheral and Thermal Control electronics, including detector digitization.

Instrument electronics assembly

  • Common chassis and parent board
  • Instrument Controller, Data Processor, HSIO and TNT cards
  • Power supply, scanner driver and encoder-processor cards

A common electronics chassis houses coordinated controller, data, timing, power, scan-drive and encoder-processing cards. In ABI this is the Electronics Unit, the main electrical interface to the spacecraft.

Cooler-control assembly

  • Spacecraft-mounted cooler-control electronics
  • Electrical connection to the cooler in the Sensor Unit
  • Temperature feedback and controlled drive

Cooler drive electronics form a separate assembly. In ABI they mount to the spacecraft and control cooler hardware inside the Sensor Unit. A cooler-control enclosure is an electrical unit, not the cold head or radiator.

Across the instrument-to-spacecraft boundary
Mounting and alignment
Mounting feet and an optical-bench reference join the sensor to the spacecraft. The interface carries loads and establishes alignment; it also conducts some heat.
Electrical power
Spacecraft feeds supply the instrument. Its electronics then produce the supplies required internally. Power conversion and command handling remain different functions even when their cards share a chassis.
Commands, telemetry and timing
The instrument’s command interface and local timing circuitry coordinate operation. Their relationship must be defined at integration. ABI’s timing card generates internal clocks; the cited description does not establish a spacecraft time-transfer protocol.
Science data
Detector-side samples pass to instrument data processing and the spacecraft interface. The spacecraft receives an instrument data stream, rather than an individual wire from every detector.
Thermal interfaces
Sensor cooling, electronics mounting and radiators have different heat paths. ABI’s Sensor Unit uses its dedicated rejection hardware; the Electronics Unit and cooler controls reject heat to spacecraft mounting panels.
Who supplies it, and who integrates it?

Contract responsibility is a different map from physical packaging. Lockheed Martin’s 2014 announcement identifies it as SBIRS prime and Northrop Grumman as payload provider, with the delivered payload proceeding to satellite-bus integration. That establishes delivery roles only.

NASA’s Landsat 9 example describes mechanical attachment of the instruments followed by power and spacecraft data-handling integration.

NASA’s interface-management guidance separates organizational boundaries from functional and physical interfaces. Teams define and control those interfaces during design and verify compatibility during integration. There is no universal rule that one company, one enclosure and one function are the same boundary.

  • Light
  • Data / control
  • Electrical power
  • Heat
  • Mechanical motion

Scene radiation reaches a filtered focal-plane module

  1. NS and EW Scan Mirror Assemblies

    Orthogonal mirrors steer the line of sight in separate directions

  2. Steered view
  3. Telescope Assembly

    Four telescope mirrors form images on three focal-plane modules

  4. Formed image
  5. VIS/IR beamsplitter (BS1)

    Separates VNIR from infrared radiation

    MW/LW beamsplitter (BS2)

    Separates the MWIR and LWIR paths

  6. Spectral branches
  7. Channel filters

    Bandpass filters select individual spectral channels

    Windows and cold stops

    Named elements within the controlled cryogenic aft optics

  8. Selected channels
  9. Focal Plane Modules (FPMs)

    Filter the image and produce analog signals

The beamsplitters create branches rather than a single serial band. A fold mirror redirects the VNIR branch; the channel filters are stationary.

Calibration supplies reference views

  1. Internal Calibration Target (ICT)

    Full-aperture blackbody reference for the infrared channels

    Solar Calibration Target (SCT)

    Diffuse white target reflects sunlight into the optical system

    Space-look reference

    Background observations support all ABI channels

  2. Reference view
  3. NS and EW Scan Mirror Assemblies

    Orthogonal mirrors steer the line of sight in separate directions

  4. Optical path
  5. Telescope Assembly

    Four telescope mirrors form images on three focal-plane modules

ICT is an onboard infrared blackbody. SCT is ABI’s solar diffuser. The space reference is a viewing direction, with no extra target installed on the bench.

Detector readout and the digital output

  1. Focal Plane Array (FPA)

    One channel’s detector array plus its ROIC

    Read-Out Integrated Circuit (ROIC)

    Electrical readout associated with each detector array

  2. Detector samples
  3. Video Processors: sample collection

    Collect and format samples for the EU Data Processor

    Analog-to-digital conversion electronics

    SUE circuit cards digitize the focal-plane data

  4. Formatted samples
  5. Data Processor

    Formats and packetizes detector data

  6. Packets to interface
  7. High Speed I/O (HSIO)

    SpaceWire communications interface to the spacecraft

Sample collection and digitization are functions of the Sensor Unit Electronics. The Data Processor and HSIO belong to the Electronics Unit; HSIO provides the spacecraft SpaceWire interface.

Mirror drive and measured position

  1. Scanner Interface & Motor Driver (SIMD)

    EU circuit card controls scan-mirror motion

  2. Motor drive
  3. Scan Drive Assembly (SDA)

    Bench-mounted motor drives one side of a scan mirror

  4. Mirror motion
  5. NS and EW Scan Mirror Assemblies

    Orthogonal mirrors steer the line of sight in separate directions

The Support Bearing Assembly carries the opposite side of the mirror. The motor supplies motion; the encoder reports position.

The scan-position feedback path

  1. Optical encoder

    Reports scan-mirror position

  2. Position measurement
  3. EW and NS Encoder Processors

    Power optical encoders and compute scan-mirror position

Separate control of focus, covers and thermal hardware

  1. Telemetry and Timing (TNT)

    Generates system clocks and handles ABI telemetry

  2. Serial command / telemetry
  3. Peripheral and Thermal Control (P&TC)

    Controls sensor-unit thermal hardware and mechanisms except the scanner

  4. Mechanism control
  5. Telescope focus motor

    Moves one telescope mirror for focus adjustment

    Optical Port Cover (OPC)

    One-time deployable protective cover

    Solar Calibration Cover (SCC)

    Motor-driven calibration cover with a launch lock

P&TC belongs to the Sensor Unit Electronics and excludes the scanner. OPC deploys once using its release and spring-hinge hardware; the solar-calibration cover is motor driven.

Heat travels from the cold region to the radiator

  1. Focal Plane Modules (FPMs)

    Filter the image and produce analog signals

  2. Focal-plane heat
  3. Two-stage pulse-tube cryocooler

    Pumps focal-plane heat toward the radiator/heat-pipe assembly

  4. Pumped heat
  5. Loop Heat Pipe (LHP) Assembly

    Transports Sensor Unit heat to the radiator

  6. Transport to radiator
  7. Thermal Control Radiator

    Releases Sensor Unit thermal energy to space

Electrical feedback controls active refrigeration

  1. Platinum resistance thermometer (PRT)

    Measures cold-head temperature for feedback

  2. Cold-head temperature
  3. Cryocooler Control Electronics (CCE)

    Operates the cooler and controls cold-head temperature

  4. Duty-cycle control
  5. Cryocooler power amplifiers

    Duty cycle adjusted to maintain the cold-head set point

  6. Cooler drive
  7. Thermal Dynamic Unit (TDU)

    Integral cooler, remote cold head, and transfer line

The thermometer, controller and power amplifier form the feedback path. Heat transport is shown in the separate row above.

Selected functional connections. Arrows describe a connection or processing step, not a separate housing for every block. Drawing arrangement is schematic. Component buttons open the reviewed evidence; component names link to the assembly catalog.

NASA TIRS-2 design architecture

TIRS-2: electrical interfaces and thermal hardware

The 2018 TIRS-2 design groups command/data, power, thermal, mechanism and high-speed-interface boards inside Main Electronics Boxes. Detector-side electronics and cooler electronics are separately identified. This is another coherent instrument architecture, with its own names and selected redundant connections.

  • Light
  • Data / control
  • Electrical power
  • Heat
  • Mechanical motion

Focal-plane electronics connect through an interface board

  1. Focal Plane Electronics

    Connect and operate detector readout

  2. Detector-side interface
  3. Focal-plane Interface Board

    Provide selected cross-connections

  4. Selected cross-connections
  5. Main Electronics Box

    House instrument-control and interface boards

MEB-A/B contain distinct command/data, power, temperature-control, mechanism-control and high-speed-interface functions.

The scene-select mechanism has its own electrical control

  1. Mechanism-control electronics

    Drive the scene-select mechanism

  2. Motor drive
  3. Scene-select motor, bearings and encoders

    Move and measure the mirror

  4. Mirror selection
  5. Scene-select mirror

    Choose Earth or a calibration reference

The mirror selects Earth, the onboard blackbody or a space view. Its selection role differs from ABI’s two-axis scan system.

The encoders return measured position

  1. Scene-select motor, bearings and encoders

    Move and measure the mirror

  2. Encoder telemetry
  3. Mechanism-control electronics

    Drive the scene-select mechanism

Cooler switching is an electrical path

  1. Cryocooler Control Electronics

    Drive and control the cooler

  2. Cooler-control connection
  3. Redundancy Switch Electronics

    Select the cooler-control connection

  4. Selected cooler drive
  5. Cryocooler thermomechanical unit

    Provide refrigeration

RSE selects the connection between the paired cooler-control electronics and the thermomechanical unit. It is an electronics interface, not a heat pipe.

Thermal transport and emission have different hardware

  1. Heat pipes

    Transport heat

  2. Transported heat
  3. Radiators

    Release thermal energy

The Earth shield, blankets and isolation also manage external and conducted heat. This row shows thermal roles rather than reconstructing the cooler’s complete thermal network.

Heater circuits add controlled heat

  1. Temperature-control boards

    Electrical thermal-control functions within the MEB

  2. Heater supply
  3. Operational heater circuits

    Support operational thermal control

NASA separately identifies survival-heater supply. Operational control, survival heating and cryocooler drive are distinct paths in the design.

Selected functional connections. Arrows describe a connection or processing step, not a separate housing for every block. Drawing arrangement is schematic. Component buttons open the reviewed evidence; component names link to the assembly catalog.

Read the hardware

The same component names and descriptions appear here and in the 3D cards. Large assemblies contain individually named subcomponents; each entry carries its evidence. Payload details are grouped under their sensor, electronics or cooler-control parent. A selectable function does not imply a separate enclosure, and a supplier responsibility does not define a physical box. GOES-R and ABI provide the detailed civil spacecraft example, while TIRS-2 shows a different instrument architecture. Shared components appear again where a close-up or civil comparison needs them.

The diagrams and 3D geometry are representative arrangements. This is a public engineering reference, not an as-built bill of materials for a military spacecraft. Connectors, fasteners, cable routing and package dimensions remain drawing choices where the sources do not establish them.

Default teaching choices: GEO · Representative · MWIR · HgCdTe

85 assembly entries · 240 component entries

Journey level

The ring

A geostationary orbit keeps a satellite above the same longitude. Follow the light, data, and heat paths through a schematic view of Earth and its orbit families.

Geostationary satellite

Geostationary orbit

View in 3D
Light Geostationary orbit

A geostationary satellite follows a circular orbit over the equator, moving in the same direction and with the same period as Earth’s rotation. It stays above the same point on the ground. The satellite markers are representative.

Geostationary altitude
35,786 km Evidence →
Geosynchronous period
23 h 56 min 4 s Evidence →
Drawing
Representative / not to scale Evidence →

Earth

Choose the frame of reference

View in 3D
Light Choose the frame of reference

In a view fixed relative to distant stars, Earth and a geostationary satellite turn together. In an Earth-fixed view, both hold their positions. The Earth, spacecraft, and orbit spacing are drawn at different scales to keep the relationships legible.

Drawing
Representative / not to scale Evidence →

Orbit paths

Read the orbit families

View in 3D
Light Read the orbit families

The public description of SBIRS includes geosynchronous and highly elliptical orbits. The drawn orbit families introduce their different shapes. Spacecraft counts and positions are illustrative, with no operational coverage represented.

SBIRS orbit families
GEO and HEO Evidence →
Drawing
Representative / not to scale Evidence →

Highly elliptical orbit spacecraft

A changing distance along an ellipse

View in 3D
Light A changing distance along an ellipse

The elongated guide introduces a highly elliptical orbit. Its shape and enlarged spacecraft marker are schematic. NASA describes Molniya as an elliptical orbit; the drawn ellipse does not encode a real trajectory.

Orbit example
Molniya: elliptical orbit Evidence →
Drawing
Representative / not to scale Evidence →
Data Instrument, spacecraft and ground interfaces

The elongated guide introduces a highly elliptical orbit. Its shape and enlarged spacecraft marker are schematic. NASA describes Molniya as an elliptical orbit; the drawn ellipse does not encode a real trajectory. The marker represents a spacecraft carrying instrument and communications equipment. Its selection identifies an orbit family; it does not assert crosslinks, link schedules or processing functions for an operational constellation.

Orbit example
Molniya: elliptical orbit Evidence →
Drawing
Representative / not to scale Evidence →
Heat The spacecraft carries its power and thermal systems

The elongated guide introduces a highly elliptical orbit. Its shape and enlarged spacecraft marker are schematic. NASA describes Molniya as an elliptical orbit; the drawn ellipse does not encode a real trajectory. Solar arrays, batteries and heat-rejection hardware travel with the vehicle. Their detailed components can be explored at the satellite level. The orbital drawing does not simulate eclipse duration, array generation or temperature.

Orbit example
Molniya: elliptical orbit Evidence →
Drawing
Representative / not to scale Evidence →

Medium Earth orbit spacecraft

An intermediate orbit family

View in 3D
Light An intermediate orbit family

This marker separates the medium Earth orbit family from GEO and LEO. The guide is compressed to fit this teaching view; its drawn radius is not an altitude specification.

Orbit family
Medium Earth orbit Evidence →
Drawing
Representative / not to scale Evidence →
Data Instrument, spacecraft and ground interfaces

This marker separates the medium Earth orbit family from GEO and LEO. The guide is compressed to fit this teaching view; its drawn radius is not an altitude specification. The marker represents a spacecraft carrying instrument and communications equipment. Its selection identifies an orbit family; it does not assert crosslinks, link schedules or processing functions for an operational constellation.

Orbit family
Medium Earth orbit Evidence →
Drawing
Representative / not to scale Evidence →
Heat The spacecraft carries its power and thermal systems

This marker separates the medium Earth orbit family from GEO and LEO. The guide is compressed to fit this teaching view; its drawn radius is not an altitude specification. Solar arrays, batteries and heat-rejection hardware travel with the vehicle. Their detailed components can be explored at the satellite level. The orbital drawing does not simulate eclipse duration, array generation or temperature.

Orbit family
Medium Earth orbit Evidence →
Drawing
Representative / not to scale Evidence →

Low Earth orbit spacecraft

A nearer orbit family

View in 3D
Light A nearer orbit family

The inner guide introduces low Earth orbit. NASA describes Terra as a civil example in this family. The oversized marker is a representative spacecraft, with no mission coverage or viewing footprint assigned.

Civil orbit example
Terra in low Earth orbit Evidence →
Drawing
Representative / not to scale Evidence →
Data Instrument, spacecraft and ground interfaces

The inner guide introduces low Earth orbit. NASA describes Terra as a civil example in this family. The oversized marker is a representative spacecraft, with no mission coverage or viewing footprint assigned. The marker represents a spacecraft carrying instrument and communications equipment. Its selection identifies an orbit family; it does not assert crosslinks, link schedules or processing functions for an operational constellation.

Civil orbit example
Terra in low Earth orbit Evidence →
Drawing
Representative / not to scale Evidence →
Heat The spacecraft carries its power and thermal systems

The inner guide introduces low Earth orbit. NASA describes Terra as a civil example in this family. The oversized marker is a representative spacecraft, with no mission coverage or viewing footprint assigned. Solar arrays, batteries and heat-rejection hardware travel with the vehicle. Their detailed components can be explored at the satellite level. The orbital drawing does not simulate eclipse duration, array generation or temperature.

Civil orbit example
Terra in low Earth orbit Evidence →
Drawing
Representative / not to scale Evidence →

Payload, mission processor and communications

Separate component roles

View in 3D
Data Separate component roles

Architectures differ in where processing happens. GAO’s public PWSA description identifies an infrared payload, an on-board mission processor, and communications equipment. The drawing distinguishes these roles without describing their internal algorithms.

Public architecture
Bus, infrared payload, mission processor, communications Evidence →
Drawing
Representative / not to scale Evidence →

Ground segment

A public architectural role

View in 3D
Data A public architectural role

GAO’s public description of the planned FORGE ground system assigns it spacecraft-operations and mission-data-processing roles. This ground marker stands for the receiving and processing segment, with no facility layout or operational algorithms represented.

FORGE role
Spacecraft operations and mission-data processing Evidence →
Drawing
Representative / not to scale Evidence →

Incident sunlight

Start with sunlight

View in 3D
Heat Start with sunlight

Sunlight brings energy to the spacecraft. The lit side and the incoming rays establish that relationship in the drawing. They are orientation cues rather than a calculation of illumination, eclipse timing, or heating.

Drawing
Representative / not to scale Evidence →

Solar array

Turn light into electrical power

View in 3D
Heat Turn light into electrical power

Solar arrays convert sunlight into electrical power for the spacecraft and its instruments. Electronics also produce heat during operation. The displayed paths separate electrical supply from heat flow without assigning an operating power budget.

Drawing
Representative / not to scale Evidence →

Spacecraft radiator

The thermal path

View in 3D
Heat The thermal path

A radiator releases heat as thermal radiation. The outgoing paths represent heat leaving the spacecraft. Their appearance does not specify radiator area, heat-rejection power, or instrument temperature.

Drawing
Representative / not to scale Evidence →

Journey level

The satellite

An observing spacecraft is a collection of working systems: structure holds the instrument, arrays and batteries feed it, sensors and wheels point it, computers move its data, and radiators reject heat. This cutaway uses representative geometry; the engineering examples and specifications are explicitly those of the public GOES-R civil spacecraft.

Infrared instrument and mounting platform

Keep the payload looking outward

View in 3D
Light Keep the payload looking outward

The telescope needs an open optical port and a stable mechanical reference. On GOES-R, ABI and GLM share an Earth-pointing platform with the star trackers and inertial reference units. Their common mounting structure connects the instrument’s viewing direction to the spacecraft’s knowledge of its orientation.

GOES-R Earth-pointing platform
Supports ABI, GLM, star trackers and inertial reference units Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Turn an observation into a data stream

ABI’s focal planes supply analog signals to its video electronics. The Sensor Unit Electronics digitizes the data; the Electronics Unit formats and packetizes it, then sends it through the spacecraft interface. The spacecraft computer receives an instrument data stream, rather than reading individual detector contacts itself.

ABI detector output
Filtered scene image becomes analog electrical signals Evidence →
ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Choose the heat paths at the mounts

An instrument mount must support the payload without forcing every component to the same temperature. GOES-R mounts ABI and GLM through titanium feet and uses blankets to reduce unwanted exchange. ABI carries its own cooler and radiator path, while its Electronics Unit rejects heat through equipment panels inside the spacecraft.

GOES-R instrument thermal interfaces
Titanium mounting feet, thermal blankets and dedicated heat-rejection paths Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Earth Pointing Platform (EPP)

Co-mounts Earth-observing instruments and attitude-reference hardware

The EPP provides the mechanical reference shared by ABI, GLM, and attitude-reference sensors. Instrument mounting and attitude knowledge therefore meet at a common structure.

GOES-R Earth Pointing Platform (EPP)
Co-mounts Earth-observing instruments and attitude-reference hardware Evidence →

Spacecraft bus and equipment panels

Carry the loads and hold alignment

View in 3D
Light Carry the loads and hold alignment

The bus is the load-bearing skeleton around the equipment. GOES-R uses a honeycomb-panel core around the propulsion system, a launch-vehicle adapter ring, equipment panels, and separate instrument platforms. The cutaway exposes those structural roles: mounts and decks carry the boxes; the foil-like thermal blanket is a different component.

GOES-R structure
Honeycomb core panels, equipment panels and instrument platforms Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Connect boxes through remote interfaces

The internal harness joins equipment distributed across the bus. GOES-R remote interface units receive commands, collect telemetry, and provide local electrical interfaces for relays, heaters, motors, and other equipment. The bus structure supports these boxes and routes; an electrical data bus is the communication path between them.

GOES-R remote interfaces
Gather telemetry and drive relays, heaters, motors and thruster interfaces Evidence →
GOES-R structure
Honeycomb core panels, equipment panels and instrument platforms Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Make the deck part of the thermal system

GOES-R’s equipment panels do more than hold boxes: heat pipes spread heat through the panels toward radiating surfaces. Thermally conductive mounting improves the path from selected boxes to those panels. MLI and low-conductivity stand-offs reduce heat flow where an interface needs isolation instead.

GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
GOES-R radiator panels
Heat pipes spread heat; optical solar reflectors limit solar absorption and emit heat Evidence →
GOES-R heat-flow control
MLI, low-emissivity coatings and low-conductivity stand-offs reduce heat transfer Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 9 component entries

Core structure and adapter ring

Honeycomb panels support propulsion; adapter ring mates to the launch vehicle

The core structure supports the propulsion system and connects the vehicle to its launch interface. It is distinct from the instrument-support platform.

GOES-R Core structure and adapter ring
Honeycomb panels support propulsion; adapter ring mates to the launch vehicle Evidence →

Equipment panels

Structural equipment mounts with embedded heat pipes

Equipment panels provide mounting surfaces for spacecraft and instrument electronics while participating in heat transport.

GOES-R Equipment panels
Structural equipment mounts with embedded heat pipes Evidence →

EPP Launch Lock Assemblies

Retain the platform for transport and launch, then release its isolation system

Launch locks hold the EPP during transport and launch. After release, the platform is supported by its damped isolation system.

GOES-R EPP Launch Lock Assemblies
Retain the platform for transport and launch, then release its isolation system Evidence →

Earth Pointing Platform isolators

Passive isolators reduce transmission of spacecraft disturbances to the payload deck

The GOES-R civil design isolates the instrument platform from bus disturbances. Flexible harnesses and blankets crossing the interface are part of the mechanical integration.

GOES-R platform isolation
Passive isolators reduce transmission of spacecraft disturbances to the payload deck Evidence →

Ground-reference connections

System-level electrical reference and control of unwanted subsystem interaction

Ground-reference connections establish the electrical reference and return architecture across subsystems. NASA treats their integration as a spacecraft-level design responsibility rather than an arbitrary set of connections.

NASA grounding architecture
System-level electrical reference and control of unwanted subsystem interaction Evidence →

Cable shields

Controls radiated emissions and crosstalk through a coordinated harness design

Shielding and connector terminations affect electrical compatibility. The drawn harness has no claimed braid, bonding, impedance, or pinout specification.

NASA electromagnetic cable shielding
Controls radiated emissions and crosstalk through a coordinated harness design Evidence →

Launch-vehicle separation interface

A clamped pair of interface rings can release and separate with springs

A launch attachment and its release interface have distinct roles. NASA provides a SmallSat clamp-ring example; the drawn GEO interface is conceptual.

NASA separation-system example
A clamped pair of interface rings can release and separate with springs Evidence →

Vented housing and vent passages

Vents and blanket venting are directed away from sensitive items

ECSS recommends directing instrument and blanket vents away from contamination-sensitive items. A representative cutaway can identify the housing opening and its routed passage.

ECSS cleanliness-oriented design
Vents and blanket venting are directed away from sensitive items Evidence →

Electrical bonding straps

Bonded structural interfaces and flexible joints

Bonding provides electrical continuity across structural interfaces and moving joints. It is distinct from the signal-return circuit.

Structural electrical continuity
Bonded structural interfaces and flexible joints Evidence →

Solar array

Make electricity at the cells

View in 3D
Light Make electricity at the cells

Light absorbed in a photovoltaic semiconductor produces electrical current. Multi-junction cells stack materials that respond to different parts of the solar spectrum. GOES-R connects cells in series strings, then joins strings in parallel circuits; the thin interconnects turn a tiled surface into an electrical network.

Photovoltaic cells
Semiconductors convert light into electrical current Evidence →
GOES-R array circuit
42 cells in series × 10 parallel strings; 16 circuits Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Array telemetry and isolation

The regulator measures array current and reports it to the onboard computer. On GOES-R, separately connected array circuits and isolation diodes limit how a shorted string or circuit affects the rest of the network. The engineering record combines electrical output with the state of the power hardware.

GOES-R power telemetry
Module temperature/status; array, battery and load currents Evidence →
GOES-R array protection
String and circuit isolation diodes Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Follow solar power onto the bus

The solar wing is the primary electrical source. GOES-R’s cells form series strings and parallel circuits that feed the power regulator; isolation diodes protect the common supply from a circuit fault. The amount generated depends on illumination, while the regulator determines how that available power reaches the loads.

GOES-R array circuit
42 cells in series × 10 parallel strings; 16 circuits Evidence →
GOES-R array protection
String and circuit isolation diodes Evidence →
GOES-R power regulation
Array shunts, battery buck/boost converters and low-voltage buck converters Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Photovoltaic cells

Convert sunlight into electrical current

A semiconductor photovoltaic cell converts absorbed light into electrical energy. NASA describes multi-junction cells as stacked junctions that respond to different portions of the solar spectrum.

Photovoltaic cells
Semiconductors convert light into electrical current Evidence →

Solar cells, strings, and circuits

GOES-R circuit: 42 cells in series per string; 10 strings in parallel

GOES-R connects cells in series strings, places strings in parallel within each circuit, and connects separate circuits to the PRU. The model illustrates this electrical hierarchy without reproducing the published cell counts.

GOES-R Solar cells, strings, and circuits
GOES-R circuit: 42 cells in series per string; 10 strings in parallel Evidence →

String and circuit isolation diodes

Limit propagation of electrical shorts

String diodes protect the rest of a circuit; circuit diodes in the PRU protect the shared supply from a circuit short.

GOES-R String and circuit isolation diodes
Limit propagation of electrical shorts Evidence →

Solar-cell coverglass and optical coatings

Coverglass and optical coatings

Coverglass protects the cell; coatings manage incoming light. The cutaway is representative, with no assigned material or thickness.

Solar-cell protective layers
Coverglass and optical coatings Evidence →

Solar-array deployment and drive assembly

Aim the wing after deployment

View in 3D
Light Aim the wing after deployment

Deployment and Sun tracking use different mechanisms. GOES-R releases its restrained wing through spring hinges and dampers, then latches it in its deployed shape. A motorized drive rotates the wing for Sun tracking; a slip-ring assembly carries electrical power across that rotating joint.

GOES-R deployment hardware
Release devices, spring hinges, dampers, hard stops and latches Evidence →
GOES-R rotating interface
Motor drive and resolver; slip rings carry array power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Drive electronics and resolver

GOES-R’s solar-array drive is operated through software and dedicated drive electronics. Motors provide rotation and resolver circuits provide the position reference. The slip rings preserve the power path as the joint turns, so mechanical orientation and electrical continuity are handled together.

GOES-R rotating interface
Motor drive and resolver; slip rings carry array power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Keep a moving joint within its temperature range

A drive assembly combines mechanical motion with an electrical interface. GOES-R blankets its gimbals while leaving their rotation interfaces clear and uses heaters for thermal control. The drive must rotate the wing and maintain its power connection across changing thermal conditions.

GOES-R gimbal thermal control
MLI around the gimbals and heaters; rotation interfaces remain clear Evidence →
GOES-R rotating interface
Motor drive and resolver; slip rings carry array power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 12 component entries

Shear tie assemblies

Actuator and retraction mechanism restrain and release deployables

The actuator secures the restraint, while the retraction mechanism removes the released bolt or cable from the deployment path. This is separate from the hinge that rotates the appendage.

GOES-R Shear tie assemblies
Actuator and retraction mechanism restrain and release deployables Evidence →

Frangibolts, separation nuts, and split-spool release devices

Named restraint-release devices used on different appendages

The Data Book names different release devices for different appendages. These are published device families, not a claim that the generic drawing reproduces their internal construction.

GOES-R Frangibolts, separation nuts, and split-spool release devices
Named restraint-release devices used on different appendages Evidence →

Deployment hinges and viscous dampers

Springs deploy appendages; dampers control their rotation

Deployment hinges use springs and dampers to move an appendage. Hard stops and latches hold it at the final position; the continuous array drive has a different role.

GOES-R Deployment hinges and viscous dampers
Springs deploy appendages; dampers control their rotation Evidence →

Solar Array Drive Assembly (SADA)

Motor-driven rotation of the solar wing

The SADA rotates the solar wing and uses resolver circuits in its drive assembly. Software and Solar Array Drive Electronics command its motion.

GOES-R Solar Array Drive Assembly (SADA)
Motor-driven rotation of the solar wing Evidence →

Slip Ring Assembly (SRA)

Electrical power crosses the rotating solar-wing interface

The SRA maintains the power connection while the solar wing rotates. It is the electrical interface, not the motor.

GOES-R Slip Ring Assembly (SRA)
Electrical power crosses the rotating solar-wing interface Evidence →

Solar Array Drive Electronics (SADE)

Electronic drive interface for SADA motion

The SADE drives the SADA under software control and communicates through the spacecraft control architecture.

GOES-R Solar Array Drive Electronics (SADE)
Electronic drive interface for SADA motion Evidence →

Sun-Pointing Platform Elevation Gimbal Assembly (SEGA)

Motor and drive train rotate the Sun-Pointing Platform

The SEGA works with the Trailer Bearing Assembly to rotate the Sun-Pointing Platform. This platform-mounted mechanism is separate from the solar-wing drive.

GOES-R Sun-Pointing Platform Elevation Gimbal Assembly (SEGA)
Motor and drive train rotate the Sun-Pointing Platform Evidence →

Trailer Bearing Assembly (TBA)

Supports the opposite end of the Sun-Pointing Platform axis

The TBA supports the platform’s rotation at the end opposite its drive mechanism.

GOES-R Trailer Bearing Assembly (TBA)
Supports the opposite end of the Sun-Pointing Platform axis Evidence →

Deployment-position sensors and latch-status indicators

Monitor deployment progress and report lock/latch state through telemetry

Position sensing and latch-status telemetry show whether a deployment completed. The sensor type and placement shown are illustrative.

ECSS mechanism status
Monitor deployment progress and report lock/latch state through telemetry Evidence →

Pressure-equalization vent passages

Venting accommodates ascent depressurization while controlling particle contamination

Enclosures may need vent passages for ascent. Sealed or pressure-qualified hardware is a different case; a vent is not automatically appropriate everywhere.

ECSS mechanism venting
Venting accommodates ascent depressurization while controlling particle contamination Evidence →

Harness clamps and strain-relief supports

Protect electrical connections from harness loads and verify repeatable routing through motion

Clamps and strain relief keep moving wiring from loading its electrical connections. Routes and supports are representative.

ECSS moving harness
Protect electrical connections from harness loads and verify repeatable routing through motion Evidence →

Bearing lubricant or lubricating surface and migration barrier

Qualify lubrication for the mission; contain fluid migration where sensitive equipment requires it

Bearings require suitable tribology; any lubricant and migration-control approach depend on the mechanism and its environment.

ECSS mechanism tribology
Qualify lubrication for the mission; contain fluid migration where sensitive equipment requires it Evidence →

Power regulation and distribution unit

Make the instrument’s supply dependable

View in 3D
Light Make the instrument’s supply dependable

The payload needs a controlled electrical supply while array output and equipment demand change. GOES-R’s regulator meters power from the array and batteries, converts it for the lower-voltage bus, and distributes it through protected feeds. The regulator and distribution boards are separate from the light-collecting telescope.

GOES-R power regulation
Array shunts, battery buck/boost converters and low-voltage buck converters Evidence →
GOES-R load distribution
Power-feed switches, current sensing and overcurrent fuses Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Read the health of the power bus

GOES-R’s power regulator reports module temperatures, operating status, and array, battery, and load currents. Commands set the battery charge rate and operate module and load switches. Those measurements let the flight software manage supply and demand instead of treating the solar array as an uncontrolled wire to every instrument.

GOES-R power telemetry
Module temperature/status; array, battery and load currents Evidence →
GOES-R load distribution
Power-feed switches, current sensing and overcurrent fuses Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Array → regulator → loads

GOES-R uses switched array shunts to regulate its main bus. Battery charger/dischargers use buck/boost conversion to move power in either direction, and buck converters create the lower-voltage supply. Protected distribution switches and fuses then divide those supplies among the spacecraft loads.

GOES-R named power buses
70 V and 28 V Evidence →
GOES-R power regulation
Array shunts, battery buck/boost converters and low-voltage buck converters Evidence →
GOES-R load distribution
Power-feed switches, current sensing and overcurrent fuses Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 12 component entries

Power Regulation Unit (PRU)

Regulates flow from arrays and batteries to loads

The PRU combines regulation, conversion, distribution, and monitoring modules. It is not just an on/off switch between the array and the payload.

GOES-R Power Regulation Unit (PRU)
Regulates flow from arrays and batteries to loads Evidence →

Central Distribution Assembly (CDA)

Main-bus regulation, load ports, current sensing, and command interface

The CDA provides the higher-voltage bus regulation electronics and load interface. It exchanges commands and telemetry with the On Board Computer.

GOES-R Central Distribution Assembly (CDA)
Main-bus regulation, load ports, current sensing, and command interface Evidence →

Solar Array Shunt (SAS) modules

Control array power admitted to the regulated bus

The shunt modules respond to the bus-regulation electronics, controlling how available array power reaches the bus.

GOES-R Solar Array Shunt (SAS) modules
Control array power admitted to the regulated bus Evidence →

Battery Charger/Discharger (BCD) modules

Buck/boost conversion manages power to and from the batteries

The BCD modules manage charge and discharge power. Flight software supplies charge commands; the conversion hardware carries the electrical power.

GOES-R Battery Charger/Discharger (BCD) modules
Buck/boost conversion manages power to and from the batteries Evidence →

Low Voltage Control Module (LCM)

Regulation electronics, load ports, and sensing for the lower-voltage bus

The LCM supervises the lower-voltage supply and communicates with the CDA. It is distinct from the power-converter modules that deliver the converted energy.

GOES-R Low Voltage Control Module (LCM)
Regulation electronics, load ports, and sensing for the lower-voltage bus Evidence →

Low Voltage Power Modules (LPMs)

Buck converters feed the lower-voltage bus

The LPMs perform voltage conversion under control of the lower-voltage regulation electronics.

GOES-R Low Voltage Power Modules (LPMs)
Buck converters feed the lower-voltage bus Evidence →

Power Distribution Modules (PDMs)

Switched feeds and current sensors serve instruments and other loads

The PDMs divide power among instrument and spacecraft loads and measure instrument feed current.

GOES-R Power Distribution Modules (PDMs)
Switched feeds and current sensors serve instruments and other loads Evidence →

Fuse Board Assemblies (FBAs)

Overcurrent protection limits fault propagation

The fuse boards provide a protection function separate from regulation and distribution switching.

GOES-R Fuse Board Assemblies (FBAs)
Overcurrent protection limits fault propagation Evidence →

Pyro Relay Assemblies (PRAs)

Relays enable and energize deployment devices

The PRAs are the deployment-device relay interface in the named GOES-R power architecture. No firing circuit or actuation sequence is reproduced.

GOES-R Pyro Relay Assemblies (PRAs)
Relays enable and energize deployment devices Evidence →

Current Sensor Unit (CSU)

Converts measured feed current into an analog telemetry voltage

The CSU senses electrical feed current. An RIU then digitizes its analog output for flight-software telemetry, a separate path from payload detector digitization.

GOES-R Current Sensor Unit (CSU)
Converts measured feed current into an analog telemetry voltage Evidence →

Transient Suppression Unit (TSU)

Passive harness interface provides a safe electrostatic-discharge path

The TSU connects harness and structure to protect susceptible circuitry from electrostatic discharge. It is passive and has no commanding or telemetry of its own.

GOES-R Transient Suppression Unit (TSU)
Passive harness interface provides a safe electrostatic-discharge path Evidence →

Battery discharge and recharge-isolation circuitry

Discharge the battery and prevent renewed charging from the solar array

Retirement includes removing stored battery energy and preventing recharge. This role belongs within the power architecture, not an invented standalone box.

ESA battery passivation guidance
Discharge the battery and prevent renewed charging from the solar array Evidence →

Rechargeable battery assembly

Keep working through eclipse

View in 3D
Light Keep working through eclipse

The array cannot generate solar power when Earth blocks the Sun. GOES-R’s rechargeable batteries then support the spacecraft loads; they also assist when demand exceeds array output. Back in sunlight, available array power supplies the loads and recharges the batteries.

GOES-R battery role
Supplies eclipse and peak-load demand; recharges from excess array power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Control charging at the cell banks

GOES-R flight software monitors the battery’s cell-bank voltages and charge state. Charging begins with controlled current, tapers near the voltage limit, and finishes by balancing the cell banks. The battery package therefore needs sensing and control connections as well as its main power leads.

GOES-R battery charge control
Cell-bank voltage monitoring, current taper and balancing Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Remove discharge heat and add heat when needed

A battery needs its own thermal path. GOES-R uses temperature sensors and heaters in the battery package and dedicated radiators to reject discharge heat. Electrical charge control and temperature control work alongside one another; neither is supplied by the solar cells alone.

GOES-R battery thermal hardware
Temperature sensors, heaters and dedicated radiators Evidence →
GOES-R battery charge control
Cell-bank voltage monitoring, current taper and balancing Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Lithium-ion cell banks

Parallel cells form banks that are connected in series

The GOES-R battery organizes cells into electrical banks. Those banks store energy for eclipse and times when array power is below load demand.

GOES-R Lithium-ion cell banks
Parallel cells form banks that are connected in series Evidence →

Cell-bank balancing circuits and bypass switches

Balance cell-bank voltages and remove a failed bank from the path

Balancing circuits manage differences between cell banks. Bypass switches provide a separate means to remove a failed bank from the electrical path.

GOES-R Cell-bank balancing circuits and bypass switches
Balance cell-bank voltages and remove a failed bank from the path Evidence →

Battery sensors, heaters, and radiator

Monitor temperature and manage battery heat

Temperature sensors, separately controlled heater zones, and dedicated radiators keep battery thermal management distinct from electrical charge management.

GOES-R Battery sensors, heaters, and radiator
Monitor temperature and manage battery heat Evidence →

Battery discharge and recharge-isolation circuitry

Discharge the battery and prevent renewed charging from the solar array

Retirement includes removing stored battery energy and preventing recharge. This role belongs within the power architecture, not an invented standalone box.

ESA battery passivation guidance
Discharge the battery and prevent renewed charging from the solar array Evidence →

Attitude and navigation sensors

Measure which way the spacecraft faces

View in 3D
Light Measure which way the spacecraft faces

A star tracker observes a star field to establish attitude, while the inertial measurement unit measures rotational motion between attitude updates. GOES-R also carries Sun sensors for acquisition and contingency use. These sensors measure orientation; the wheels and thrusters supply the torques that change it.

GOES-R attitude measurement
Star trackers and an inertial measurement unit Evidence →
GOES-R Sun sensors
Coarse analog sensors for Sun acquisition; fine sensor on the Sun-pointing platform Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Measured attitude and angular motion

GOES-R combines star-tracker attitude measurements with inertial measurements for attitude determination. Sun-sensor outputs support Sun acquisition, while the computer also handles gimbal pointing. The sensors feed the estimate; the controller uses that estimate to command the actuators.

GOES-R attitude measurement
Star trackers and an inertial measurement unit Evidence →
GOES-R Sun sensors
Coarse analog sensors for Sun acquisition; fine sensor on the Sun-pointing platform Evidence →
GOES-R onboard computer
Runs flight software; routes commands, telemetry and instrument data Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Stabilize the sensor mounting environment

GOES-R’s Earth-pointing platform co-locates the instruments and attitude-reference hardware. Its star tracker has a dedicated radiator, thermal straps, and heaters, while the inertial units use a cold-plate/radiator assembly. Thermal control is part of maintaining the measurement environment, not just protecting electronics from damage.

GOES-R Earth-pointing platform
Supports ABI, GLM, star trackers and inertial reference units Evidence →
GOES-R instrument thermal interfaces
Titanium mounting feet, thermal blankets and dedicated heat-rejection paths Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Star trackers

Provide celestial attitude-reference measurements

Star trackers contribute attitude observations. They are sensors; reaction wheels and thrusters are the actuators that change orientation.

GOES-R Star trackers
Provide celestial attitude-reference measurements Evidence →

Inertial Measurement Units (IMUs)

Gyros and accelerometers supply inertial measurements

GOES-R’s IMUs contain gyros and accelerometers. The flight software combines inertial information with other attitude-reference data.

GOES-R Inertial Measurement Units (IMUs)
Gyros and accelerometers supply inertial measurements Evidence →

Global Positioning System Receiver (GPSR)

Provides orbit-determination information

The GPS receiver provides navigation information. Orbit position and spacecraft orientation are different quantities with different sensor inputs.

