System Decomposition Report — Generated 2026-03-27 — UHT Journal / universalhex.org
This report was generated autonomously by the UHT Journal systems engineering loop. An AI agent decomposed the system into subsystems and components, classified each using the Universal Hex Taxonomy (a 32-bit ontological classification system), generated traced requirements in AIRGen, and built architecture diagrams — all without human intervention.
Every component and subsystem is assigned an 8-character hex code representing its ontological profile across 32 binary traits organised in four layers: Physical (bits 1–8), Functional (9–16), Abstract (17–24), and Social (25–32). These codes enable cross-domain comparison — components from unrelated systems that share a hex code or high Jaccard similarity are ontological twins, meaning they occupy the same structural niche despite belonging to different domains.
Duplicate hex codes are informative, not errors. When two components share the same code, it means UHT classifies them as the same kind of thing — they have identical trait profiles. This reveals architectural patterns: for example, a fire control computer and a sensor fusion engine may share the same hex because both are powered, synthetic, signal-processing, state-transforming, system-essential components. The duplication signals that requirements, interfaces, and verification approaches from one may transfer to the other.
Requirements follow the EARS pattern (Easy Approach to Requirements Syntax) and are traced through a derivation chain: Stakeholder Needs (STK) → System Requirements (SYS) → Subsystem Requirements (SUB) / Interface Requirements (IFC) → Verification Plan (VER). The traceability matrices at the end of this report show every link in that chain.
| Acronym | Expansion |
|---|---|
| ARC | Architecture Decisions |
| CCCS | Completeness, Consistency, Correctness, Stability |
| EARS | Easy Approach to Requirements Syntax |
| IFC | Interface Requirements |
| RMAP | Remote Memory Access Protocol |
| STK | Stakeholder Requirements |
| SUB | Subsystem Requirements |
| SYS | System Requirements |
| UHT | Universal Hex Taxonomy |
| VER | Verification Plan |
flowchart TB n0["system<br>Earth Observation Satellite"] n1["actor<br>Ground Control Station"] n2["actor<br>Mission Planning System"] n3["actor<br>Data Archive Centre"] n4["actor<br>Sun"] n5["actor<br>Earth Surface"] n0 -->|Telemetry and commands| n1 n2 -->|Imaging tasking orders| n0 n0 -->|Earth observation data| n3 n4 -->|Solar radiation| n0 n5 -->|Reflected and emitted radiation| n0
Earth Observation Satellite — Context
flowchart TB n0["system<br>Earth Observation Satellite"] n1["subsystem<br>Optical Payload Subsystem"] n2["subsystem<br>Attitude and Orbit Control Subsystem"] n3["subsystem<br>Electrical Power Subsystem"] n4["subsystem<br>Telemetry Tracking and Command Subsystem"] n5["subsystem<br>Onboard Data Handling Subsystem"] n6["subsystem<br>Thermal Control Subsystem"] n7["system<br>Earth Observation Satellite"] n8["subsystem<br>Optical Payload"] n9["subsystem<br>AOCS"] n10["subsystem<br>Electrical Power"] n11["subsystem<br>OBDH"] n12["subsystem<br>TTC"] n13["subsystem<br>Thermal Control"] n14["subsystem<br>Structure & Mechanisms"] n15["subsystem<br>Propulsion"] n0 -->|contains| n1 n0 -->|contains| n2 n0 -->|contains| n3 n0 -->|contains| n4 n0 -->|contains| n5 n0 -->|contains| n6 n1 -->|Image data| n5 n5 -->|Downlink data| n4 n2 -->|Attitude telemetry| n5 n3 -->|Power status| n5 n8 -->|image data| n11 n11 -->|downlink data| n12 n10 -->|regulated power| n11 n9 -->|thruster commands| n15 n13 -->|cryo cooling| n8 n14 -->|array deployment| n10
Earth Observation Satellite — Decomposition
| Ref | Requirement | V&V | Tags |
|---|---|---|---|
| STK-STAKEHOLDERNEEDS-001 | The Earth Observation Satellite shall acquire multispectral imagery of the Earth's surface with sufficient spatial resolution to support land use classification, vegetation monitoring, and disaster response. | — | stakeholder, session-176 |
| STK-STAKEHOLDERNEEDS-002 | The Earth Observation Satellite shall downlink acquired imagery to designated ground stations within 24 hours of acquisition to enable timely analysis. | — | stakeholder, session-176 |
| STK-STAKEHOLDERNEEDS-003 | The Earth Observation Satellite shall operate autonomously in low Earth orbit for a minimum mission lifetime of 7 years without requiring on-orbit servicing. | — | stakeholder, session-176 |
| STK-STAKEHOLDERNEEDS-004 | The Earth Observation Satellite shall comply with applicable space debris mitigation guidelines, including controlled deorbiting within 25 years of end of mission. | — | stakeholder, session-176 |
| STK-STAKEHOLDERNEEDS-005 | The Earth Observation Satellite shall maintain pointing accuracy sufficient to geolocate acquired imagery to within 50 metres without ground control points. | — | stakeholder, session-176 |