GOES-R Global Positioning System Receiver (GPSR)
Provides orbit-determination information Evidence →

Coarse and Fine Sun Sensor Assemblies

Measure Sun direction relative to the spacecraft or platform

Coarse Sun Sensor Assemblies provide broad Sun-direction knowledge. The Fine Sun Sensor Assembly provides a separate platform reference; neither is the array-drive motor.

GOES-R Coarse and Fine Sun Sensor Assemblies
Measure Sun direction relative to the spacecraft or platform Evidence →

Reaction-wheel assembly

Turn the body without expelling propellant

View in 3D
Light Turn the body without expelling propellant

Accelerating a reaction wheel turns the spacecraft in the opposite sense; slowing it exchanges momentum back. GOES-R uses wheels as its primary attitude actuators. External torques can build up stored wheel momentum, so propulsion supplies the external torque needed for momentum management.

Reaction-wheel principle
Exchange angular momentum between wheel and spacecraft Evidence →
GOES-R attitude actuators
Reaction wheels, with propulsion for momentum management Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Wheel command and telemetry

A reaction wheel is a commanded actuator, not an attitude sensor. GOES-R’s remote interface units provide its wheel command and telemetry interfaces. The attitude-control system uses wheels for routine body control and calls on propulsion for momentum management.

GOES-R remote interfaces
Gather telemetry and drive relays, heaters, motors and thruster interfaces Evidence →
GOES-R attitude actuators
Reaction wheels, with propulsion for momentum management Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Give motorized equipment a rejection path

GOES-R mounts reaction-wheel assemblies on thermally controlled equipment panels along with computers and communications hardware. The panel carries their heat toward radiating surfaces. A wheel’s mechanical job is attitude control; its mounting also supplies structural support and a thermal interface.

GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
GOES-R attitude actuators
Reaction wheels, with propulsion for momentum management Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 2 component entries

Reaction Wheel Assemblies (RWAs)

Primary attitude-control actuators in the named GOES-R design

Reaction wheels apply attitude-control torque by exchanging angular momentum with the spacecraft. Propulsion also supports momentum management.

GOES-R Reaction Wheel Assemblies (RWAs)
Primary attitude-control actuators in the named GOES-R design Evidence →

Reaction-wheel isolators

Separate passive isolation at the reaction wheels complements platform isolation

The design also places isolation at the wheel assemblies, reducing disturbance transmission near its source. The teaching model does not reproduce the isolator construction.

GOES-R wheel isolation
Separate passive isolation at the reaction wheels complements platform isolation Evidence →

Propellant tanks and thrusters

Connect a tank to controlled thrust

View in 3D
Light Connect a tank to controlled thrust

A thruster is the outlet of a larger system. GOES-R’s tanks include devices that deliver liquid without gas to the feed lines. Pressurant, valves, filters, and pressure sensors support that delivery; the propulsion subsystem provides orbit changes and attitude-control functions.

GOES-R propellant feed
Tanks, pressurant, management devices, valves, filters and pressure sensors Evidence →
GOES-R propulsion functions
Orbit changes, attitude control and reaction-wheel momentum management Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Measure the feed and command the valves

Pressure transducers report the condition of GOES-R’s propulsion feed system. The remote interface units provide electrical control interfaces for thruster solenoids and heaters. These are the links between flight-software commands and the physical valves and thermal hardware at the tanks and thrusters.

GOES-R propellant feed
Tanks, pressurant, management devices, valves, filters and pressure sensors Evidence →
GOES-R remote interfaces
Gather telemetry and drive relays, heaters, motors and thruster interfaces Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Separate the tank environment from the hot engine

GOES-R’s MLI-lined bus cavity moderates the environment around propulsion components. Thruster-heater interfaces support temperature control, and a heat shield protects nearby hardware around the apogee engine. The tank, feed line, actuator, and exhaust region impose different thermal needs.

GOES-R propulsion thermal interfaces
Blanketed spacecraft cavity; heat shield around the apogee engine Evidence →
GOES-R remote interfaces
Gather telemetry and drive relays, heaters, motors and thruster interfaces Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 6 component entries

Propellant tanks and management devices

Store propellant and supply gas-free liquid to the feed system

The tanks contain propellant-management devices that control liquid location in the space environment. Their internal geometry is not inferred for the generic model.

GOES-R Propellant tanks and management devices
Store propellant and supply gas-free liquid to the feed system Evidence →

Pressurant tanks and pressure regulator

Supply gas pressure and regulate the tank environment

GOES-R’s named system includes pressurant tanks and regulation hardware. These are distinct from fuel storage and from the thrusters that create force.

GOES-R Pressurant tanks and pressure regulator
Supply gas pressure and regulate the tank environment Evidence →

Check valves, latch valves, and service valves

Control feed-system flow and servicing interfaces

Check valves prevent propellant vapor from migrating into the pressurant system. Latch valves isolate flow paths, while service valves support filling, draining, and test connections.

GOES-R Check valves, latch valves, and service valves
Control feed-system flow and servicing interfaces Evidence →

Filters and pressure transducers

Limit contamination and supply pressure telemetry

Filters protect the feed path from contamination; pressure transducers report conditions at points in the system.

GOES-R Filters and pressure transducers
Limit contamination and supply pressure telemetry Evidence →

Liquid Apogee Engine, REAs, and arcjets

Distinct propulsion assemblies serve orbit and attitude roles

GOES-R’s Liquid Apogee Engine supports orbit insertion. Its other named thruster assemblies support attitude control, momentum management, or station-keeping; the public design includes reaction engine assemblies and arcjets with distinct roles.

GOES-R Liquid Apogee Engine, REAs, and arcjets
Distinct propulsion assemblies serve orbit and attitude roles Evidence →

Propellant and pressurant depletion or vent paths

Retirement addresses remaining propellant and pressurant energy

Propulsion has a retirement role as well as an operating role: remaining stored energy must be addressed. The illustration specifies no actuation sequence.

ESA end-of-life passivation
Retirement addresses remaining propellant and pressurant energy Evidence →

Flight computer and remote interface units

Coordinate an observation

View in 3D
Light Coordinate an observation

An instrument does not operate alone. GOES-R’s onboard computer runs flight software, exchanges commands with the instruments, and collects their data for downlink. Its links to the attitude sensors also bring in the orientation information needed by spacecraft control.

GOES-R onboard computer
Runs flight software; routes commands, telemetry and instrument data Evidence →
Drawing
Representative arrangement / not to scale Evidence →
NASA safe-state guidance
Preserve spacecraft resources and commandability while maintaining a sustainable power and thermal state Evidence →
NASA fault-containment guidance
Redundancy depends on containing faults within defined regions Evidence →
ECSS radiation-assurance scope
Project-specific assurance addresses ionizing dose, displacement damage, and single-event effects in EEE components Evidence →
Data Separate commands, telemetry and stored records

GOES-R’s command processor validates uplink commands and gathers health telemetry, while its onboard computer routes instrument data. In the general NASA architecture, memory also holds command sequences and can retain data until transmission is available. These are distinct jobs: commanding an action, describing equipment health, and preserving an observation. Fault protection coordinates recovery across the power, attitude, thermal and communications systems. A safe state is an operating condition, not another hardware box. Radiation assurance evaluates the mission environment and electronics rather than assigning a universal radiation-proof label.

GOES-R command gateway
Validates commands and formats spacecraft health telemetry Evidence →
GOES-R onboard computer
Runs flight software; routes commands, telemetry and instrument data Evidence →
Spacecraft data handling
Command sequences and data records can be stored in onboard memory Evidence →
Drawing
Representative arrangement / not to scale Evidence →
NASA safe-state guidance
Preserve spacecraft resources and commandability while maintaining a sustainable power and thermal state Evidence →
NASA fault-containment guidance
Redundancy depends on containing faults within defined regions Evidence →
ECSS radiation-assurance scope
Project-specific assurance addresses ionizing dose, displacement damage, and single-event effects in EEE components Evidence →
Heat Conduct electronics heat through the chassis

The flight computer and other electronics occupy boxes attached to GOES-R’s thermally controlled equipment panels. Where more conductance is needed, the mounting uses a thermally conductive bond. The chassis and its contact with the panel are therefore part of the heat path, alongside the circuitry’s electrical connections.

GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
NASA safe-state guidance
Preserve spacecraft resources and commandability while maintaining a sustainable power and thermal state Evidence →
NASA fault-containment guidance
Redundancy depends on containing faults within defined regions Evidence →
ECSS radiation-assurance scope
Project-specific assurance addresses ionizing dose, displacement damage, and single-event effects in EEE components Evidence →
Inside this assembly 15 component entries

Command and Telemetry Processor (CTP)

Validates uplink commands and formats health telemetry

The CTP is the command gateway and spacecraft-health telemetry formatter. It passes validated commands to the flight-computer architecture.

GOES-R Command and Telemetry Processor (CTP)
Validates uplink commands and formats health telemetry Evidence →

Relay Drive Card (RDC)

Discrete component on/off commanding

The CTP’s RDC provides discrete commands to turn components on and off. Those commands are distinct from the power-regulation function.

GOES-R Relay Drive Card (RDC)
Discrete component on/off commanding Evidence →

Redundancy Management Card (RMC)

Monitors OBC heartbeat and supports recovery

The RMC monitors the flight computer’s heartbeat and supports reboot or reconfiguration after a detected fault. The teaching catalog describes the role, not fault-response timing.

GOES-R Redundancy Management Card (RMC)
Monitors OBC heartbeat and supports recovery Evidence →

On Board Computer (OBC)

Runs flight software and gathers/routes commands and data

The OBC hosts the software that coordinates spacecraft operation, handles instrument data, and communicates with subsystem interfaces.

GOES-R On Board Computer (OBC)
Runs flight software and gathers/routes commands and data Evidence →

SpaceWire Router Card (SWRC)

Collects instrument science data for the Raw Data Link

The SWRC receives instrument science data inside the OBC and formats it for downlink. It is not evidence of an unspecified mass-memory capacity.

GOES-R SpaceWire Router Card (SWRC)
Collects instrument science data for the Raw Data Link Evidence →

Remote Interface Units (RIUs) and SPP Interface Unit (SIU)

Route subsystem commands and collect requested telemetry

These remote interfaces connect the flight computer’s data bus to distributed spacecraft equipment and measurements.

GOES-R Remote Interface Units (RIUs) and SPP Interface Unit (SIU)
Route subsystem commands and collect requested telemetry Evidence →

RIU/SIU converter, control board, and harness backplane

Modular power, data-bus, and board-interface hardware

The RIU/SIU core consists of an Electronic Power Converter board, Control & 1553 Board, and Harness Board/Backplane. The modular interfaces accommodate different equipment functions.

GOES-R RIU/SIU converter, control board, and harness backplane
Modular power, data-bus, and board-interface hardware Evidence →

RIU telemetry and actuator interfaces

Collect analog/status measurements and issue relay, heater, and motor commands

The RIU handles engineering telemetry as well as actuator interfaces. Housekeeping measurements such as current, temperatures, and state flags are distinct from detector science data.

GOES-R RIU telemetry and actuator interfaces
Collect analog/status measurements and issue relay, heater, and motor commands Evidence →

Command memory and data storage

Stores command sequences or data awaiting transmission

Onboard memory stores command sequences for execution and measurement records awaiting transmission. These are different storage roles; this general explanation does not establish a GOES-R recorder type or capacity.

General spacecraft memory
Stores command sequences or data awaiting transmission Evidence →

Boot and recovery memory

Permanent memory can retain processor boot/safe-hold code or a basic programmable-logic configuration

Protected startup storage is distinct from working memory and stored observations. Its drawn package and memory organization are illustrative.

NASA recovery-memory guidance
Permanent memory can retain processor boot/safe-hold code or a basic programmable-logic configuration Evidence →

Memory interface and error-correction logic

Memory interfaces implement error detection and correction appropriate to their application

Error-protection logic belongs at the memory interface. Memory scrubbing is a maintenance operation, not necessarily a separate chip.

NASA memory-protection guidance
Memory interfaces implement error detection and correction appropriate to their application Evidence →

Power-on-reset circuitry

Reset circuitry coordinates startup and protects critical signals while power and clocks settle

Reset circuitry gives the board a controlled starting state. It may be integrated rather than packaged as a separate supervisor.

NASA board-reset guidance
Reset circuitry coordinates startup and protects critical signals while power and clocks settle Evidence →

Spacecraft time counter

A data-system counter schedules activity and time-tags engineering and science data

The spacecraft time counter is a data-handling function. It is distinct from detector sample clocks and the radio reference oscillator.

NASA spacecraft-clock description
A data-system counter schedules activity and time-tags engineering and science data Evidence →

Deployment-position sensors and latch-status indicators

Monitor deployment progress and report lock/latch state through telemetry

Position sensing and latch-status telemetry show whether a deployment completed. The sensor type and placement shown are illustrative.

ECSS mechanism status
Monitor deployment progress and report lock/latch state through telemetry Evidence →

Electronics enclosure and shield terminations

Chassis, seams, cable shields and entry terminations

The chassis, seams, cable shields, and connector entries participate in shielding. The exploded enclosure illustrates these interfaces without a shielding rating.

Electronics shielding interfaces
Chassis, seams, cable shields and entry terminations Evidence →

Radiator panels and thermal insulation

Choose how a surface exchanges radiation

View in 3D
Light Choose how a surface exchanges radiation

A spacecraft surface is part of its thermal design. GOES-R uses radiator finishes that absorb little sunlight while efficiently emitting thermal radiation. Other regions use multilayer insulation to reduce heat exchange. The bright radiator and blanket therefore serve different purposes.

GOES-R radiator panels
Heat pipes spread heat; optical solar reflectors limit solar absorption and emit heat Evidence →
GOES-R heat-flow control
MLI, low-emissivity coatings and low-conductivity stand-offs reduce heat transfer Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Thermistors, heaters and telemetry

Passive radiators continue exchanging heat without a command. Active thermal control adds temperature measurements and heaters. GOES-R uses both thermostatic circuits and computer-controlled heater circuits; the latter use thermistor feedback and adjustable control settings.

GOES-R heater control
Thermostatic circuits and computer-controlled circuits with thermistor feedback Evidence →
GOES-R radiator panels
Heat pipes spread heat; optical solar reflectors limit solar absorption and emit heat Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Spread heat before radiating it

GOES-R embeds heat pipes in radiator panels to spread heat and reduce hot spots. Optical solar reflectors combine low solar absorption with strong thermal emission. Heat flows through the mounting and transport hardware to the panel, then leaves the spacecraft as radiation.

GOES-R radiator panels
Heat pipes spread heat; optical solar reflectors limit solar absorption and emit heat Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 7 component entries

Multilayer insulation and low-conductivity supports

Reduce unwanted thermal exchange

Blankets and thermally isolating supports restrict selected heat paths. They complement the conductive interfaces used where heat needs to leave equipment.

GOES-R Multilayer insulation and low-conductivity supports
Reduce unwanted thermal exchange Evidence →

Optical solar reflectors and radiator heat pipes

Limit solar absorption, spread heat, and emit thermal energy

GOES-R radiators use optical solar reflectors and embedded heat pipes. The surface optical properties and the internal heat-transport function are separate design features.

GOES-R Optical solar reflectors and radiator heat pipes
Limit solar absorption, spread heat, and emit thermal energy Evidence →

Thermostats, thermistors, and heater circuits

Fixed thermostatic control or software control with temperature feedback

The spacecraft uses both mechanical thermostats and computer-controlled heater circuits. These thermistors are distinct from ABI’s cold-head platinum resistance thermometer.

GOES-R Thermostats, thermistors, and heater circuits
Fixed thermostatic control or software control with temperature feedback Evidence →

Conductive equipment mounts

Selected boxes use conductive bonds to equipment panels

A conductive mounting interface carries heat from an electronics chassis to its panel. Other interfaces use dry mounting when enhanced conduction is unnecessary.

GOES-R Conductive equipment mounts
Selected boxes use conductive bonds to equipment panels Evidence →

Adhesives, coatings, insulation, and harness materials

Outgassing evaluation considers sensitive surfaces and cryogenic water deposition

NASA's materials standard calls for vacuum-stability screening and allows stricter evaluation near optical surfaces. Cold optics require particular attention to water deposition. Screening and bakeout are verification processes, not separate flight boxes.

NASA materials selection
Outgassing evaluation considers sensitive surfaces and cryogenic water deposition Evidence →

Thermal-blanket bonding tabs

Bonding tabs connect conductive layers to structure

Tabs connect conductive blanket layers to the spacecraft reference. Thermal insulation alone is not an electromagnetic enclosure.

Blanket electrical connection
Bonding tabs connect conductive layers to structure Evidence →

Charge-dissipative surface coating

Ground-referenced conductive or dissipative surfaces

A grounded dissipative coating can manage surface charge. Material selection must also suit the surface's optical and thermal role.

Surface charge management
Ground-referenced conductive or dissipative surfaces Evidence →

Journey level

The payload

Start with a complete instrument: sensor assembly, instrument electronics chassis and separate cooler controls. Open the enclosures to follow their boards and functions. ABI supplies the named civil packaging example; the drawing is representative. Component stops identify details and connections within that instrument, not an independent box for every function or company.

Sensor assembly / Component detail

Telescope and optical bench

Form an image on a stable bench

View in 3D
Light Form an image on a stable bench

The telescope redirects incoming scene radiation to the image plane. ABI uses a four-mirror telescope and an optical bench that supports the sensor subsystems. The bench holds the optical relationships while the mirrors perform the image-forming work.

ABI image formation
Four-mirror telescope forms images on three focal-plane modules Evidence →
ABI optical bench
Supports the sensor subsystems Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Motor drivers and encoders

In ABI, commanded scan mirrors direct the viewing line before the telescope forms the image. Motor-driver circuitry moves those mirrors, while optical encoders report their position. This is the published civil scan mechanism; the generic cutaway illustrates the image-forming telescope without assigning it ABI’s scan performance.

ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Bench and thermal interfaces

The optical bench carries the instrument components, but the thermal design establishes different paths for the cold optics and the surrounding structure. ABI uses controlled aft-optics regions, cooler connections, and a radiator system. Structural support and thermal conductance have to be designed together.

ABI optical bench
Supports the sensor subsystems Evidence →
ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Optical Bench

Supports the sensor subsystems and carries loads to the spacecraft

The Optical Bench carries the optical, calibration, electronics, and cooling assemblies while transferring instrument loads to the spacecraft.

ABI Optical Bench
Supports the sensor subsystems and carries loads to the spacecraft Evidence →

Telescope Assembly

Four telescope mirrors form images on three focal-plane modules

ABI’s Telescope Assembly forms the scene image and includes the VIS/IR beamsplitter and fold mirror. The two scan mirrors are upstream components, not part of the four-mirror telescope count.

ABI Telescope Assembly
Four telescope mirrors form images on three focal-plane modules Evidence →

Adhesives, coatings, insulation, and harness materials

Outgassing evaluation considers sensitive surfaces and cryogenic water deposition

NASA's materials standard calls for vacuum-stability screening and allows stricter evaluation near optical surfaces. Cold optics require particular attention to water deposition. Screening and bakeout are verification processes, not separate flight boxes.

NASA materials selection
Outgassing evaluation considers sensitive surfaces and cryogenic water deposition Evidence →

Sensor assembly / Component detail

Optical-port baffles and sunshield

Keep unwanted light out of the optical path

View in 3D
Light Keep unwanted light out of the optical path

ABI’s optical-port assembly uses baffles to reduce stray light entering the instrument. Its cover protects the opening from contamination before deployment. Inside the sensor, additional shrouds intercept solar energy that enters the scan cavity and connect that absorbed heat to the rejection system.

ABI optical-port assembly
Baffles reduce stray light; deployable cover protects against contamination Evidence →
ABI scan-shroud heat path
Shields collect solar heat; constant-conductance heat pipes carry it away Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Control the covers and peripheral mechanisms

ABI’s Peripheral and Thermal Control electronics operates mechanisms such as the solar calibration cover and telescope focus motor. It also controls optical-port and calibration-cover launch-lock release. These commands configure physical hardware around the optical path rather than carrying the measured image itself.

ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Carry intercepted solar heat away

ABI’s scan shrouds protect the internal instrument structure when solar energy enters the optical port. The metal shields collect that energy; constant-conductance heat pipes transport it to the radiator and loop-heat-pipe assembly. A baffle can therefore participate in both the light path and the heat path.

ABI scan-shroud heat path
Shields collect solar heat; constant-conductance heat pipes carry it away Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 2 component entries

Optical Port Sunshield Assembly (OPSA)

Baffles reduce stray light entering the sensor

The OPSA defines the optical entrance and reduces stray light. It also supports the solar-calibration assembly and the protective optical-port cover.