| STK-STAKEHOLDERNEEDS-006 | The Earth Observation Satellite shall be compatible with existing ground segment infrastructure and data distribution standards used by the operating agency. | — | stakeholder, session-176 |
| STK-STAKEHOLDERNEEDS-007 | The Earth Observation Satellite shall survive and recover from single-event upsets and transient radiation effects encountered in the LEO radiation environment. | — | stakeholder, session-176 |
| Ref | Requirement | V&V | Tags |
|---|---|---|---|
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | The Optical Payload Subsystem SHALL provide multispectral imaging in at least 4 spectral bands spanning visible (450-690 nm), near-infrared (760-900 nm), and shortwave infrared (1550-1750 nm) wavelengths. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-002 | The Optical Payload Subsystem SHALL achieve a ground sampling distance of 10 metres or better at nadir from the operational orbit altitude. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | The Telemetry Tracking and Command Subsystem SHALL support a payload data downlink rate of at least 800 Mbps via X-band to enable full orbit data dump within available ground station contact windows. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | The Electrical Power Subsystem SHALL generate a minimum of 2500 W end-of-life orbital average power to sustain all subsystem operations over the 7-year mission lifetime. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | The Onboard Data Handling Subsystem SHALL execute autonomous fault detection, isolation, and recovery procedures to maintain safe mode within 60 seconds of anomaly detection without ground intervention. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-006 | The Attitude and Orbit Control Subsystem SHALL provide sufficient delta-V capacity for controlled deorbit at end of mission to achieve atmospheric re-entry within 5 years of decommissioning. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | The Attitude and Orbit Control Subsystem SHALL maintain pointing knowledge accuracy of 0.01 degrees (3-sigma) in all three axes during imaging operations. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-008 | The Attitude and Orbit Control Subsystem SHALL achieve pointing stability of 0.001 degrees per second (3-sigma) during payload data acquisition. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | The Telemetry Tracking and Command Subsystem SHALL implement CCSDS packet telemetry and telecommand standards for all ground-to-space and space-to-ground communications. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-010 | The Onboard Data Handling Subsystem SHALL employ radiation-hardened or radiation-tolerant components rated to a minimum total ionising dose of 30 krad for all mission-critical processing elements. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | The Thermal Control Subsystem SHALL maintain all satellite components within their qualified operating temperature ranges throughout all orbital conditions including eclipse, sunlit, and safe mode. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | The Onboard Data Handling Subsystem SHALL provide a minimum of 2 Tbit solid-state mass memory capacity for storing payload data between ground station contacts. | — | system, session-176 |
| SYS-SYSTEM-LEVELREQUIREMENTS-013 | The Structure and Mechanisms Subsystem SHALL withstand quasi-static launch loads of 8g axial and 3g lateral with positive structural margins, maintain first natural frequencies above 25 Hz axial and 10 Hz lateral, and provide mounting interfaces for all satellite subsystems. | — | system, structure-mechanisms, session-184 |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | The Structure and Mechanisms Subsystem SHALL withstand quasi-static launch loads of 8g axial and 3g lateral with positive structural margins, maintain first natural frequencies above 25 Hz axial and 10 Hz lateral, and provide mounting interfaces for all satellite subsystems. | — | system, structure-mechanisms, session-184 |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | The Propulsion Subsystem SHALL provide a total delta-V capacity of at least 150 m/s for a 2000 kg satellite to support orbit maintenance manoeuvres and controlled deorbit within 25 years in compliance with IADC space debris mitigation guidelines. | — | system, propulsion, session-184 |
| Ref | Requirement | V&V | Tags |
|---|---|---|---|
| SUB-SUBSYSTEMREQUIREMENTS-001 | The Telescope Assembly SHALL provide a clear aperture diameter of not less than 500 mm with a Korsch three-mirror anastigmat design to achieve the required ground sampling distance. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-002 | The Focal Plane Array SHALL provide detector elements covering visible (450-690 nm), near-infrared (760-900 nm), and shortwave infrared (1550-1750 nm) spectral bands with quantum efficiency exceeding 0.6 in each band. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-003 | While imaging, the Focal Plane Array SWIR detectors SHALL be maintained at an operating temperature of 150 K or below by the integrated cryocooler to achieve the required signal-to-noise ratio. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-004 | The Image Processing Unit SHALL implement CCSDS 122.0 lossless compression achieving a compression ratio of at least 2:1 for all spectral bands without loss of radiometric fidelity. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-005 | The Image Processing Unit SHALL process and format payload data at a sustained throughput of at least 1.2 Gbps to prevent data loss during continuous imaging passes. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-006 | The Spectral Filter Mechanism SHALL achieve out-of-band rejection of at least 10^-4 for each spectral channel to prevent cross-band contamination of image data. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-007 | The Spectral Filter Mechanism SHALL complete band selection transitions in less than 200 milliseconds to support multi-band imaging within a single ground track pass. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-008 | The Calibration System SHALL provide absolute radiometric calibration accuracy of 5% or better traceable to SI standards across all spectral bands over the full mission lifetime. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-009 | While in imaging mode, the Telescope Assembly SHALL maintain primary-to-secondary mirror alignment within 5 micrometres to preserve modulation transfer function performance across the full field of view. | — | subsystem, optical-payload, session-177 |
| SUB-SUBSYSTEMREQUIREMENTS-010 | The Star Tracker Assembly SHALL determine inertial attitude with an accuracy of 3 arcseconds (3-sigma) per axis across the full celestial sphere, excluding zones within 20 degrees of the Sun. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-011 | The Reaction Wheel Assembly SHALL provide a total angular momentum storage capacity of at least 50 Nms per axis in a four-wheel redundant tetrahedral configuration to support agile imaging slew manoeuvres of 30 degrees in under 60 seconds. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-012 | The Magnetorquer System SHALL generate a magnetic dipole moment of at least 30 Am2 per axis to desaturate the Reaction Wheel Assembly from 80% stored momentum to below 20% within one orbit period at any orbital inclination. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-013 | The GNSS Receiver SHALL provide autonomous orbit position determination with accuracy better than 10 metres (3-sigma) and velocity determination better than 0.1 m/s (3-sigma) using dual-frequency GPS/Galileo L1/L5 signals. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-014 | The AOCS Flight Software SHALL implement an extended Kalman filter fusing star tracker, GNSS, and magnetometer measurements to provide filtered attitude knowledge with accuracy better than 0.005 degrees (3-sigma) per axis at a minimum update rate of 10 Hz. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-015 | When a fault is detected by the AOCS Flight Software, the AOCS shall autonomously transition from any operational mode to safe mode within 10 seconds while maintaining Sun-pointing attitude to preserve positive power balance. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-016 | While in imaging mode, the Reaction Wheel Assembly SHALL limit micro-vibration disturbance torque to below 10 mNm amplitude at frequencies above 1 Hz to prevent image smear in the Optical Payload Subsystem. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-017 | The GNSS Receiver SHALL provide a UTC time reference with accuracy better than 100 nanoseconds (1-sigma) to the Onboard Data Handling Subsystem for payload image time-stamping and orbit event synchronisation. | — | subsystem, aocs, session-178 |