ABI Optical Port Sunshield Assembly (OPSA)
Baffles reduce stray light entering the sensor Evidence →

Vented housing and vent passages

Vents and blanket venting are directed away from sensitive items

ECSS recommends directing instrument and blanket vents away from contamination-sensitive items. A representative cutaway can identify the housing opening and its routed passage.

ECSS cleanliness-oriented design
Vents and blanket venting are directed away from sensitive items Evidence →

Sensor assembly / Component detail

Focal-plane modules

Choose a band, then detect the image

View in 3D
Light Choose a band, then detect the image

ABI separates incoming radiation with beamsplitters and places channel filters above its detector arrays. Each focal-plane array combines a detector array with a readout integrated circuit. The module converts the filtered image into analog electrical signals for the video electronics.

ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
ABI detector output
Filtered scene image becomes analog electrical signals Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Read the detector through its integrated circuit

A detector array is paired with a readout integrated circuit in ABI’s focal-plane array. The module supplies analog signals to the video processors. Readout is therefore a distinct step between the absorbing detector elements and the electronics that will digitize and package their measurements.

ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
ABI detector output
Filtered scene image becomes analog electrical signals Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Remove heat from the focal planes

The focal planes sit at the cold end of ABI’s thermal system. Its active cooler transports heat toward loop heat pipes, which carry it to the radiator for rejection. The cooler does not destroy heat: it provides a path from the cold assembly to the warmer rejection hardware.

ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Focal Plane Modules (FPMs)

Filter the image and produce analog signals

ABI has VNIR, MWIR, and LWIR modules. A module groups filtered channel assemblies and converts the image to analog signals for the video electronics.

ABI Focal Plane Modules (FPMs)
Filter the image and produce analog signals Evidence →

Focal Plane Array (FPA)

One channel’s detector array plus its ROIC

An ABI FPA combines a detector array and its associated Read-Out Integrated Circuit for one spectral channel. The larger FPM can contain several such channel assemblies.

ABI Focal Plane Array (FPA)
One channel’s detector array plus its ROIC Evidence →

Read-Out Integrated Circuit (ROIC)

Electrical readout associated with each detector array

The ROIC is part of the focal-plane array. The separately mounted Video Processors are the next interface and must not be drawn or described as the same device.

ABI Read-Out Integrated Circuit (ROIC)
Electrical readout associated with each detector array Evidence →

Sensor assembly / Component detail

Sensor Unit Electronics

Carry the electrical image out of the detector

View in 3D
Light Carry the electrical image out of the detector

The detector and its readout integrated circuit belong together at the focal plane. ABI’s video processors form the next interface: they supply the timing and bias needed to read the arrays and collect their samples. The optical image has now become an ordered electrical measurement.

ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Video-processing interface

ABI’s video processors generate focal-plane timing signals and bias voltages, collect detector samples, and format them for the Electronics Unit. Bias establishes the electrical operating conditions; timing determines when the arrays are read. The detector’s physical arrangement and the outgoing sample stream are different descriptions of the same measurement chain.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat ROIC and video-processing hardware

ABI’s focal-plane array includes its readout integrated circuit. The video-processing electronics is a separate part of the Sensor Unit Electronics. The instrument therefore needs both a controlled detector environment and electrical connections to the electronics that supplies readout timing, bias, and sample handling.

ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Sensor Unit Electronics (SUE)

Video Processors plus Peripheral and Thermal Control electronics

The SUE resides in the Sensor Unit. Its circuit cards digitize focal-plane data and control sensor-unit mechanisms and temperatures.

ABI Sensor Unit Electronics (SUE)
Video Processors plus Peripheral and Thermal Control electronics Evidence →

Video Processors: bias interface

Provide detector-array operating bias voltages

ABI’s Video Processors provide the bias voltages used to read the focal-plane arrays. Bias supplies establish electrical operating conditions; the readout timing controls when samples are collected.

ABI Video Processors: bias interface
Provide detector-array operating bias voltages Evidence →

Video Processors: readout timing

Generate the timing used to read focal-plane arrays

Readout timing coordinates the collection of detector samples. It belongs to the VP interface and is distinct from the EU’s system-clock card.

ABI Video Processors: readout timing
Generate the timing used to read focal-plane arrays Evidence →

Video Processors: sample collection

Collect and format samples for the EU Data Processor

The VP collects the arrays’ samples and formats them for transmission to the Data Processor in the Electronics Unit.

ABI Video Processors: sample collection
Collect and format samples for the EU Data Processor Evidence →

Sensor assembly / Component detail

Analog-to-digital conversion circuitry

Represent the samples as numbers

View in 3D
Light Represent the samples as numbers

ABI’s focal-plane modules produce analog signals, and its Sensor Unit Electronics digitizes the focal-plane data. This selectable circuit region is inside the sensor-side electronics, alongside readout functions. It is a functional close-up within an assembly; the public description does not establish a standalone converter board or enclosure.

ABI detector output
Filtered scene image becomes analog electrical signals Evidence →
ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Digitize → format → transmit

The Sensor Unit Electronics digitizes ABI’s focal-plane data. The Electronics Unit’s Data Processor then formats and packetizes the detector data supplied by the video processor, and its High Speed I/O card provides the SpaceWire interface to the spacecraft. Conversion, packet formation, and transport are separate functions.

ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Place conversion at the correct thermal boundary

ABI’s digitization belongs to the Sensor Unit Electronics, where readout, bias and peripheral functions are coordinated with the sensor. It does not belong to the separate EU merely because both contain electronics. This cutaway keeps the conversion circuitry on the sensor side; detailed circuit dissipation and mounting conductance are unspecified.

ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Analog-to-digital conversion electronics

SUE circuit cards digitize the focal-plane data

The source establishes an analog-to-digital function inside the Sensor Unit Electronics. The cutaway identifies a circuit region within that assembly; no separate ADC board or enclosure is established by the public description.

ABI Focal-plane digitization
SUE circuit cards digitize the focal-plane data Evidence →

Sensor assembly / Component detail

Scan mirrors and drive assembly

Steer incoming radiation into the telescope

View in 3D

The scan mirrors, motors and encoders are in the sensor assembly; ABI’s scan-drive and encoder-processing cards are in the Electronics Unit.

Light Steer incoming radiation into the telescope

ABI places independently driven scan mirrors ahead of its telescope. Mirror rotation redirects the line of sight while the telescope and focal-plane assemblies remain mounted to the optical bench. The two exposed axes in this teaching assembly separate the mirror surface, shaft, bearing support, motor and position encoder.

ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Close the mirror-position control loop

The instrument controller coordinates the requested scan with the timing electronics. Motor-driver circuitry supplies the actuators, and encoder circuitry measures mirror position. Position information accompanies the optical sampling process; the moving mirror, its position sensor and its driver are distinct hardware.

ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Support moving optics and remove absorbed heat

The scan assembly combines motorized hardware with an optical entrance. ABI uses surrounding scan shrouds to intercept unwanted solar energy and heat pipes to move that absorbed heat away. Bearings and mounting structure support motion; the shroud supplies a separate thermal path.

ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
ABI scan-shroud heat path
Shields collect solar heat; constant-conductance heat pipes carry it away Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 9 component entries

NS and EW Scan Mirror Assemblies

Orthogonal mirrors steer the line of sight in separate directions

ABI uses separate north–south and east–west scan mirrors. Each assembly combines its mirror, drive assembly, and support bearing.

ABI NS and EW Scan Mirror Assemblies
Orthogonal mirrors steer the line of sight in separate directions Evidence →

Scan Drive Assembly (SDA)

Bench-mounted motor drives one side of a scan mirror

Each SDA supports one side of its mirror and applies motor motion. The separate support bearing anchors the opposite side.

ABI Scan Drive Assembly (SDA)
Bench-mounted motor drives one side of a scan mirror Evidence →

Optical encoder

Reports scan-mirror position

An optical encoder measures the mirror’s position. Its measurement is distinct from the electrical command sent to the motor.

ABI Optical encoder
Reports scan-mirror position Evidence →

Support Bearing Assembly

Supports the opposite side of the scan mirror

The support bearing mounts to the Optical Bench and supports the mirror opposite the Scan Drive Assembly.

ABI Support Bearing Assembly
Supports the opposite side of the scan mirror Evidence →

Scanner Interface & Motor Driver (SIMD)

EU circuit card controls scan-mirror motion

The SIMD card belongs to ABI’s Electronics Unit and drives the Scan Drive Assembly motors. It is separate from the optical encoders and their processor cards.

ABI Scanner Interface & Motor Driver (SIMD)
EU circuit card controls scan-mirror motion Evidence →

EW and NS Encoder Processors

Power optical encoders and compute scan-mirror position

The Encoder Processor cards sit inside the Electronics Unit chassis. They power the optical encoders on the scan mechanism and calculate mirror position. The motor-driver card supplies motion; the encoder-processing path reports position.

ABI EW and NS Encoder Processors
Power optical encoders and compute scan-mirror position Evidence →

Pressure-equalization vent passages

Venting accommodates ascent depressurization while controlling particle contamination

Enclosures may need vent passages for ascent. Sealed or pressure-qualified hardware is a different case; a vent is not automatically appropriate everywhere.

ECSS mechanism venting
Venting accommodates ascent depressurization while controlling particle contamination Evidence →

Harness clamps and strain-relief supports

Protect electrical connections from harness loads and verify repeatable routing through motion

Clamps and strain relief keep moving wiring from loading its electrical connections. Routes and supports are representative.

ECSS moving harness
Protect electrical connections from harness loads and verify repeatable routing through motion Evidence →

Bearing lubricant or lubricating surface and migration barrier

Qualify lubrication for the mission; contain fluid migration where sensitive equipment requires it

Bearings require suitable tribology; any lubricant and migration-control approach depend on the mechanism and its environment.

ECSS mechanism tribology
Qualify lubrication for the mission; contain fluid migration where sensitive equipment requires it Evidence →

Sensor assembly / Component detail

Port-cover and focus mechanisms

Protect the entrance and adjust optical focus

View in 3D
Light Protect the entrance and adjust optical focus

The optical-port cover protects the instrument before deployment. A separate telescope focus motor adjusts the optical assembly. ABI assigns cover and focus control to its peripheral electronics. The drawing opens the cover on a hinge and separates the focus actuator so their different jobs are visible.

ABI Shape-memory-alloy pin-puller launch lock
Nonexplosive release for the optical-port cover Evidence →
ABI Spring-loaded cover hinges and stop
Open the released cover and capture it at a stop Evidence →
ABI Solar Calibration Cover (SCC)
Motor-driven calibration cover with a launch lock Evidence →
ABI optical-port assembly
Baffles reduce stray light; deployable cover protects against contamination Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Command actuators through peripheral electronics

ABI’s Sensor Unit Electronics release the optical-port and solar-calibration cover launch locks. The optical-port cover then opens on spring-loaded hinges. Peripheral and Thermal Control electronics operate the motor-driven solar-calibration cover and telescope focus mechanism alongside heater functions. The drawn hinge and actuator packaging are representative.

ABI Shape-memory-alloy pin-puller launch lock
Nonexplosive release for the optical-port cover Evidence →
ABI Spring-loaded cover hinges and stop
Open the released cover and capture it at a stop Evidence →
ABI Solar Calibration Cover (SCC)
Motor-driven calibration cover with a launch lock Evidence →
ABI optical-port assembly
Baffles reduce stray light; deployable cover protects against contamination Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Keep mechanisms within their thermal environment

Mechanical interfaces also conduct heat. ABI combines mechanism control and thermal-control functions in its peripheral electronics, while its operational, survival and outgas heaters serve different purposes. No motor duty cycle or mechanism operating temperature is assigned to this drawing.

ABI Shape-memory-alloy pin-puller launch lock
Nonexplosive release for the optical-port cover Evidence →
ABI Spring-loaded cover hinges and stop
Open the released cover and capture it at a stop Evidence →
ABI Solar Calibration Cover (SCC)
Motor-driven calibration cover with a launch lock Evidence →
ABI optical-port assembly
Baffles reduce stray light; deployable cover protects against contamination Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
ABI heater functions
Survival, operational and outgas heating Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 10 component entries

Optical Port Cover (OPC)

One-time deployable protective cover

The OPC protects ABI before deployment. It is a launch-protection cover, not a repeatedly operated imaging shutter.

ABI Optical Port Cover (OPC)
One-time deployable protective cover Evidence →

Shape-memory-alloy pin-puller launch lock

Nonexplosive release for the optical-port cover

The cover is secured by a nonexplosive pin-puller launch lock. Releasing that lock allows the spring-loaded cover hinges to open.

ABI Shape-memory-alloy pin-puller launch lock
Nonexplosive release for the optical-port cover Evidence →

Spring-loaded cover hinges and stop

Open the released cover and capture it at a stop

The hinges open the released OPC, and a mechanical stop captures it. The source describes a Velcro strip at the stop; the teaching model need not reproduce that fastening detail.

ABI Spring-loaded cover hinges and stop
Open the released cover and capture it at a stop Evidence →

Telescope focus motor

Moves one telescope mirror for focus adjustment

One telescope mirror is motor-adjustable for focus. The P&TC motor driver can be switched between the focus motor and the Solar Calibration Cover.

ABI Telescope focus motor
Moves one telescope mirror for focus adjustment Evidence →

Solar Calibration Cover (SCC)

Motor-driven calibration cover with a launch lock

The SUE controls release of the SCC launch lock, and its P&TC electronics drive the SCC motor. This cover is distinct from the one-time Optical Port Cover.

ABI Solar Calibration Cover (SCC)
Motor-driven calibration cover with a launch lock Evidence →

Deployment-position sensors and latch-status indicators

Monitor deployment progress and report lock/latch state through telemetry

Position sensing and latch-status telemetry show whether a deployment completed. The sensor type and placement shown are illustrative.

ECSS mechanism status
Monitor deployment progress and report lock/latch state through telemetry Evidence →

Pressure-equalization vent passages

Venting accommodates ascent depressurization while controlling particle contamination

Enclosures may need vent passages for ascent. Sealed or pressure-qualified hardware is a different case; a vent is not automatically appropriate everywhere.

ECSS mechanism venting
Venting accommodates ascent depressurization while controlling particle contamination Evidence →

Harness clamps and strain-relief supports

Protect electrical connections from harness loads and verify repeatable routing through motion

Clamps and strain relief keep moving wiring from loading its electrical connections. Routes and supports are representative.

ECSS moving harness
Protect electrical connections from harness loads and verify repeatable routing through motion Evidence →

Bearing lubricant or lubricating surface and migration barrier

Qualify lubrication for the mission; contain fluid migration where sensitive equipment requires it

Bearings require suitable tribology; any lubricant and migration-control approach depend on the mechanism and its environment.

ECSS mechanism tribology
Qualify lubrication for the mission; contain fluid migration where sensitive equipment requires it Evidence →

Instrument purge connection

A defined mechanical connection links instrument and ground purge equipment

NASA's hosted-payload guidance separates the instrument's purge connection from the ground equipment that filters, conditions, and regulates the supplied gas.

NASA instrument purge interface
A defined mechanical connection links instrument and ground purge equipment Evidence →

Sensor assembly / Component detail

Calibration targets and reference views

Observe known references as well as Earth

View in 3D
Light Observe known references as well as Earth

ABI uses an internal infrared calibration target, a solar calibration target for reflected-solar channels, and a view of space. These are distinct reference observations. The drawn cavity and diffuser represent the named civil instrument’s two target types; space is a viewing direction, not another object inside the payload.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →
ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →
ABI Space-look reference
Background observations support all ABI channels Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Associate samples with the reference observation

Calibration needs both the selected reference and a record of the instrument state. The controller commands the observation, scan encoders describe the mirror position, and peripheral electronics support the target. Calibration processing can then distinguish reference samples from Earth-view samples.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →
ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →
ABI Space-look reference
Background observations support all ABI channels Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Measure and control the thermal reference

The infrared target provides a controlled thermal reference. ABI’s peripheral electronics include target and thermal-control functions. A solar diffuser has a different role: it redirects sunlight for the reflected-solar channels and is not a blackbody source for the thermal-infrared detector.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →
ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →
ABI Space-look reference
Background observations support all ABI channels Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Internal Calibration Target (ICT)

Full-aperture blackbody reference for the infrared channels

ABI’s MWIR and LWIR channels observe the ICT as a blackbody thermal reference. Its measured temperature determines the reference radiance used for calibration.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →

Solar Calibration Target (SCT)

Diffuse white target reflects sunlight into the optical system

The SCT supplies a sunlight reference for ABI’s VNIR channels. It is part of the Solar Calibration Assembly within the OPSA and is separate from the infrared blackbody target.

ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →

Space-look reference

Background observations support all ABI channels

ABI also observes space to measure its background signal. A space look is a viewing direction, not an additional onboard calibration object.

ABI Space-look reference
Background observations support all ABI channels Evidence →

Sensor assembly / Component detail

Beamsplitters, filters and cold stops

Divide the image into spectral channels

View in 3D
Light Divide the image into spectral channels

After the telescope, ABI’s beamsplitters divide the radiation among spectral regions. Channel filters define which wavelengths reach each array, while windows and cold stops complete the optical interfaces. The exploded deck separates these stationary elements; it does not depict a filter wheel.

ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Preserve channel identity at the readout

A spectral channel is a physical optical selection paired with its detector and readout. In ABI, filters and focal-plane arrays are grouped into modules. The electronics must preserve that channel identity when detector outputs are digitized and organized into data.

ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Bound the detector’s optical environment

Cold stops and cooled aft optics help define the radiation environment seen by the detector. They are distinct from the active refrigeration that removes heat. The illustrated stop, filter mounts and window occupy separate supports so the optical and thermal responsibilities remain visible.

ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 5 component entries

VIS/IR beamsplitter (BS1)

Separates VNIR from infrared radiation

BS1 sends the infrared and VNIR portions into different optical paths. The fold mirror directs the transmitted VNIR path toward its module.

ABI VIS/IR beamsplitter (BS1)
Separates VNIR from infrared radiation Evidence →

Fold mirror

Redirects the VNIR path toward its focal-plane module

The fold mirror turns the VNIR path after the first beamsplitter. It is named separately from the four image-forming telescope mirrors.

ABI Fold mirror
Redirects the VNIR path toward its focal-plane module Evidence →

MW/LW beamsplitter (BS2)

Separates the MWIR and LWIR paths

The second beamsplitter divides the infrared path into MWIR and LWIR portions before the channel-filtered focal-plane modules.

ABI MW/LW beamsplitter (BS2)
Separates the MWIR and LWIR paths Evidence →

Channel filters

Bandpass filters select individual spectral channels

The beamsplitters divide broad spectral regions; filters above the detector arrays select individual ABI channels. These functions should not be conflated.

ABI Channel filters
Bandpass filters select individual spectral channels Evidence →

Windows and cold stops

Named elements within the controlled cryogenic aft optics

ABI’s aft optics contains windows and cold stops and maintains the focal-plane modules in a controlled cryogenic environment. The drawing’s stop sizes and enclosure shapes remain representative.

ABI Windows and cold stops
Named elements within the controlled cryogenic aft optics Evidence →

Instrument electronics assembly / Component detail

Instrument controller and timing cards

Coordinate the optics and electronics

View in 3D

The main controller and timing cards are in ABI’s Electronics Unit. The related Peripheral and Thermal Control card is in the Sensor Unit Electronics.

Light Coordinate the optics and electronics

ABI’s Electronics Unit contains an instrument-controller computer, system timing, scan-control circuitry, and a spacecraft interface. The controller operates the instrument while the timing electronics generate clocks. Moving an optical mechanism and reading its detector must be coordinated within the same instrument.

ABI instrument controller
A single-board computer operates the instrument Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Keep clocks, commands and telemetry together

ABI’s controller computer and Telemetry and Timing card share the Electronics Unit chassis with data, power and scanner-control cards. The Peripheral and Thermal Control card is in the Sensor Unit Electronics and receives commands from the EU timing card. One coordinated instrument can therefore span several housings without making every function a separate box.

ABI instrument controller
A single-board computer operates the instrument Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Operational and survival control

ABI uses operational heaters to control temperatures, survival heaters when normal instrument power is absent, and outgas heaters before cooling its aft optics. The Peripheral and Thermal Control electronics commands several of these functions. An instrument thermal system has to prevent both excessive heating and excessive cooling.

ABI heater functions
Survival, operational and outgas heating Evidence →
ABI peripheral controls
Calibration target, heaters, covers and telescope focus motor Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Electronics Unit (EU)

Main spacecraft interface with power, control, data, and scan electronics

The EU houses the instrument’s principal power and processing interfaces in a chassis with a parent board and circuit-card assemblies.

ABI Electronics Unit (EU)
Main spacecraft interface with power, control, data, and scan electronics Evidence →

Instrument Controller (IC)

Single-board computer operates ABI

The IC runs instrument operations. It is a named EU card, distinct from the spacecraft’s On Board Computer.

ABI Instrument Controller (IC)
Single-board computer operates ABI Evidence →

Peripheral and Thermal Control (P&TC)

Controls sensor-unit thermal hardware and mechanisms except the scanner

The P&TC card is part of the Sensor Unit Electronics. It handles calibration-target temperature, VNIR-module temperature, heat-pipe and outgas heaters, covers, and telescope focus. Scanner motion has separate drive cards inside the Electronics Unit.

ABI Peripheral and Thermal Control (P&TC)
Controls sensor-unit thermal hardware and mechanisms except the scanner Evidence →

P&TC command and telemetry interface

Serial control link to the EU Telemetry and Timing card

The P&TC receives control information over a serial interface from the Telemetry and Timing card in the EU.

ABI P&TC command and telemetry interface
Serial control link to the EU Telemetry and Timing card Evidence →

Instrument electronics assembly / Component detail

Data processor and interface cards

Carry observations beyond the optical assembly

View in 3D
Light Carry observations beyond the optical assembly

Once the focal-plane signal has been digitized, its route continues through electronics. ABI’s Data Processor prepares the samples for transmission and its High Speed I/O card connects with the spacecraft using SpaceWire. These are downstream of the detector and video electronics.

ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Format data and cross the spacecraft interface

ABI’s Data Processor, High Speed I/O and timing cards share its Electronics Unit chassis. The Data Processor organizes samples into packets, HSIO communicates with the spacecraft and the timing card supplies clocks and telemetry services. They are coordinated cards within one electrical assembly, with distinct functional responsibilities.

ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Conduct electronics heat through the chassis

The interface and processing cards consume electrical power and belong to the instrument’s warm Electronics Unit. GOES-R mounts that unit on thermally controlled equipment panels. Card supports, chassis and panel interfaces form a heat path separate from the cold detector assembly.

ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Data Processor

Formats and packetizes detector data

The EU Data Processor receives data from the Video Processor and forms packets. Packet formation is separate from earlier digitization in the Sensor Unit.

ABI Data Processor
Formats and packetizes detector data Evidence →

High Speed I/O (HSIO)

SpaceWire communications interface to the spacecraft

The HSIO card is ABI’s EU communications interface to the spacecraft. It communicates through SpaceWire, downstream of the Data Processor’s formatting and packetization.

ABI High Speed I/O (HSIO)
SpaceWire communications interface to the spacecraft Evidence →

Telemetry and Timing (TNT)

Generates system clocks and handles ABI telemetry

The TNT card supplies system timing and handles telemetry. Detector readout timing and peripheral control are coordinated through their respective interfaces.

ABI Telemetry and Timing (TNT)
Generates system clocks and handles ABI telemetry Evidence →

Instrument electronics assembly / Component detail

Instrument power-supply card

Supply the instrument’s electrical assemblies

View in 3D
Light Supply the instrument’s electrical assemblies

The telescope does not supply its own operating power. ABI’s Electronics Unit converts spacecraft input power into instrument supplies. The resulting feeds support controllers, readout electronics and mechanism-related circuitry; the cryocooler also has its own control electronics.

ABI electronics power
Power supply converts spacecraft input to instrument rails Evidence →
GOES-R load distribution
Power-feed switches, current sensing and overcurrent fuses Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Separate supply conversion from command handling

A power-supply card converts electrical input, while command and timing cards coordinate instrument operation. These functions share ABI’s Electronics Unit chassis and parent board. The cutaway exposes the supply card inside that common enclosure so the power path can be followed alongside the internal data and control connections.

ABI electronics power
Power supply converts spacecraft input to instrument rails Evidence →
GOES-R load distribution
Power-feed switches, current sensing and overcurrent fuses Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Carry conversion heat to the mounting panel

Electrical conversion is part of the instrument’s heat load. The Electronics Unit rejects heat through its spacecraft equipment-panel interface. The cold head is served by the cooler and its dedicated thermal transport, so instrument electronics and detector cooling are represented as separate branches.

ABI electronics power
Power supply converts spacecraft input to instrument rails Evidence →
GOES-R load distribution
Power-feed switches, current sensing and overcurrent fuses Evidence →
GOES-R electronics mounting
Equipment panels conduct and radiate heat toward spacecraft radiators Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

EU Power Supply

Converts spacecraft input into ABI electronics supply voltages

The EU Power Supply converts the spacecraft input into the electrical supplies required by ABI electronics. It supplies power rather than interpreting commands or detector samples.

ABI EU Power Supply
Converts spacecraft input into ABI electronics supply voltages Evidence →

EU parent board and redundant card sets

Parent board and CCAs provide separate Side 1/Side 2 electronics

The published EU includes a parent board and redundant circuit-card sets. Connector positions and traces in the model are illustrative.

ABI EU parent board and redundant card sets
Parent board and CCAs provide separate Side 1/Side 2 electronics Evidence →

SUE redundant electronics

Separate Side 1/Side 2 electronics

ABI’s SUE is described as Side 1/Side 2 redundant. Redundancy is a system property; the representative cutaway need not reproduce the complete duplicated wiring.

ABI SUE redundant electronics
Separate Side 1/Side 2 electronics Evidence →

Cooler-control assembly / Component detail

Cryocooler and control electronics

Give the image plane a controlled environment

View in 3D

This view spans the separately mounted cooler controls, the cooler in the sensor assembly, and the heat-transport and radiator hardware.

Light Give the image plane a controlled environment

ABI’s aft optics includes windows, cold stops, and a controlled cryogenic environment around the focal-plane modules. The cooler removes heat from that cold region and transfers it toward loop heat pipes and a radiator. The optical and thermal layouts meet at the detector.

ABI aft optics
Beamsplitters, channel filters, windows and cold stops Evidence →
ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Control the cooler with temperature feedback

ABI’s cryocooler controller reads a platinum resistance thermometer at the cold head. It adjusts the power-amplifier duty cycle to hold the temperature set point. The temperature measurement, control electronics, and cooler power stage close the feedback loop.

ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Reject heat from both cooler and controller

ABI’s thermal dynamic unit moves focal-plane heat toward the loop heat pipes and radiator. Its cryocooler control electronics mounts on the spacecraft and rejects its own waste heat there. The cold head and the electronics that drive it occupy different places in the overall thermal network.

ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 12 component entries

Two-stage pulse-tube cryocooler

Pumps focal-plane heat toward the radiator/heat-pipe assembly

ABI’s published cooler is a two-stage pulse-tube design. Its heat-rejection path ends at the radiator through the loop heat pipes.

ABI Two-stage pulse-tube cryocooler
Pumps focal-plane heat toward the radiator/heat-pipe assembly Evidence →

Thermal Dynamic Unit (TDU)

Integral cooler, remote cold head, and transfer line

The TDU is the thermomechanical part of each ABI cooler. Its remote cold head and transfer line are separate named elements, not electronics cards.

ABI Thermal Dynamic Unit (TDU)
Integral cooler, remote cold head, and transfer line Evidence →

Remote cold head

Cold region monitored by the CCE thermometer

The remote cold head belongs to the TDU. A platinum resistance thermometer reports its temperature to the separate Cryocooler Control Electronics.

ABI Remote cold head
Cold region monitored by the CCE thermometer Evidence →

Cryocooler Control Electronics (CCE)

Operates the cooler and controls cold-head temperature

The CCE mounts to the spacecraft and operates the TDU in the Sensor Unit. Its own waste heat is rejected through the spacecraft.

ABI Cryocooler Control Electronics (CCE)
Operates the cooler and controls cold-head temperature Evidence →

Platinum resistance thermometer (PRT)

Measures cold-head temperature for feedback

The PRT is the specified ABI cold-head sensor. It should not be labeled a thermistor; GOES-R uses thermistors elsewhere for spacecraft heater control.

ABI Platinum resistance thermometer (PRT)
Measures cold-head temperature for feedback Evidence →

Cryocooler power amplifiers

Duty cycle adjusted to maintain the cold-head set point

The CCE adjusts the amplifier duty cycle using measured cold-head temperature. This is a temperature-control function, not detector signal amplification.

ABI Cryocooler power amplifiers
Duty cycle adjusted to maintain the cold-head set point Evidence →

Redundant cryocooler units

Can operate individually or together

ABI’s published design has redundant cooler units, each comprising a TDU and CCE. The representative diagram may show one functional path without claiming the hardware count is reproduced.

ABI Redundant cryocooler units
Can operate individually or together Evidence →

Scan Shroud Assembly

Shields collect solar heat in the scan cavity

The scan shrouds intercept solar energy entering the optical port and route the absorbed heat toward the radiator. They are distinct from the cold-stop region around the focal planes.

ABI Scan Shroud Assembly
Shields collect solar heat in the scan cavity Evidence →

Constant-conductance heat pipes

Carry scan-shroud heat to the radiator/LHP assembly

Constant-conductance heat pipes connect the scan shrouds to the rejection assembly. The book separately names loop heat pipes as the instrument-to-radiator interface.

ABI Constant-conductance heat pipes
Carry scan-shroud heat to the radiator/LHP assembly Evidence →

Loop Heat Pipe (LHP) Assembly

Transports Sensor Unit heat to the radiator

The LHP assembly carries excess Sensor Unit energy to its radiator. It is a heat-transport component, not an electrical power cable.

ABI Loop Heat Pipe (LHP) Assembly
Transports Sensor Unit heat to the radiator Evidence →

Thermal Control Radiator

Releases Sensor Unit thermal energy to space

The radiator is the final radiative rejection surface for the instrument thermal path.

ABI Thermal Control Radiator
Releases Sensor Unit thermal energy to space Evidence →

Survival, operational, and outgas heaters

Protect, control, or warm the Sensor Unit for distinct purposes

Survival heaters protect an unpowered instrument; operational heaters regulate temperatures; outgas heaters warm optical hardware before cryogenic operation. Those are different heater functions.

ABI Survival, operational, and outgas heaters
Protect, control, or warm the Sensor Unit for distinct purposes Evidence →

Journey level

The focal plane

A detector package is an optical surface, an electronic assembly, and a thermal load at once. This open teaching assembly separates its cold detector and readout from the warm video electronics. ABI provides the cited civil example; geometry and packaging remain representative.

Detector array and readout integrated circuit

The image plane

View in 3D
Light The image plane

The optical image lands on the detector array. The readout integrated circuit measures the detector signals; it is part of the focal-plane module, rather than the larger warm electronics board beside it. ABI explicitly separates the detector/ROIC module from its video-processing electronics.

ABI focal-plane array
Detector array and associated readout integrated circuit per spectral channel Evidence →
ABI analog path
Focal-plane output to Video Processor Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Data Close to the detector

ABI defines the focal-plane array for each spectral channel as a detector array and associated ROIC. The focal-plane module groups the arrays and filters for a spectral region. This is where detector outputs become an organized electrical readout. The larger board beside the cold plate represents later video processing, not a second detector array.

ABI focal-plane array
Detector array and associated readout integrated circuit per spectral channel Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Heat The cold electronic assembly

Cooling can reduce thermal noise. The detector and nearby ROIC are parts of an electronic assembly with a thermal design; a material name alone does not specify its operating temperature. TIRS-2 supplies a separately named civil temperature example.

ABI focal-plane array
Detector array and associated readout integrated circuit per spectral channel Evidence →
Cryogenic cooling
Can reduce thermal noise Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Inside this assembly 3 component entries

Focal Plane Array (FPA)

One channel’s detector array plus its ROIC

An ABI FPA combines a detector array and its associated Read-Out Integrated Circuit for one spectral channel. The larger FPM can contain several such channel assemblies.

ABI Focal Plane Array (FPA)
One channel’s detector array plus its ROIC Evidence →

Read-Out Integrated Circuit (ROIC)

Electrical readout associated with each detector array

The ROIC is part of the focal-plane array. The separately mounted Video Processors are the next interface and must not be drawn or described as the same device.

ABI Read-Out Integrated Circuit (ROIC)
Electrical readout associated with each detector array Evidence →

Focal Plane Modules (FPMs)

Filter the image and produce analog signals

ABI has VNIR, MWIR, and LWIR modules. A module groups filtered channel assemblies and converts the image to analog signals for the video electronics.

ABI Focal Plane Modules (FPMs)
Filter the image and produce analog signals Evidence →

Window and cold-stop assembly

Control the optical entrance

View in 3D
Light Control the optical entrance

The aft optics give the detector a controlled optical environment. ABI includes windows and cold stops with its cryogenic focal-plane optics. The open-sided shield shows the idea of defining an entrance around a detector; it is not an ABI enclosure drawing.

ABI aft optics
Windows and cold stops in a controlled cryogenic environment Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Data Keep optics distinct from readout

The shield and optical entrance condition the detector’s environment. They are different from the electronic functions that bias, clock, and read the detector. ABI’s published component descriptions distinguish these optical and electronic responsibilities.

ABI aft optics
Windows and cold stops in a controlled cryogenic environment Evidence →
ABI detector electronics
Timing, bias, and array readout Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Heat A separate thermal region

ABI’s windows and cold stops belong to its controlled cryogenic optical environment. Keeping that region distinct from warm surrounding equipment is part of the instrument design. Blue in this cutaway identifies a role, not a temperature measurement.

ABI aft optics
Windows and cold stops in a controlled cryogenic environment Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Inside this assembly 1 component entries

Windows and cold stops

Named elements within the controlled cryogenic aft optics

ABI’s aft optics contains windows and cold stops and maintains the focal-plane modules in a controlled cryogenic environment. The drawing’s stop sizes and enclosure shapes remain representative.

ABI Windows and cold stops
Named elements within the controlled cryogenic aft optics Evidence →

Detector carrier and mounting frame

Keep the optical assembly supported

View in 3D
Light Keep the optical assembly supported

A mount connects the instrument to its supporting structure and is also a thermal interface. GOES-R uses titanium mounting feet to thermally isolate ABI from its platform. The carrier, standoffs, and fasteners drawn here illustrate that support problem at package scale; their materials and spacing are drawing choices.

GOES-R ABI mounting
Thermal isolation at titanium mounting feet Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Data A supported electrical interface

This drawing puts the package on a carrier and fixes the warm board to a separate tray. Fasteners, strain relief, and connector shells show how the chosen interconnect is held in place. Their number and arrangement are representative drawing choices.

Drawing
Representative cutaway / not to scale Evidence →
Heat Support and isolation

GOES-R’s thermal design isolates ABI at its mounting feet and gives the instrument dedicated heat-rejection hardware. Structural support and intended heat-removal paths therefore need separate treatment. The carrier and standoffs here make those interfaces visible.

GOES-R ABI mounting
Thermal isolation at titanium mounting feet Evidence →
ABI heat rejection
Cryocooler, loop heat pipes, radiator Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Inside this assembly 1 component entries

Optical Bench

Supports the sensor subsystems and carries loads to the spacecraft

The Optical Bench carries the optical, calibration, electronics, and cooling assemblies while transferring instrument loads to the spacecraft.

ABI Optical Bench
Supports the sensor subsystems and carries loads to the spacecraft Evidence →

Detector-package interconnect

From package to board

View in 3D
Light From package to board

The gold ribbon separates the detector package from the board in this drawing. Its bends, contacts, and visible conductors make the connection readable. It illustrates an interconnect without specifying the cable construction used by ABI.

Drawing
Representative cutaway / not to scale Evidence →
Data More than one electrical role

An array needs controlled bias and timing as well as an output path. ABI’s Sensor Unit Electronics provide these functions. The broad ribbon stands for the package interconnect; visible trace count and routing are illustrative.

ABI detector electronics
Timing, bias, and array readout Evidence →
ABI analog path
Focal-plane output to Video Processor Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Heat Drawn interconnect

The representative ribbon bridges the cold package and warm board. Its physical route is drawn alongside the separate thermal strap to distinguish electrical connection from the intended heat-removal path. No thermal conductance is assigned to the ribbon.

Drawing
Representative cutaway / not to scale Evidence →
Inside this assembly 3 component entries

Video Processors: bias interface

Provide detector-array operating bias voltages

ABI’s Video Processors provide the bias voltages used to read the focal-plane arrays. Bias supplies establish electrical operating conditions; the readout timing controls when samples are collected.

ABI Video Processors: bias interface
Provide detector-array operating bias voltages Evidence →

Video Processors: readout timing

Generate the timing used to read focal-plane arrays

Readout timing coordinates the collection of detector samples. It belongs to the VP interface and is distinct from the EU’s system-clock card.

ABI Video Processors: readout timing
Generate the timing used to read focal-plane arrays Evidence →

Adhesives, coatings, insulation, and harness materials

Outgassing evaluation considers sensitive surfaces and cryogenic water deposition

NASA's materials standard calls for vacuum-stability screening and allows stricter evaluation near optical surfaces. Cold optics require particular attention to water deposition. Screening and bakeout are verification processes, not separate flight boxes.

NASA materials selection
Outgassing evaluation considers sensitive surfaces and cryogenic water deposition Evidence →

Warm video electronics

After the focal-plane module

View in 3D
Light After the focal-plane module

The detector/ROIC assembly and the warm video board have different jobs. ABI sends analog detector outputs to its Video Processor. The board shows connectors, component packages, and traces so that this next stage has a physical place.

ABI focal-plane array
Detector array and associated readout integrated circuit per spectral channel Evidence →
ABI analog path
Focal-plane output to Video Processor Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Data Warm electronics

Analog detector outputs leave the focal-plane module for video processing. ABI’s Sensor Unit Electronics perform analog-to-digital conversion before the data reaches its Electronics Unit for formatting and packetization. Analog conditioning, conversion, and packet handling are separate operations.

ABI analog path
Focal-plane output to Video Processor Evidence →
ABI digital data path
SUE conversion; Electronics Unit formatting and packetization Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Heat Beyond the cold stage

The video-processing board sits outside the drawn cold enclosure. ABI’s published radiator and loop-heat-pipe assembly rejects instrument heat to space. The separate warm and cold paths show why the board, cooler, and detector should not be treated as a single temperature.

ABI analog path
Focal-plane output to Video Processor Evidence →
ABI heat rejection
Cryocooler, loop heat pipes, radiator Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Inside this assembly 2 component entries

Sensor Unit Electronics (SUE)

Video Processors plus Peripheral and Thermal Control electronics

The SUE resides in the Sensor Unit. Its circuit cards digitize focal-plane data and control sensor-unit mechanisms and temperatures.

ABI Sensor Unit Electronics (SUE)
Video Processors plus Peripheral and Thermal Control electronics Evidence →

Video Processors: sample collection

Collect and format samples for the EU Data Processor

The VP collects the arrays’ samples and formats them for transmission to the Data Processor in the Electronics Unit.

ABI Video Processors: sample collection
Collect and format samples for the EU Data Processor Evidence →

Cold finger and thermal strap

The optical assembly needs cooling

View in 3D
Light The optical assembly needs cooling

ABI maintains its infrared optical and focal-plane regions at cryogenic temperature. The cold finger and flexible metallic link in the drawing make the connection to refrigeration visible while keeping the optical entrance open.

ABI aft optics
Windows and cold stops in a controlled cryogenic environment Evidence →
ABI heat rejection
Cryocooler, loop heat pipes, radiator Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Data A control loop alongside the data path

ABI’s cryocooler control electronics use temperature feedback and power-amplifier electronics to regulate cooling. Temperature telemetry is engineering information about the instrument, distinct from the detector’s image data.

ABI cooler control
Temperature feedback and power-amplifier drive Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Heat A deliberate path

The cold plate connects the package to the illustrated strap and cold finger. In ABI, the cryocooler transfers focal-plane heat toward loop heat pipes and the radiator. The flexible link here represents a thermal connection without assigning its conductance or load.

ABI heat rejection
Cryocooler, loop heat pipes, radiator Evidence →
Drawing
Representative cutaway / not to scale Evidence →
Inside this assembly 3 component entries

Thermal Dynamic Unit (TDU)

Integral cooler, remote cold head, and transfer line

The TDU is the thermomechanical part of each ABI cooler. Its remote cold head and transfer line are separate named elements, not electronics cards.

ABI Thermal Dynamic Unit (TDU)
Integral cooler, remote cold head, and transfer line Evidence →

Remote cold head

Cold region monitored by the CCE thermometer

The remote cold head belongs to the TDU. A platinum resistance thermometer reports its temperature to the separate Cryocooler Control Electronics.

ABI Remote cold head
Cold region monitored by the CCE thermometer Evidence →

Loop Heat Pipe (LHP) Assembly

Transports Sensor Unit heat to the radiator

The LHP assembly carries excess Sensor Unit energy to its radiator. It is a heat-transport component, not an electrical power cable.