| SUB-SUBSYSTEMREQUIREMENTS-018 | The Solar Array Assembly SHALL generate a minimum beginning-of-life power of 3200 W under AM0 illumination at normal incidence to ensure 2500 W end-of-life orbital average power after accounting for cell degradation, cosine losses, and eclipse fraction over a 7-year mission. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-019 | The Battery Assembly SHALL provide a minimum usable energy storage capacity of 1500 Wh at end-of-life to sustain all essential spacecraft loads during a maximum eclipse duration of 35 minutes without bus voltage excursion below 26 V. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-020 | The Power Control and Distribution Unit SHALL regulate the primary power bus to 28 V +/- 2 V under all load conditions from minimum keep-alive to peak imaging power, including load transients of up to 500 W step change. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-021 | The Solar Array Drive Mechanism SHALL track the Sun with a pointing accuracy of 1 degree or better about the rotation axis throughout the sunlit portion of each orbit to maintain solar array power output within 2% of the maximum achievable. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-022 | When the battery state of charge falls below 30%, the Power Management Software SHALL autonomously execute load shedding of non-essential loads within 500 milliseconds in a priority sequence defined by the ground-configurable load priority table. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-023 | The Battery Assembly SHALL sustain a minimum of 60000 charge-discharge cycles at a depth of discharge not exceeding 25% with capacity fade of less than 20% from beginning-of-life rated capacity over the 7-year mission duration. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-024 | The Power Control and Distribution Unit SHALL implement maximum power point tracking with an efficiency of 97% or better across the full solar array voltage range from beginning-of-life cold to end-of-life hot operating conditions. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-025 | When the spacecraft enters safe mode, the Power Management Software SHALL configure the Electrical Power Subsystem to maintain positive power balance by shedding all payload loads and non-essential platform loads within 2 seconds while preserving Sun-pointing attitude control power. | — | subsystem, eps, session-179 |
| SUB-SUBSYSTEMREQUIREMENTS-026 | The Onboard Computer SHALL employ a radiation-hardened processor with a minimum computational throughput of 400 MIPS and 256 MB of EDAC-protected SRAM to support concurrent execution of FDIR, command processing, and telemetry formatting tasks. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-027 | The Mass Memory Unit SHALL provide a minimum of 2 Tbit usable storage capacity using NAND flash with triple-module redundancy error correction achieving a bit error rate below 10^-15 after correction. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-028 | The SpaceWire Network Router SHALL provide at least 8 bidirectional SpaceWire ports operating at a link rate of 200 Mbps per port with deterministic latency not exceeding 5 microseconds per hop. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-029 | The Mass Memory Unit SHALL support simultaneous write from the payload data stream and read for downlink at a sustained aggregate throughput of 1.5 Gbps without data loss or write-stall conditions. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-030 | The Onboard Data Handling Software SHALL implement autonomous fault detection, isolation, and recovery covering at minimum single-event upsets, processor watchdog timeout, memory parity errors, and SpaceWire link failures, with fault detection latency not exceeding 500 milliseconds. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-031 | The Remote Terminal Unit SHALL acquire analog sensor measurements with 16-bit resolution and absolute accuracy of 0.1% of full scale, sampling at least 100 channels at a minimum rate of 1 Hz for housekeeping telemetry collection. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-032 | When a telecommand is received, the Onboard Data Handling Software SHALL validate command authentication, sequence count, and parameter range within 100 milliseconds and reject commands failing any validation check with a rejection telemetry report. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-033 | The SpaceWire Network Router SHALL distribute time-code ticks synchronised to the GNSS-derived UTC reference with a maximum jitter of 1 microsecond to all connected subsystem nodes for correlation of payload and housekeeping timestamps. | — | subsystem, obdh, session-180 |
| SUB-SUBSYSTEMREQUIREMENTS-034 | The S-Band Transponder SHALL receive telecommands at data rates up to 64 kbps on the 2025-2110 MHz uplink band and transmit telemetry at data rates up to 512 kbps on the 2200-2290 MHz downlink band, with a minimum receiver sensitivity of -110 dBm. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-035 | The S-Band Transponder SHALL support coherent turnaround mode with a transponder ratio of 240/221 to enable two-way Doppler range-rate measurements with an accuracy better than 0.1 mm/s. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-036 | The X-Band Transmitter SHALL deliver a minimum RF output power of 8 W at the antenna port across the 8.025-8.4 GHz downlink band, supporting selectable data rates of 150, 300, 450, 600, and 800 Mbps with OQPSK modulation. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-037 | The X-Band Transmitter SHALL achieve a power-added efficiency of not less than 25% at the rated 8 W output, with total DC power consumption not exceeding 50 W in transmit mode. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-038 | The Baseband Data Processor SHALL implement CCSDS AOS transfer frame assembly with virtual channel multiplexing supporting at least 8 virtual channels, and SHALL apply concatenated Reed-Solomon (223,255) and convolutional (rate 1/2, K=7) forward error correction coding for X-band downlink. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-039 | The Baseband Data Processor SHALL sustain a continuous throughput of 800 Mbps from the Mass Memory Unit to the X-Band Transmitter without frame loss during ground station passes. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-040 | The X-Band High-Gain Antenna SHALL provide a minimum gain of 34 dBi at 8.2 GHz with a two-axis gimbal mechanism enabling ±90 degree steering in both azimuth and elevation to track ground stations during LEO passes. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-041 | The X-Band High-Gain Antenna gimbal SHALL achieve a pointing accuracy better than 0.3 degrees and a slew rate of at least 2 degrees per second to maintain link margin during overhead passes with angular rates up to 1 degree per second. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-042 | The S-Band Antenna Assembly SHALL provide near-omnidirectional coverage with a minimum gain of -3 dBi over at least 95% of the sphere surrounding the spacecraft to ensure telecommand reception and telemetry transmission in any attitude. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-043 | When the onboard schedule initiates a ground station pass, the Baseband Data Processor SHALL prioritise real-time imaging data replay over deferred housekeeping data, ensuring that the highest-priority virtual channel occupies at least 80% of the available downlink bandwidth. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-044 | While the spacecraft is in safe mode, the S-Band Transponder SHALL remain operational on low-power mode with telemetry transmission at a minimum rate of 4 kbps to support anomaly diagnosis from the ground. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-045 | The S-Band Transponder SHALL implement CCSDS Proximity-1 compatible command authentication to reject unauthorized telecommands with a false-acceptance probability below 10^-16 per command. | — | subsystem, ttc, session-182 |
| SUB-SUBSYSTEMREQUIREMENTS-046 | The Pulse-Tube Cryocooler SHALL maintain the SWIR focal plane array cold-finger temperature at 150 K ±2 K throughout the orbital cycle, including during eclipse transient conditions. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-047 | The Thermostatically Controlled Heater System SHALL maintain battery pack temperature above 0°C and propellant line temperature above 5°C during eclipse and safe-mode conditions without OBC intervention. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-048 | The Optical Solar Reflector Radiator Panels SHALL reject a minimum of 600 W orbit-average heat load while maintaining panel equilibrium temperature below 20°C at end-of-life solar absorptance. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-049 | The Heat Pipe Network SHALL limit equipment panel temperature gradients to less than 5°C across any 0.5 m span under maximum internal dissipation conditions. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-050 | The Deployable Cryocooler Radiator SHALL reject a minimum of 100 W at a panel equilibrium temperature of -40°C to provide adequate thermal margin for end-of-life cryocooler waste heat dissipation. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-051 | The Multi-Layer Insulation Blankets SHALL achieve an effective emittance of less than 0.03 over all covered external surfaces to limit parasitic heat leaks to below 50 W total. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-052 | While the spacecraft is in safe mode, the Thermal Control Subsystem SHALL maintain all equipment within survival temperature limits using only survival heater circuits powered from the unregulated bus. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-053 | The Pulse-Tube Cryocooler SHALL export vibration forces of less than 100 mN at the compressor drive frequency to prevent degradation of optical payload image quality. | — | subsystem, thermal-control, session-183 |