ABI Loop Heat Pipe (LHP) Assembly
Transports Sensor Unit heat to the radiator Evidence →

Detector bias and timing electronics

Establish the detector’s electrical operating conditions

View in 3D
Light Establish the detector’s electrical operating conditions

A focal-plane module needs electrical bias and a readout sequence in addition to incoming light. ABI’s video processors supply the timing and bias that operate its arrays. The separate board strip in this cutaway represents those functions without assigning voltages, clock rates or a particular circuit design.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Clock the array and collect its output

The readout integrated circuit is associated with the detector array. Warm video electronics supply the bias and timing, collect the output and prepare it for later processing. Keeping those electronics separate from the cold ROIC prevents the drawing from collapsing several distinct stages into one board.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Keep warm drive electronics separate from the cold package

The detector’s electrical interfaces cross a thermal boundary. The teaching interconnect connects the cold package to a separately mounted warm board. It shows the need for both electrical continuity and controlled heat flow; its conductor layout and thermal conductance are unspecified.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 2 component entries

Video Processors: bias interface

Provide detector-array operating bias voltages

ABI’s Video Processors provide the bias voltages used to read the focal-plane arrays. Bias supplies establish electrical operating conditions; the readout timing controls when samples are collected.

ABI Video Processors: bias interface
Provide detector-array operating bias voltages Evidence →

Video Processors: readout timing

Generate the timing used to read focal-plane arrays

Readout timing coordinates the collection of detector samples. It belongs to the VP interface and is distinct from the EU’s system-clock card.

ABI Video Processors: readout timing
Generate the timing used to read focal-plane arrays Evidence →

Cold-head thermometer and cooler controller

Measure the cold-head condition

View in 3D
Light Measure the cold-head condition

ABI uses a platinum resistance thermometer at the cooler cold head. The sensor is an electrical temperature measurement device; it is separate from the imaging detector. The cutaway distinguishes this small sensor from the cold finger that transports heat.

ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Adjust the cooler from temperature feedback

The measured cold-head temperature feeds ABI’s Cryocooler Control Electronics. The controller adjusts the power-amplifier duty cycle to regulate temperature. The feedback path runs from thermometer to electronics to cooler drive, alongside the outward instrument-data path.

ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Regulate heat removal through the cooler

The cold finger accepts heat from the detector region, while the cooler’s warm side rejects both the extracted heat and the energy needed to drive refrigeration. Feedback governs the cooler drive; loop heat pipes and the radiator carry away the rejected heat.

ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Remote cold head

Cold region monitored by the CCE thermometer

The remote cold head belongs to the TDU. A platinum resistance thermometer reports its temperature to the separate Cryocooler Control Electronics.

ABI Remote cold head
Cold region monitored by the CCE thermometer Evidence →

Cryocooler Control Electronics (CCE)

Operates the cooler and controls cold-head temperature

The CCE mounts to the spacecraft and operates the TDU in the Sensor Unit. Its own waste heat is rejected through the spacecraft.

ABI Cryocooler Control Electronics (CCE)
Operates the cooler and controls cold-head temperature Evidence →

Platinum resistance thermometer (PRT)

Measures cold-head temperature for feedback

The PRT is the specified ABI cold-head sensor. It should not be labeled a thermistor; GOES-R uses thermistors elsewhere for spacecraft heater control.

ABI Platinum resistance thermometer (PRT)
Measures cold-head temperature for feedback Evidence →

Cryocooler power amplifiers

Duty cycle adjusted to maintain the cold-head set point

The CCE adjusts the amplifier duty cycle using measured cold-head temperature. This is a temperature-control function, not detector signal amplification.

ABI Cryocooler power amplifiers
Duty cycle adjusted to maintain the cold-head set point Evidence →

Journey level

The pixel

An enlarged conceptual hybrid separates absorber, contact, indium connection, readout cell, mounting support and output. Webb and NASA Goddard supply explicitly named public examples; the drawing is not a fabrication stack for ABI, TIRS-2 or a military sensor.

Infrared absorber

Let light interact with material

View in 3D
Light Let light interact with material

Incoming radiation interacts with the detector material. This layer represents that role without assigning a military detector material, thickness, or quantum efficiency.

Drawing
Representative / not to scale Evidence →
Data From radiation to signal

Absorbed light can produce an electrical response in a semiconductor detector. ABI’s published detector role gives a named civil example. The generic schematic assigns no material, conversion gain, signal size, or ABI pixel construction.

ABI detector role
Converts incident photons into an electrical signal Evidence →
Drawing
Representative / not to scale Evidence →
Heat Recognize thermal noise

Thermal noise is part of the measurement problem; NIST lists its reduction among the benefits of cryogenic temperatures. The general principle assigns no material or operating conditions to a real military sensor.

Cryogenic cooling
Can reduce thermal noise Evidence →
Drawing
Representative / not to scale Evidence →

Detector contact pad

Provide the detector-side electrical interface

View in 3D
Light Provide the detector-side electrical interface

The contact pad is the metallized electrical interface on the detector side. It is distinct from the indium joint that bridges to the readout in the illustrated hybrid.

Drawing
Representative / not to scale Evidence →
Data Pass the response to the interconnect

The path proceeds from detector contact to interconnect to readout. The separate output circuitry then carries the readout signal toward the instrument interface.

Drawing
Representative / not to scale Evidence →
Heat Include the pad in the package structure

The enlarged pad belongs to the package structure. Its metal, dimensions and thermal conductance are unspecified; this is a conceptual cross-section.

Drawing
Representative / not to scale Evidence →

Readout circuit cell

Place electronics beneath the response

View in 3D
Light Place electronics beneath the response

The readout cell measures the detector’s electrical response. ABI’s detector-array readout supplies a civil example of the role. The generic layer stack is a conceptual arrangement, not ABI pixel construction.

ABI readout role
Reads detector arrays with video-processing electronics Evidence →
Drawing
Representative / not to scale Evidence →
Data Measure before processing

Measuring a detector response precedes later image processing and communication. ABI’s published array-readout role illustrates this stage. The conceptual cell assigns no ABI construction, timing, digitization precision, or data rate.

ABI readout role
Reads detector arrays with video-processing electronics Evidence →
Drawing
Representative / not to scale Evidence →
Heat Keep instrument temperatures specific

The temperature of a detector assembly is an instrument-specific design choice. The TIRS-2 side level provides a published civil focal-plane value; it does not set a generic pixel temperature.

Drawing
Representative / not to scale Evidence →

Indium interconnect

Join the detector to its readout

View in 3D
Light Join the detector to its readout

Webb is a public example of a hybrid detector joined to silicon readout by indium. This enlarged joint is conceptual.

Indium interconnect
Webb indium interconnects join absorber pixels to the silicon readout circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Carry the local electrical response

The interconnect bridges detector and readout. It is not the separate output route from the readout to warm electronics.

Indium interconnect
Webb indium interconnects join absorber pixels to the silicon readout circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Show the material interface

The joint also sits within a mechanical and thermal assembly. Its dimensions and conductance remain unspecified.

Indium interconnect
Webb indium interconnects join absorber pixels to the silicon readout circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Indium interconnect

Webb indium interconnects join absorber pixels to the silicon readout circuit

Webb provides a named civil example of a hybrid detector connected to its readout by indium. The enlarged joint here is conceptual.

Indium interconnect
Webb indium interconnects join absorber pixels to the silicon readout circuit Evidence →

Detector support and circuit-board interface

Hold the detector and readout assembly

View in 3D
Light Hold the detector and readout assembly

NASA Goddard describes packaging detectors and their readout onto fixtures and circuit boards. The support drawn here is representative.

Detector support and circuit-board interface
NASA detector packaging bonds detector/readout assemblies to fixtures and circuit boards Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Carry the package interfaces

The package connects the detector assembly with surrounding instrument electronics. It is separate from the absorber and each pixel’s local readout.

Detector support and circuit-board interface
NASA detector packaging bonds detector/readout assemblies to fixtures and circuit boards Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Connect the assembly to its mounting environment

The mounting support is part of the thermal path. This drawing specifies no material, interface conductance or operating temperature.

Detector support and circuit-board interface
NASA detector packaging bonds detector/readout assemblies to fixtures and circuit boards Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Detector support and circuit-board interface

NASA detector packaging bonds detector/readout assemblies to fixtures and circuit boards

Packaging connects a detector/readout hybrid to its fixtures and electronics. The pedestal is representative, with no specified material or dimensions.

Detector support and circuit-board interface
NASA detector packaging bonds detector/readout assemblies to fixtures and circuit boards Evidence →

Readout output circuitry

Continue beyond a single pixel

View in 3D
Light Continue beyond a single pixel

The absorber and interconnect feed the readout; its output continues toward the wider instrument. The exposed trace is symbolic.

Readout output circuitry
Webb readout circuitry carries many pixel signals to fewer outputs Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Route pixel measurements outward

Webb’s ROIC architecture connects many pixels to fewer outputs. This example explains the output role without assigning a generic array size or rate.

Readout output circuitry
Webb readout circuitry carries many pixel signals to fewer outputs Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Place the output in the electronics assembly

The output belongs to the readout and package thermal environment. It is not another refrigerator or a separate detector.

Readout output circuitry
Webb readout circuitry carries many pixel signals to fewer outputs Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Readout output circuitry

Webb readout circuitry carries many pixel signals to fewer outputs

The output route continues beyond a single pixel. Its illustrated trace is schematic.

Readout output circuitry
Webb readout circuitry carries many pixel signals to fewer outputs Evidence →

Journey level

The photon

Follow a rising source of infrared radiation, then inspect the molecules that give the spectrum its bands. Historical NASA Earth imagery and an enlarged atmospheric rim provide context. Earth, plume, and molecules use separate drawing scales; no event location, flight, or visibility is calculated.

Hot emitting gas

Start with emitting gas

View in 3D
Light Start with emitting gas

Hot gases can emit infrared radiation. The rising glow and trailing gas introduce emission as the start of a light path. Shape, motion, atmospheric thickness, and false color are drawing choices. No altitude, temperature, radiant intensity, or real vehicle identity is assigned.

Drawing
Representative / not to scale Evidence →
Data Mark an illustrative event

A source event provides context for an observation. The drawing carries no real launch location, event record, or operational timing.

Drawing
Representative / not to scale Evidence →
Heat Connect heat with radiation

Radiation is one way energy leaves a hot emitting region. The plume’s drawn color and glow make that idea visible without acting as a thermometer.

Drawing
Representative / not to scale Evidence →

Molecular emission bands

Keep the molecular bands named

View in 3D
Light Keep the molecular bands named

A civil combustion study identifies emission bands associated with carbon dioxide and water. These approximate band locations explain molecular spectroscopy; they do not define a military sensor’s passbands.

CO2 molecular emission band
Near 4.3 μm Evidence →
H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative / not to scale Evidence →
Data Keep wavelength with its label

A wavelength label belongs to the stated molecular emission band. Keep that source identity with the value when following the light into the detector explanation.

CO2 molecular emission band
Near 4.3 μm Evidence →
H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative / not to scale Evidence →
Heat Separate molecular identity from brightness

A molecular band location and the amount of radiation in that band are different quantities. The cited rows locate the bands; no band intensity is assigned here.

CO2 molecular emission band
Near 4.3 μm Evidence →
H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative / not to scale Evidence →

Radiation paths

Read the light paths as symbols

View in 3D
Light Read the light paths as symbols

The drawn rays connect the emitting region to the rest of the explanation. Their count, direction, brightness, and spacing are visual choices, not simulated photons or a sensor measurement.

Drawing
Representative / not to scale Evidence →
Data Treat animation time as a teaching aid

Any animated progression is chosen for explanation. It is not a measured event duration or the time a warning system takes to produce an output.

Drawing
Representative / not to scale Evidence →
Heat Leave the thermal history unspecified

The changing shape of an illustrative plume does not establish a temperature history, fuel, engine cycle, or real flight event.

Drawing
Representative / not to scale Evidence →

Carbon dioxide molecules

Identify an emitting molecule

View in 3D
Light Identify an emitting molecule

Carbon dioxide supplies one of the molecular-emission examples in the cited civil study. The molecular marker locates that identity within the schematic plume; it does not assign abundance or brightness.

CO2 molecular emission band
Near 4.3 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Keep molecule and wavelength together

The species label and cited band reference remain paired in the named civil combustion example. They do not identify the channels of an operational warning instrument.

CO2 molecular emission band
Near 4.3 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Distinguish a band location from its strength

A molecular band identifies a wavelength region, not a gas temperature or radiant intensity. The colored emission marker is an explanatory choice.

CO2 molecular emission band
Near 4.3 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →

Water-vapor molecules

Identify an emitting molecule

View in 3D
Light Identify an emitting molecule

Water vapor supplies one of the molecular-emission examples in the cited civil study. The molecular marker locates that identity within the schematic plume; it does not assign abundance or brightness.

H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Keep molecule and wavelength together

The species label and cited band reference remain paired in the named civil combustion example. They do not identify the channels of an operational warning instrument.

H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Distinguish a band location from its strength

A molecular band identifies a wavelength region, not a gas temperature or radiant intensity. The colored emission marker is an explanatory choice.

H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →

Civil / context level

Ground segment

Trace a representative ground path from antenna and receiver to processing, archive and spacecraft operations, with separate electrical support. Civil NASA ground-system examples provide the detail; public FORGE statements establish only its high-level roles.

Ground-station antenna

Separate communication from observation

View in 3D
Light Separate communication from observation

The ground interface receives information from the space segment. A drawn beam here symbolizes communication; it is not the telescope’s optical view.

Drawing
Representative / not to scale Evidence →
Data Connect space and ground

The receive marker represents the interface between spacecraft information and ground equipment. The path sets no real network route, communications rate, or latency.

Drawing
Representative / not to scale Evidence →
Heat Power the receiving equipment

Receiving equipment needs electrical power and produces heat during operation. The drawn energy paths are representative and carry no facility power budget.

Drawing
Representative / not to scale Evidence →

Mission-data processing equipment

Show information on a display

View in 3D
Light Show information on a display

A display makes information available to its user. The screen imagery and equipment arrangement are illustrative and do not reproduce an operational console.

Drawing
Representative / not to scale Evidence →
Data Identify the public processing role

GAO’s public description of the planned FORGE system includes processing the mission data collected by satellites. This card names that role without describing software internals or operational algorithms.

FORGE role
Spacecraft operations and mission-data processing Evidence →
Drawing
Representative / not to scale Evidence →
Heat Remember the electronics heat

Electronic processing equipment belongs in a thermal design. The illustration indicates the role of heat removal without depicting an actual equipment room or cooling installation.

Drawing
Representative / not to scale Evidence →
Inside this assembly 1 component entries

Science-processing servers

Science pipelines transform uncorrected, uncalibrated data into usable products

Civil science pipelines turn raw observations into usable products. This provides a public comparison for processing infrastructure without describing warning algorithms.

Science-processing servers
Science pipelines transform uncorrected, uncalibrated data into usable products Evidence →

Spacecraft-operations workstations

Give the interface a place

View in 3D
Light Give the interface a place

The operations area provides a visual setting for the ground role. Its room layout, equipment, and staffing are drawing choices.

Drawing
Representative / not to scale Evidence →
Data Keep spacecraft operations distinct

GAO’s public description of the planned FORGE system gives it a spacecraft-operations role. Operating a spacecraft and processing its observations are distinct responsibilities within the high-level architecture.

FORGE role
Spacecraft operations and mission-data processing Evidence →
Drawing
Representative / not to scale Evidence →
Heat Keep room conditions unspecified

The room and equipment arrangement provide context. Their appearance supplies no operating temperatures, cooling capacities, or actual site configuration.

Drawing
Representative / not to scale Evidence →

Receiver and demodulation equipment

Receive the communication signal

View in 3D
Light Receive the communication signal

This is radio reception after the spacecraft has made an observation. It is separate from infrared detection at the payload.

Receiver and demodulation equipment
RF front ends and receiver processing connect radio waveforms with data packets Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Recover the data carried by the signal

RF front ends and receiver processing turn received waveforms into data for the ground system. The illustration assigns no actual network route or receiver configuration.

Receiver and demodulation equipment
RF front ends and receiver processing connect radio waveforms with data packets Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Support the receiver electronics

The drawn equipment rack represents electrical hardware with a power and cooling interface. Its construction and thermal capacity are illustrative.

Receiver and demodulation equipment
RF front ends and receiver processing connect radio waveforms with data packets Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Receiver and demodulation equipment

RF front ends and receiver processing connect radio waveforms with data packets

The antenna collects the radio signal. Receiver electronics and signal-processing software recover the transmitted data; the layout is schematic.

Receiver and demodulation equipment
RF front ends and receiver processing connect radio waveforms with data packets Evidence →

Telemetry and science-data archive

Give recorded observations a storage destination

View in 3D
Light Give recorded observations a storage destination

The cabinet marks a storage role rather than another sensor. It is a representative physical display of a function that may be distributed.

Telemetry and science-data archive
Ground systems preserve telemetry and science records for later analysis Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Preserve records for later interpretation

An archive stores mission telemetry and science records for retrieval and analysis. It is distinct from the receiver and the processing stage.

Telemetry and science-data archive
Ground systems preserve telemetry and science records for later analysis Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Include storage in facility support

Storage equipment depends on electrical and environmental support. The model makes no claim about capacity, cooling method or availability.

Telemetry and science-data archive
Ground systems preserve telemetry and science records for later analysis Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Telemetry and science-data archive

Ground systems preserve telemetry and science records for later analysis

Mission records and science products need storage and retrieval. The illustrated server cabinet does not assign a storage technology or capacity.

Telemetry and science-data archive
Ground systems preserve telemetry and science records for later analysis Evidence →

Uninterruptible power supply

Support the ground equipment

View in 3D
Light Support the ground equipment

The supply cabinet illustrates supporting infrastructure beneath the visible antenna, workstations and data racks. It is not a spacecraft component.

Uninterruptible power supply
Stored energy can provide backup electrical power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Maintain electrical continuity

A UPS provides a backup-power function. The schematic does not describe a real facility’s redundancy or operating procedure.

Uninterruptible power supply
Stored energy can provide backup electrical power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Keep the facility energy budget explicit

Backup power and heat removal are different responsibilities. The drawn cabinet has no specified energy storage, load rating or runtime.

Uninterruptible power supply
Stored energy can provide backup electrical power Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Uninterruptible power supply

Stored energy can provide backup electrical power

A UPS supports electrical continuity. The drawn cabinet is a general infrastructure example, not a documented installation at an OPIR facility.

Uninterruptible power supply
Stored energy can provide backup electrical power Evidence →

Civil / context level

Civil twin: ABI

Explore ABI as separate optical, scanning, calibration, detector, readout, controller, power and thermal assemblies. Each stop retains its named civil evidence; dimensions and placement remain representative.

ABI telescope and optical bench

Follow ABI’s reflective telescope

View in 3D
Light Follow ABI’s reflective telescope

The GOES-R Data Book describes a four-mirror telescope forming images on three focal-plane modules. The mirror count applies to the telescope, not every mirror in ABI. Shapes, spacing, and ray paths in the drawing remain representative.

ABI telescope
Four mirrors; three focal-plane modules Evidence →
ABI telescope role
Forms a scene image on focal-plane detectors Evidence →
Drawing
Representative / not to scale Evidence →
Data Form the image that the detectors measure

The telescope forms a scene image on the focal-plane modules. Its mirrors and optical bench establish the optical path upstream of detection; the scan drives, clock generation and packet formatting have their own assembly stops.

ABI telescope
Four mirrors; three focal-plane modules Evidence →
ABI telescope role
Forms a scene image on focal-plane detectors Evidence →
Drawing
Representative / not to scale Evidence →
Heat Keep ABI’s thermal regions distinct

The Data Book distinguishes the visible/near-infrared optics and focal-plane region, including a stated GOES-R focal-plane exception. The full qualifier stays with the published temperature row.

ABI VNIR optics and focal plane
Approximately 170 K; GOES-R FPM 180 K Evidence →
Drawing
Representative / not to scale Evidence →
Inside this assembly 7 component entries

Optical Bench

Supports the sensor subsystems and carries loads to the spacecraft

The Optical Bench carries the optical, calibration, electronics, and cooling assemblies while transferring instrument loads to the spacecraft.

ABI Optical Bench
Supports the sensor subsystems and carries loads to the spacecraft Evidence →

Telescope Assembly

Four telescope mirrors form images on three focal-plane modules

ABI’s Telescope Assembly forms the scene image and includes the VIS/IR beamsplitter and fold mirror. The two scan mirrors are upstream components, not part of the four-mirror telescope count.

ABI Telescope Assembly
Four telescope mirrors form images on three focal-plane modules Evidence →

Optical Port Cover (OPC)

One-time deployable protective cover

The OPC protects ABI before deployment. It is a launch-protection cover, not a repeatedly operated imaging shutter.

ABI Optical Port Cover (OPC)
One-time deployable protective cover Evidence →

Shape-memory-alloy pin-puller launch lock

Nonexplosive release for the optical-port cover

The cover is secured by a nonexplosive pin-puller launch lock. Releasing that lock allows the spring-loaded cover hinges to open.

ABI Shape-memory-alloy pin-puller launch lock
Nonexplosive release for the optical-port cover Evidence →

Spring-loaded cover hinges and stop

Open the released cover and capture it at a stop

The hinges open the released OPC, and a mechanical stop captures it. The source describes a Velcro strip at the stop; the teaching model need not reproduce that fastening detail.

ABI Spring-loaded cover hinges and stop
Open the released cover and capture it at a stop Evidence →

Telescope focus motor

Moves one telescope mirror for focus adjustment

One telescope mirror is motor-adjustable for focus. The P&TC motor driver can be switched between the focus motor and the Solar Calibration Cover.

ABI Telescope focus motor
Moves one telescope mirror for focus adjustment Evidence →

Solar Calibration Cover (SCC)

Motor-driven calibration cover with a launch lock

The SUE controls release of the SCC launch lock, and its P&TC electronics drive the SCC motor. This cover is distinct from the one-time Optical Port Cover.

ABI Solar Calibration Cover (SCC)
Motor-driven calibration cover with a launch lock Evidence →

ABI beamsplitters and spectral filters

Separate the spectral channels

View in 3D
Light Separate the spectral channels

ABI observes Earth using visible and infrared channels. Its published channel count belongs to ABI, and the display’s band colors are illustrative.

ABI spectral channels
16 Evidence →
Drawing
Representative / not to scale Evidence →
Data Separate spectral paths before detection

The aft optics use beamsplitters to divide broad spectral regions. Filters above the detector arrays select individual channels, preserving channel identity before the readout collects electrical samples.

ABI VIS/IR beamsplitter (BS1)
Separates VNIR from infrared radiation Evidence →
ABI MW/LW beamsplitter (BS2)
Separates the MWIR and LWIR paths Evidence →
ABI Channel filters
Bandpass filters select individual spectral channels Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Identify the infrared cold region

The Data Book gives an approximate temperature for ABI’s MWIR/LWIR optics and focal planes. It is a named civil-instrument design value, not a default for an infrared band.

ABI MWIR/LWIR optics and focal planes
Approximately 60 K Evidence →
Drawing
Representative / not to scale Evidence →
Inside this assembly 5 component entries

VIS/IR beamsplitter (BS1)

Separates VNIR from infrared radiation

BS1 sends the infrared and VNIR portions into different optical paths. The fold mirror directs the transmitted VNIR path toward its module.

ABI VIS/IR beamsplitter (BS1)
Separates VNIR from infrared radiation Evidence →

Fold mirror

Redirects the VNIR path toward its focal-plane module

The fold mirror turns the VNIR path after the first beamsplitter. It is named separately from the four image-forming telescope mirrors.

ABI Fold mirror
Redirects the VNIR path toward its focal-plane module Evidence →

MW/LW beamsplitter (BS2)

Separates the MWIR and LWIR paths

The second beamsplitter divides the infrared path into MWIR and LWIR portions before the channel-filtered focal-plane modules.

ABI MW/LW beamsplitter (BS2)
Separates the MWIR and LWIR paths Evidence →

Channel filters

Bandpass filters select individual spectral channels

The beamsplitters divide broad spectral regions; filters above the detector arrays select individual ABI channels. These functions should not be conflated.

ABI Channel filters
Bandpass filters select individual spectral channels Evidence →

Windows and cold stops

Named elements within the controlled cryogenic aft optics

ABI’s aft optics contains windows and cold stops and maintains the focal-plane modules in a controlled cryogenic environment. The drawing’s stop sizes and enclosure shapes remain representative.

ABI Windows and cold stops
Named elements within the controlled cryogenic aft optics Evidence →

ABI focal-plane modules

Identify ABI’s infrared detector material

View in 3D
Light Identify ABI’s infrared detector material

The Data Book identifies the material used for ABI’s infrared channels. That civil-instrument specification stays with ABI; it does not identify any military detector material.

ABI infrared channels
HgCdTe Evidence →
Drawing
Representative / not to scale Evidence →
Data Read each spectral channel through its ROIC

An ABI focal-plane module contains filtered spectral channels; each focal-plane array combines a detector array with a readout integrated circuit. The module converts the image to analog electrical signals for the video processors. The published mesoscale cadence describes acquisition of image areas, not the time to read a single detector element.

ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
ABI detector output
Filtered scene image becomes analog electrical signals Evidence →
ABI mesoscale cadence
30-60 s Evidence →
Drawing
Representative / not to scale Evidence →
Heat Maintain the detector modules within their thermal regions

The focal-plane modules sit in the instrument’s separately described visible/near-infrared and infrared thermal regions. The complete GOES-R qualifier accompanies the published temperature rows. Cooling links connect the detector assembly with separately identified refrigeration and heat-rejection hardware.

ABI VNIR optics and focal plane
Approximately 170 K; GOES-R FPM 180 K Evidence →
Drawing
Representative / not to scale Evidence →
ABI MWIR/LWIR optics and focal planes
Approximately 60 K Evidence →
Inside this assembly 3 component entries

Focal Plane Modules (FPMs)

Filter the image and produce analog signals

ABI has VNIR, MWIR, and LWIR modules. A module groups filtered channel assemblies and converts the image to analog signals for the video electronics.

ABI Focal Plane Modules (FPMs)
Filter the image and produce analog signals Evidence →

Focal Plane Array (FPA)

One channel’s detector array plus its ROIC

An ABI FPA combines a detector array and its associated Read-Out Integrated Circuit for one spectral channel. The larger FPM can contain several such channel assemblies.

ABI Focal Plane Array (FPA)
One channel’s detector array plus its ROIC Evidence →

Read-Out Integrated Circuit (ROIC)

Electrical readout associated with each detector array

The ROIC is part of the focal-plane array. The separately mounted Video Processors are the next interface and must not be drawn or described as the same device.

ABI Read-Out Integrated Circuit (ROIC)
Electrical readout associated with each detector array Evidence →

ABI scan mirrors and drives

Redirect the scene into the telescope

View in 3D
Light Redirect the scene into the telescope

The north–south and east–west scan mirrors are separate moving optics upstream of the telescope. Their drawn supports distinguish mirror surfaces, bearings, motors and position feedback.

ABI NS and EW Scan Mirror Assemblies
Orthogonal mirrors steer the line of sight in separate directions Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Measure position while commanding motion

Motor-driver and encoder-processor electronics close the mirror-position path. Their information is separate from the image samples carried by the video electronics.

ABI NS and EW Scan Mirror Assemblies
Orthogonal mirrors steer the line of sight in separate directions Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
ABI full-disk cadence
10 min Evidence →
ABI mainland U.S. cadence
5 min Evidence →
Heat Separate moving optics from thermal shielding

The scan structure supports motion; surrounding shrouds intercept unwanted energy. The cooler and radiator handle other thermal paths, so the moving assembly is not represented as a refrigerator.

ABI NS and EW Scan Mirror Assemblies
Orthogonal mirrors steer the line of sight in separate directions Evidence →
ABI scan controls
Motor-driver circuitry moves mirrors; encoder circuitry reports position Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 6 component entries

NS and EW Scan Mirror Assemblies

Orthogonal mirrors steer the line of sight in separate directions

ABI uses separate north–south and east–west scan mirrors. Each assembly combines its mirror, drive assembly, and support bearing.

ABI NS and EW Scan Mirror Assemblies
Orthogonal mirrors steer the line of sight in separate directions Evidence →

Scan Drive Assembly (SDA)

Bench-mounted motor drives one side of a scan mirror

Each SDA supports one side of its mirror and applies motor motion. The separate support bearing anchors the opposite side.

ABI Scan Drive Assembly (SDA)
Bench-mounted motor drives one side of a scan mirror Evidence →

Optical encoder

Reports scan-mirror position

An optical encoder measures the mirror’s position. Its measurement is distinct from the electrical command sent to the motor.

ABI Optical encoder
Reports scan-mirror position Evidence →

Support Bearing Assembly

Supports the opposite side of the scan mirror

The support bearing mounts to the Optical Bench and supports the mirror opposite the Scan Drive Assembly.

ABI Support Bearing Assembly
Supports the opposite side of the scan mirror Evidence →

Scanner Interface & Motor Driver (SIMD)

EU circuit card controls scan-mirror motion

The SIMD card belongs to ABI’s Electronics Unit and drives the Scan Drive Assembly motors. It is separate from the optical encoders and their processor cards.

ABI Scanner Interface & Motor Driver (SIMD)
EU circuit card controls scan-mirror motion Evidence →

EW and NS Encoder Processors

Power optical encoders and compute scan-mirror position

The Encoder Processor cards sit inside the Electronics Unit chassis. They power the optical encoders on the scan mechanism and calculate mirror position. The motor-driver card supplies motion; the encoder-processing path reports position.

ABI EW and NS Encoder Processors
Power optical encoders and compute scan-mirror position Evidence →

ABI calibration targets

Observe infrared and solar references

View in 3D
Light Observe infrared and solar references

ABI has an internal infrared target and a solar calibration target. A space view is another reference direction, not a third installed target.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →
ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →
ABI Space-look reference
Background observations support all ABI channels Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Identify reference samples

The selected target, mirror position and instrument state establish the context of a reference observation. The diagram keeps reference observations separate from Earth-view observations.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →
ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →
ABI Space-look reference
Background observations support all ABI channels Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Distinguish the thermal target from the diffuser

The infrared reference has a thermal role; the solar target redirects incident sunlight. The two target types should not be treated as interchangeable blackbodies.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →
ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →
ABI Space-look reference
Background observations support all ABI channels Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Internal Calibration Target (ICT)

Full-aperture blackbody reference for the infrared channels

ABI’s MWIR and LWIR channels observe the ICT as a blackbody thermal reference. Its measured temperature determines the reference radiance used for calibration.

ABI Internal Calibration Target (ICT)
Full-aperture blackbody reference for the infrared channels Evidence →

Solar Calibration Target (SCT)

Diffuse white target reflects sunlight into the optical system

The SCT supplies a sunlight reference for ABI’s VNIR channels. It is part of the Solar Calibration Assembly within the OPSA and is separate from the infrared blackbody target.

ABI Solar Calibration Target (SCT)
Diffuse white target reflects sunlight into the optical system Evidence →

Space-look reference

Background observations support all ABI channels

ABI also observes space to measure its background signal. A space look is a viewing direction, not an additional onboard calibration object.

ABI Space-look reference
Background observations support all ABI channels Evidence →

ABI Sensor Unit Electronics

Connect the detectors to warm electronics

View in 3D
Light Connect the detectors to warm electronics

The focal-plane module converts the optical image to an electrical signal. Sensor Unit Electronics then operate and read the detector interface.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Supply bias and timing, then collect samples

ABI video processors provide detector timing and bias and collect the outputs. Sensor Unit Electronics digitize the focal-plane data before the Electronics Unit prepares transmission packets.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Keep the cold package and warm cards distinct

The detector-side readout and warm electronics occupy different thermal roles. Their connection carries electrical signals across the boundary; no interface conductance or wiring design is inferred.

ABI video processors
Supply readout timing and bias; collect and format detector samples Evidence →
ABI digitization
Sensor Unit Electronics digitizes focal-plane data Evidence →
ABI focal-plane array
Detector array plus its readout integrated circuit Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 4 component entries

Sensor Unit Electronics (SUE)

Video Processors plus Peripheral and Thermal Control electronics

The SUE resides in the Sensor Unit. Its circuit cards digitize focal-plane data and control sensor-unit mechanisms and temperatures.

ABI Sensor Unit Electronics (SUE)
Video Processors plus Peripheral and Thermal Control electronics Evidence →

Video Processors: bias interface

Provide detector-array operating bias voltages

ABI’s Video Processors provide the bias voltages used to read the focal-plane arrays. Bias supplies establish electrical operating conditions; the readout timing controls when samples are collected.

ABI Video Processors: bias interface
Provide detector-array operating bias voltages Evidence →

Video Processors: readout timing

Generate the timing used to read focal-plane arrays

Readout timing coordinates the collection of detector samples. It belongs to the VP interface and is distinct from the EU’s system-clock card.

ABI Video Processors: readout timing
Generate the timing used to read focal-plane arrays Evidence →

Video Processors: sample collection

Collect and format samples for the EU Data Processor

The VP collects the arrays’ samples and formats them for transmission to the Data Processor in the Electronics Unit.

ABI Video Processors: sample collection
Collect and format samples for the EU Data Processor Evidence →

ABI controller and data-interface cards

Coordinate an observation

View in 3D
Light Coordinate an observation

The Instrument Controller operates ABI. Its cards are physically distinct from the telescope and the detector that first receive the scene.

ABI instrument controller
A single-board computer operates the instrument Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Format samples and hand them to the spacecraft

The Data Processor formats and packetizes measurements. High Speed I/O supplies the SpaceWire interface, while Telemetry and Timing generates system clocks and supports instrument telemetry.

ABI instrument controller
A single-board computer operates the instrument Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Carry electronics heat through the mounting interface

The warm Electronics Unit has a spacecraft-panel thermal interface. This path is separate from refrigeration at the focal plane.

ABI instrument controller
A single-board computer operates the instrument Evidence →
ABI timing
Telemetry and Timing card generates system clocks and handles telemetry Evidence →
ABI digital data path
Data Processor formats and packetizes; HSIO interfaces with SpaceWire Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 7 component entries

Electronics Unit (EU)

Main spacecraft interface with power, control, data, and scan electronics

The EU houses the instrument’s principal power and processing interfaces in a chassis with a parent board and circuit-card assemblies.

ABI Electronics Unit (EU)
Main spacecraft interface with power, control, data, and scan electronics Evidence →

Instrument Controller (IC)

Single-board computer operates ABI

The IC runs instrument operations. It is a named EU card, distinct from the spacecraft’s On Board Computer.

ABI Instrument Controller (IC)
Single-board computer operates ABI Evidence →

Peripheral and Thermal Control (P&TC)

Controls sensor-unit thermal hardware and mechanisms except the scanner

The P&TC card is part of the Sensor Unit Electronics. It handles calibration-target temperature, VNIR-module temperature, heat-pipe and outgas heaters, covers, and telescope focus. Scanner motion has separate drive cards inside the Electronics Unit.

ABI Peripheral and Thermal Control (P&TC)
Controls sensor-unit thermal hardware and mechanisms except the scanner Evidence →

P&TC command and telemetry interface

Serial control link to the EU Telemetry and Timing card

The P&TC receives control information over a serial interface from the Telemetry and Timing card in the EU.

ABI P&TC command and telemetry interface
Serial control link to the EU Telemetry and Timing card Evidence →

Data Processor

Formats and packetizes detector data

The EU Data Processor receives data from the Video Processor and forms packets. Packet formation is separate from earlier digitization in the Sensor Unit.

ABI Data Processor
Formats and packetizes detector data Evidence →

High Speed I/O (HSIO)

SpaceWire communications interface to the spacecraft

The HSIO card is ABI’s EU communications interface to the spacecraft. It communicates through SpaceWire, downstream of the Data Processor’s formatting and packetization.

ABI High Speed I/O (HSIO)
SpaceWire communications interface to the spacecraft Evidence →

Telemetry and Timing (TNT)

Generates system clocks and handles ABI telemetry

The TNT card supplies system timing and handles telemetry. Detector readout timing and peripheral control are coordinated through their respective interfaces.

ABI Telemetry and Timing (TNT)
Generates system clocks and handles ABI telemetry Evidence →

ABI cryocooler and heat transport

Keep the infrared assembly in its thermal environment

View in 3D
Light Keep the infrared assembly in its thermal environment

The cooler serves the cold focal-plane region. Shields and shrouds limit unwanted radiation before that energy becomes another load to remove.

ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
ABI scan-shroud heat path
Shields collect solar heat; constant-conductance heat pipes carry it away Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Use temperature feedback to control refrigeration

A cold-head thermometer supplies feedback to Cryocooler Control Electronics. Cooler control is a separate circuit from the instrument image-data interface.

ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
ABI scan-shroud heat path
Shields collect solar heat; constant-conductance heat pipes carry it away Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Trace heat from cold hardware to space

The cooler removes heat from the cold assembly. Warm-side rejection and heat-transport hardware carry energy toward the radiator. The geometry illustrates a path without assigning cooler performance.

ABI cooler heat path
Focal planes → cooler → loop heat pipes → radiator Evidence →
ABI cryocooler feedback
Cold-head thermometer feeds power-amplifier duty-cycle control Evidence →
ABI scan-shroud heat path
Shields collect solar heat; constant-conductance heat pipes carry it away Evidence →
Drawing
Representative arrangement / not to scale Evidence →
ABI cryocooler design
Two redundant two-stage pulse-tube coolers Evidence →
ABI radiator role
Rejects excess instrument thermal energy to space Evidence →
Inside this assembly 12 component entries

Two-stage pulse-tube cryocooler

Pumps focal-plane heat toward the radiator/heat-pipe assembly

ABI’s published cooler is a two-stage pulse-tube design. Its heat-rejection path ends at the radiator through the loop heat pipes.

ABI Two-stage pulse-tube cryocooler
Pumps focal-plane heat toward the radiator/heat-pipe assembly Evidence →

Thermal Dynamic Unit (TDU)

Integral cooler, remote cold head, and transfer line

The TDU is the thermomechanical part of each ABI cooler. Its remote cold head and transfer line are separate named elements, not electronics cards.

ABI Thermal Dynamic Unit (TDU)
Integral cooler, remote cold head, and transfer line Evidence →

Remote cold head

Cold region monitored by the CCE thermometer

The remote cold head belongs to the TDU. A platinum resistance thermometer reports its temperature to the separate Cryocooler Control Electronics.

ABI Remote cold head
Cold region monitored by the CCE thermometer Evidence →

Cryocooler Control Electronics (CCE)

Operates the cooler and controls cold-head temperature

The CCE mounts to the spacecraft and operates the TDU in the Sensor Unit. Its own waste heat is rejected through the spacecraft.

ABI Cryocooler Control Electronics (CCE)
Operates the cooler and controls cold-head temperature Evidence →

Platinum resistance thermometer (PRT)

Measures cold-head temperature for feedback

The PRT is the specified ABI cold-head sensor. It should not be labeled a thermistor; GOES-R uses thermistors elsewhere for spacecraft heater control.

ABI Platinum resistance thermometer (PRT)
Measures cold-head temperature for feedback Evidence →

Cryocooler power amplifiers

Duty cycle adjusted to maintain the cold-head set point

The CCE adjusts the amplifier duty cycle using measured cold-head temperature. This is a temperature-control function, not detector signal amplification.

ABI Cryocooler power amplifiers
Duty cycle adjusted to maintain the cold-head set point Evidence →

Redundant cryocooler units

Can operate individually or together

ABI’s published design has redundant cooler units, each comprising a TDU and CCE. The representative diagram may show one functional path without claiming the hardware count is reproduced.

ABI Redundant cryocooler units
Can operate individually or together Evidence →

Scan Shroud Assembly

Shields collect solar heat in the scan cavity

The scan shrouds intercept solar energy entering the optical port and route the absorbed heat toward the radiator. They are distinct from the cold-stop region around the focal planes.

ABI Scan Shroud Assembly
Shields collect solar heat in the scan cavity Evidence →

Constant-conductance heat pipes

Carry scan-shroud heat to the radiator/LHP assembly

Constant-conductance heat pipes connect the scan shrouds to the rejection assembly. The book separately names loop heat pipes as the instrument-to-radiator interface.

ABI Constant-conductance heat pipes
Carry scan-shroud heat to the radiator/LHP assembly Evidence →

Loop Heat Pipe (LHP) Assembly

Transports Sensor Unit heat to the radiator

The LHP assembly carries excess Sensor Unit energy to its radiator. It is a heat-transport component, not an electrical power cable.

ABI Loop Heat Pipe (LHP) Assembly
Transports Sensor Unit heat to the radiator Evidence →

Thermal Control Radiator

Releases Sensor Unit thermal energy to space

The radiator is the final radiative rejection surface for the instrument thermal path.

ABI Thermal Control Radiator
Releases Sensor Unit thermal energy to space Evidence →

Survival, operational, and outgas heaters

Protect, control, or warm the Sensor Unit for distinct purposes

Survival heaters protect an unpowered instrument; operational heaters regulate temperatures; outgas heaters warm optical hardware before cryogenic operation. Those are different heater functions.

ABI Survival, operational, and outgas heaters
Protect, control, or warm the Sensor Unit for distinct purposes Evidence →

ABI instrument power supply

Provide energy to the instrument assemblies

View in 3D
Light Provide energy to the instrument assemblies

The EU Power Supply converts spacecraft input into instrument electrical supplies. It supports the electronics responsible for observing, reading and controlling the instrument.

ABI electronics power
Power supply converts spacecraft input to instrument rails Evidence →
ABI EU parent board and redundant card sets
Parent board and CCAs provide separate Side 1/Side 2 electronics Evidence →
ABI SUE redundant electronics
Separate Side 1/Side 2 electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Keep power conversion separate from command routing

The supply card and parent board support the instrument electronics, but do not replace the controller or data interface. Published redundant card sets remain specific to ABI.

ABI electronics power
Power supply converts spacecraft input to instrument rails Evidence →
ABI EU parent board and redundant card sets
Parent board and CCAs provide separate Side 1/Side 2 electronics Evidence →
ABI SUE redundant electronics
Separate Side 1/Side 2 electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Account for the warm electrical path

Power conversion and the operating cards contribute to the instrument thermal load. Their warm mounting interface remains distinct from the cooled detector region.

ABI electronics power
Power supply converts spacecraft input to instrument rails Evidence →
ABI EU parent board and redundant card sets
Parent board and CCAs provide separate Side 1/Side 2 electronics Evidence →
ABI SUE redundant electronics
Separate Side 1/Side 2 electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

EU Power Supply

Converts spacecraft input into ABI electronics supply voltages

The EU Power Supply converts the spacecraft input into the electrical supplies required by ABI electronics. It supplies power rather than interpreting commands or detector samples.

ABI EU Power Supply
Converts spacecraft input into ABI electronics supply voltages Evidence →

EU parent board and redundant card sets

Parent board and CCAs provide separate Side 1/Side 2 electronics

The published EU includes a parent board and redundant circuit-card sets. Connector positions and traces in the model are illustrative.

ABI EU parent board and redundant card sets
Parent board and CCAs provide separate Side 1/Side 2 electronics Evidence →

SUE redundant electronics

Separate Side 1/Side 2 electronics

ABI’s SUE is described as Side 1/Side 2 redundant. Redundancy is a system property; the representative cutaway need not reproduce the complete duplicated wiring.

ABI SUE redundant electronics
Separate Side 1/Side 2 electronics Evidence →

Civil / context level

Civil twin: TIRS-2

Explore TIRS-2’s telescope, scene selection, blackbody, fixed filters, detector package, focal-plane electronics, main electronics, cooler and heat rejection. Ground-established alignment shims are distinct from moving mechanisms.

TIRS-2 refractive telescope

Follow the refractive telescope

View in 3D
Light Follow the refractive telescope

NASA describes TIRS-2’s refractive telescope and field of view. The drawing preserves the published element count while identifying lens shapes, distances, and ray paths as representative.

TIRS-2 refractive telescope
Four elements; f/1.64 Evidence →
TIRS-2 field of view
15 degrees Evidence →
Drawing
Representative / not to scale Evidence →
Data Civil Earth observation

NASA publishes TIRS-2’s swath and ground sampling. Those values describe this civil instrument and do not establish a generic telescope’s imaging performance.

TIRS-2 swath
185 km Evidence →
TIRS-2 ground sampling
100 m Evidence →
Drawing
Representative / not to scale Evidence →
Heat Identify the telescope temperature

NASA describes a controlled telescope temperature for TIRS-2. It is a separate published design value from the colder focal plane.

TIRS-2 telescope design temperature
185 K Evidence →
Drawing
Representative / not to scale Evidence →
Inside this assembly 1 component entries

Lens baffles and spacers

Control unwanted light around the lenses

The TIRS-2 design includes lens-region baffles and spacers. Its refractive optical train is distinct from ABI’s reflective telescope; the fixed interference filters are a separately selectable assembly.

TIRS-2 internal baffles
Lens-region baffles and spacers control the optical path Evidence →

TIRS-2 detector arrays

Name the TIRS-2 detector assemblies

View in 3D
Light Name the TIRS-2 detector assemblies

The published TIRS-2 description identifies its QWIP arrays and physical format. The drawing shows representative detector packages and blank detector faces; the published physical format remains in the evidence row.

TIRS-2 detector assemblies
Three QWIP arrays; 640 × 512 physical pixels each Evidence →
Drawing
Representative / not to scale Evidence →
Data Separate the physical array from the science row

The detector study describes an effective science row for each channel, formed by combining physical rows and accounting for overlap between arrays. That per-channel row is separate from the physical array dimensions.

TIRS-2 effective science row
1,850 cross-track pixels Evidence →
TIRS-2 detector assemblies
Three QWIP arrays; 640 × 512 physical pixels each Evidence →
Drawing
Representative / not to scale Evidence →
Heat Hold the focal plane at its design temperature

NASA describes a mechanical cryocooler maintaining the TIRS-2 focal plane at its required operating temperature. This specification belongs to the named civil instrument.

TIRS-2 focal-plane design temperature
43 K Evidence →
Drawing
Representative / not to scale Evidence →
Inside this assembly 1 component entries

Detector alignment shims

Ground focus measurements inform alignment-shim fabrication

TIRS-2 subsystem optical tests supplied focus information for fabrication of alignment shims. These are fixed mechanical adjustments, not an on-orbit focusing actuator.

TIRS-2 detector alignment
Ground focus measurements inform alignment-shim fabrication Evidence →

TIRS-2 cryocooler

Provide refrigeration for the detector assembly

View in 3D
Light Provide refrigeration for the detector assembly

The cryocooler thermomechanical unit provides refrigeration to the detector assembly. It is physically distinct from the fixed filters that select the thermal channels.

TIRS-2 cooler hardware
Thermomechanical unit, cooler-control electronics and redundancy-switch electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Operate the cooler through control and switching electronics

Cryocooler Control Electronics operate the thermomechanical unit through the Redundancy Switch Electronics. These interfaces support the cooler rather than carrying the instrument’s science-image samples.

TIRS-2 cooler hardware
Thermomechanical unit, cooler-control electronics and redundancy-switch electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Move heat from the cold assembly toward rejection

The cooler removes heat from the cold assembly; the external thermal hardware transports and rejects that heat. The cold-stage temperature belongs to the named civil design, while the drawn cooler and heat links remain representative.

TIRS-2 cooler hardware
Thermomechanical unit, cooler-control electronics and redundancy-switch electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
TIRS-2 focal-plane design temperature
43 K Evidence →
Inside this assembly 3 component entries

Cryocooler thermomechanical unit

Provide refrigeration

TIRS-2 separates the cooler’s thermomechanical hardware from its control and switching electronics. This description admits no new performance or operating-temperature values from the design presentation.

TIRS-2 cooler hardware
Thermomechanical unit, cooler-control electronics and redundancy-switch electronics Evidence →

Cryocooler Control Electronics

Drive and control the cooler

The NASA block diagram includes paired cooler-control electronics connected to the thermomechanical unit through switching hardware.

TIRS-2 cooler hardware
Thermomechanical unit, cooler-control electronics and redundancy-switch electronics Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →

Redundancy Switch Electronics

Select the cooler-control connection

The RSE connects the redundant cooler electronics to the thermomechanical unit. It is a distinct interface assembly in the TIRS-2 design.

TIRS-2 cooler hardware
Thermomechanical unit, cooler-control electronics and redundancy-switch electronics Evidence →

TIRS-2 scene-select mechanism

Select Earth, blackbody or space

View in 3D
Light Select Earth, blackbody or space

The mirror changes which scene reaches the telescope. The onboard blackbody is hardware; the space reference is a viewing direction.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →
TIRS-2 mechanism hardware
Mirror, motor, bearings, position encoders and motor-control electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Command motion and measure position

The mechanism includes motor, bearings, position encoders and control electronics. Commanded motion and measured position are separate responsibilities.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →
TIRS-2 mechanism hardware
Mirror, motor, bearings, position encoders and motor-control electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Support the mechanism within the instrument

Bearings and mounts support the moving mirror. The drawing specifies neither bearing construction nor motor duty cycle.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →
TIRS-2 mechanism hardware
Mirror, motor, bearings, position encoders and motor-control electronics Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 2 component entries

Scene-select mirror

Choose Earth or a calibration reference

The TIRS-2 scene-select mechanism points toward Earth, its onboard blackbody or a space view. This civil mechanism has a different observing role from ABI’s two-axis scanning assembly.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →

Scene-select motor, bearings and encoders

Move and measure the mirror

NASA’s TIRS-2 design separates the motor, mirror support, encoders and mechanism-control electronics. Motion and measured position are distinct hardware responsibilities.

TIRS-2 mechanism hardware
Mirror, motor, bearings, position encoders and motor-control electronics Evidence →

TIRS-2 onboard blackbody

Provide an onboard thermal reference

View in 3D
Light Provide an onboard thermal reference

The scene-select mirror can direct the telescope toward an internal blackbody reference instead of Earth. The target is distinct from the telescope lenses.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →
TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Associate samples with a reference view

Reference observations need the scene identity to accompany their samples. This illustration identifies the reference route without reproducing calibration algorithms.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →
TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Connect the reference to thermal control

The thermal target belongs to the instrument thermal design. Its drawn shape assigns no emissivity, operating temperature or calibration accuracy.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →
TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Onboard blackbody target

Provide a thermal reference

The blackbody is an internal reference that the scene-select mirror can observe. Space supplies another reference view rather than another installed target.

TIRS-2 scene-select mechanism
Mirror selects Earth, a blackbody target or a space view Evidence →

TIRS-2 focal-plane electronics

Connect the detector package to instrument electronics

View in 3D
Light Connect the detector package to instrument electronics

The Focal Plane Electronics form the detector-side electrical interface. They are distinct from the detector material and from the main electronics chassis.

TIRS-2 focal-plane electronics
FPE connects detector assemblies to the main electronics through an interface board Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Pass measurements through the interface board

The Focal-plane Interface Board connects selected FPE and main-electronics paths. NASA’s civil design uses selected cross-connections rather than every possible redundant connection.

TIRS-2 focal-plane electronics
FPE connects detector assemblies to the main electronics through an interface board Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Keep the readout interfaces physically identifiable

Electrical continuity and thermal mounting are different design responsibilities. The exposed boards clarify the connection without prescribing package or harness details.

TIRS-2 focal-plane electronics
FPE connects detector assemblies to the main electronics through an interface board Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 2 component entries

Focal Plane Electronics

Connect and operate detector readout

NASA’s design diagram separates the detector assemblies from the FPE and main electronics. The FPE forms the instrument’s detector-side electrical interface.

TIRS-2 focal-plane electronics
FPE connects detector assemblies to the main electronics through an interface board Evidence →

Focal-plane Interface Board

Provide selected cross-connections

The TIRS-2 interface board connects the focal-plane electronics to the paired main electronics. The design uses selected cross-strapping rather than making every possible connection redundant.

TIRS-2 focal-plane electronics
FPE connects detector assemblies to the main electronics through an interface board Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →

TIRS-2 Main Electronics Box

House the instrument-control electronics

View in 3D
Light House the instrument-control electronics

The Main Electronics Box contains several functional boards. It operates downstream of the telescope and focal plane rather than acting as another optical stage.

TIRS-2 main electronics
Separate boards for command/data, power, thermal control, mechanism control and high-speed interfaces Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Separate command, mechanism and science-data interfaces

NASA’s block diagram distinguishes command/data handling, power, temperature control, mechanism control and high-speed interfaces. Each has a different responsibility within the electronics box.

TIRS-2 main electronics
Separate boards for command/data, power, thermal control, mechanism control and high-speed interfaces Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Connect thermal control with instrument operation

Temperature-control boards command thermal functions. The controlled heaters and the electronics that drive them are distinct items.

TIRS-2 main electronics
Separate boards for command/data, power, thermal control, mechanism control and high-speed interfaces Evidence →
TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Main Electronics Box

House instrument-control and interface boards

The MEB contains separate functions for command/data handling, power, temperature control, mechanism control and high-speed data interfaces. The NASA diagram distinguishes power, command, telemetry and science-data connections.

TIRS-2 main electronics
Separate boards for command/data, power, thermal control, mechanism control and high-speed interfaces Evidence →

Mechanism-control electronics

Drive the scene-select mechanism

The MCE interfaces with the motor, encoders and deployable hardware in NASA’s block diagram. It is separate from the high-speed science-data interface.

TIRS-2 mechanism hardware
Mirror, motor, bearings, position encoders and motor-control electronics Evidence →
TIRS-2 main electronics
Separate boards for command/data, power, thermal control, mechanism control and high-speed interfaces Evidence →

Redundant electronics interfaces

Provide alternate hardware paths

The 2018 design pairs main-electronics and cooler-control functions and cross-connects selected interfaces. This is an explicitly named civil design example, not an assumed property of the representative payload.

TIRS-2 redundant interfaces
Paired electronics with selected cross-connections and cooler switching Evidence →

TIRS-2 radiators and Earth shield

Separate thermal shielding from the observing path

View in 3D
Light Separate thermal shielding from the observing path

The Earth shield manages the instrument environment. It is not another imaging mirror or an installed calibration target.

TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
TIRS-2 launch restraints
Earth-shield deployment hardware and a cryocooler launch lock Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Distinguish deployment from continuous control

The Earth-shield deployment interface and cryocooler launch lock serve configuration changes. Thermal measurements and heater commands serve continuing operation.

TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
TIRS-2 launch restraints
Earth-shield deployment hardware and a cryocooler launch lock Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Carry and reject heat outside the cold assembly

The published civil design includes radiators, heat pipes, isolation, blankets and heaters. These complement the cryocooler rather than duplicating its refrigeration cycle.

TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
TIRS-2 launch restraints
Earth-shield deployment hardware and a cryocooler launch lock Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 3 component entries

Radiators, heat pipes and Earth shield

Manage external and conducted heat

TIRS-2’s thermal design includes transport, emitting surfaces, shielding, blankets and isolation. These hardware roles are distinct from the active refrigeration cycle.

TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →

Operational and survival heater circuits

Support separate thermal operating states

NASA’s design distinguishes operational temperature control from survival-heater supply. Temperature-control boards and the heaters they drive are separate items in the electrical diagram.

TIRS-2 thermal hardware
Radiators, heat pipes, isolation, Earth shield, operational and survival heaters Evidence →
TIRS-2 main electronics
Separate boards for command/data, power, thermal control, mechanism control and high-speed interfaces Evidence →

Cryocooler launch lock and Earth-shield deployment hardware

Restrain hardware for launch

The TIRS-2 diagram includes launch-restraint and deployment interfaces. These serve structural configuration changes rather than image-data processing.

TIRS-2 launch restraints
Earth-shield deployment hardware and a cryocooler launch lock Evidence →

TIRS-2 interference filters

Select spectral channels above the arrays

View in 3D
Light Select spectral channels above the arrays

Fixed interference filters select TIRS-2’s thermal channels. The filter tiles are separate from the telescope lenses and detector surfaces.

TIRS-2 spectral selection
Interference filters over the arrays select the channels Evidence →
TIRS-2 internal baffles
Lens-region baffles and spacers control the optical path Evidence →
Drawing
Representative arrangement / not to scale Evidence →
TIRS thermal bands
10.6-11.2 μm; 11.5-12.5 μm Evidence →
Data Preserve the channel identity

The filter selects the optical channel before the electronic signal is read. No bit depth, sample rate or additional channel is implied by the drawing.

TIRS-2 spectral selection
Interference filters over the arrays select the channels Evidence →
TIRS-2 internal baffles
Lens-region baffles and spacers control the optical path Evidence →
Drawing
Representative arrangement / not to scale Evidence →
TIRS thermal bands
10.6-11.2 μm; 11.5-12.5 μm Evidence →
Heat Place spectral selection in the detector environment

The filter and detector assembly belong to the instrument’s thermal design. The illustrated mount does not specify its material, coating stack or heat conductance.

TIRS-2 spectral selection
Interference filters over the arrays select the channels Evidence →
TIRS-2 internal baffles
Lens-region baffles and spacers control the optical path Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Inside this assembly 1 component entries

Spectral interference filters

Interference filters over the arrays select the channels

The TIRS-2 paper places interference filters over the detector arrays to select its spectral channels.

TIRS-2 spectral selection
Interference filters over the arrays select the channels Evidence →

Civil / context level

The atmosphere

A schematic air column introduces wavelength-dependent absorption. It is a qualitative molecular-physics view, with no altitude-dependent transmission or sensor-detection model.

Atmospheric gas column

Let wavelength matter

View in 3D
Light Let wavelength matter

Atmospheric gases absorb some wavelengths while transmitting others. The air column illustrates that qualitative idea; layer spacing and colors do not encode a measured transmission profile.

Atmospheric absorption
Gases absorb some wavelengths while transmitting others Evidence →
Drawing
Representative / not to scale Evidence →
Data A useful distinction

Interpreting a spectral observation requires keeping its physical context clear. This drawing supplies a qualitative absorption concept, not corrections for a measured observation.

Atmospheric absorption
Gases absorb some wavelengths while transmitting others Evidence →
Drawing
Representative / not to scale Evidence →
Heat Radiation interacting with gas

Absorption transfers energy from radiation to material. The cited qualitative atmospheric description explains why wavelength belongs in that energy story.

Atmospheric absorption
Gases absorb some wavelengths while transmitting others Evidence →
Drawing
Representative / not to scale Evidence →

Molecular absorption bands

Keep emission and transmission distinct

View in 3D
Light Keep emission and transmission distinct

The cited carbon-dioxide and water values locate emission bands in a civil combustion study. They are not atmospheric transmission percentages or altitude-dependent visibility results.

CO2 molecular emission band
Near 4.3 μm Evidence →
H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative / not to scale Evidence →
Data Carry the band label with the value

Keep the emitting molecule and the approximate wavelength together. Those labels describe the cited examples and do not identify a real warning sensor’s channels.

CO2 molecular emission band
Near 4.3 μm Evidence →
H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative / not to scale Evidence →
Heat Keep color separate from temperature

The band colors distinguish parts of the explanation. They are neither visible colors of the gases nor a calibrated temperature scale.

Drawing
Representative / not to scale Evidence →

Source-to-sensor path

Read the path as a schematic

View in 3D
Light Read the path as a schematic

The path through the column connects the source, intervening atmosphere, and instrument. It sets no atmospheric state, weather profile, or operational line of sight.

Drawing
Representative / not to scale Evidence →
Data Separate illustration from measurement

An animated ray or colored atmospheric layer is an explanatory symbol. A measured spectrum or modeled transmission curve would need its own inputs, method, and evidence.

Drawing
Representative / not to scale Evidence →
Heat Leave the thermal profile unspecified

This column has no assigned temperature, humidity, or altitude profile. Its purpose is to connect molecular absorption with the light path at a qualitative level.

Drawing
Representative / not to scale Evidence →

Atmospheric carbon dioxide

Identify a gas in the optical path

View in 3D
Light Identify a gas in the optical path

Carbon dioxide is identified separately in the schematic gas column. The band row is a molecular-emission reference; it does not supply atmospheric transmission or a visibility calculation.

CO2 molecular emission band
Near 4.3 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Keep molecule and wavelength together

The species label and cited band reference remain paired in the qualitative atmospheric view. They do not identify the channels of an operational warning instrument.

CO2 molecular emission band
Near 4.3 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Distinguish a band location from its strength

A molecular band identifies a wavelength region, not a gas temperature or radiant intensity. The colored gas marker is an explanatory choice.

CO2 molecular emission band
Near 4.3 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →

Atmospheric water vapor

Identify a gas in the optical path

View in 3D
Light Identify a gas in the optical path

Water vapor is identified separately in the schematic gas column. The band row is a molecular-emission reference; it does not supply atmospheric transmission or a visibility calculation.

H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Data Keep molecule and wavelength together

The species label and cited band reference remain paired in the qualitative atmospheric view. They do not identify the channels of an operational warning instrument.

H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →
Heat Distinguish a band location from its strength

A molecular band identifies a wavelength region, not a gas temperature or radiant intensity. The colored gas marker is an explanatory choice.

H2O molecular emission band
Near 2.7 μm Evidence →
Drawing
Representative arrangement / not to scale Evidence →