| SUB-SUBSYSTEMREQUIREMENTS-054 | The Primary Structure SHALL maintain positive structural margins under combined quasi-static loads of 8g axial and 3g lateral with a factor of safety of 1.25 on yield and 1.5 on ultimate for all load-bearing members. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-055 | The Primary Structure SHALL exhibit a first natural frequency above 25 Hz in the axial direction and above 10 Hz in the lateral direction in the stowed launch configuration. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-056 | The Solar Array Deployment Mechanism SHALL deploy both solar array wings to the operational configuration within 120 seconds of receiving the deployment command, with deployment confirmation telemetry provided to the OBDH within 5 seconds of latch engagement. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-057 | The Launch Vehicle Adapter SHALL achieve clean separation with tip-off rates below 1.0 deg/s in all axes and a relative separation velocity of 0.5 m/s plus or minus 0.1 m/s. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-058 | The Antenna Deployment Boom SHALL exhibit a first deployed natural frequency above 5 Hz with the antenna payload mass of 3.2 kg at the tip, to avoid coupling with the AOCS control bandwidth. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-059 | The Harness Assembly SHALL maintain a minimum separation of 50 mm between power, signal, and pyrotechnic harness routing paths and SHALL employ shielded connectors with EMI backshells on all data interfaces to limit conducted emissions below MIL-STD-461G CE102 limits. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-060 | The Solar Array Deployment Mechanism hold-down and release system SHALL achieve a release reliability of at least 0.9999 per wing using redundant Frangibolt actuators with independent initiation circuits. | — | subsystem, structure-mechanisms, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-061 | The Thruster Assembly SHALL deliver a thrust of 0.9 N to 1.1 N per thruster over the blowdown pressure range of 22 bar to 5.5 bar with a specific impulse of at least 215 seconds. | — | subsystem, propulsion, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-062 | The Thruster Assembly SHALL provide a minimum impulse bit of 50 mN-s or less to support fine orbit adjustment manoeuvres. | — | subsystem, propulsion, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-063 | The Propellant Tank SHALL store a minimum of 45 kg of hydrazine propellant with a MEOP of 24 bar and an expulsion efficiency of at least 98%. | — | subsystem, propulsion, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-064 | When a thruster firing is commanded, the catalyst bed heaters SHALL have maintained the catalyst bed temperature above 150 degrees Celsius for a minimum of 30 minutes prior to the first pulse to prevent cold-start degradation. | — | subsystem, propulsion, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-065 | The Propellant Management Assembly SHALL provide series-redundant propellant isolation via two normally-closed latch valves, each independently commandable, to prevent uncommanded propellant flow to the thrusters. | — | subsystem, propulsion, session-184 |
| SUB-SUBSYSTEMREQUIREMENTS-066 | The Thruster Assembly SHALL be qualified for a minimum of 50000 pulses and 10 hours cumulative firing time without degradation in thrust or specific impulse below specification limits. | — | subsystem, propulsion, session-184 |
| Ref | Requirement | V&V | Tags |
|---|---|---|---|
| IFC-INTERFACEDEFINITIONS-001 | The interface between Telescope Assembly and Spectral Filter Mechanism SHALL present a collimated beam with wavefront error not exceeding lambda/10 RMS at 632.8 nm across the full field of view. | — | interface, optical-payload, session-177 |
| IFC-INTERFACEDEFINITIONS-002 | The interface between Focal Plane Array and Image Processing Unit SHALL use LVDS differential signalling at a data rate of 1.2 Gbps per channel with a maximum of 4 parallel channels. | — | interface, optical-payload, session-177 |
| IFC-INTERFACEDEFINITIONS-003 | The interface between Image Processing Unit and Onboard Data Handling Subsystem SHALL use SpaceWire links conforming to ECSS-E-ST-50-12C with a link rate of 200 Mbps per port. | — | interface, optical-payload, session-177 |
| IFC-INTERFACEDEFINITIONS-004 | The interface between Calibration System and Focal Plane Array SHALL provide a uniform illumination field with spatial non-uniformity of less than 1% across the detector active area during calibration sequences. | — | interface, optical-payload, session-177 |
| IFC-INTERFACEDEFINITIONS-005 | The interface between the Star Tracker Assembly and the AOCS Flight Software SHALL use a MIL-STD-1553B data bus transmitting attitude quaternion packets at 10 Hz with a maximum latency of 5 milliseconds from measurement to availability in the Kalman filter. | — | interface, aocs, session-178 |
| IFC-INTERFACEDEFINITIONS-006 | The interface between the AOCS Flight Software and the Reaction Wheel Assembly SHALL transmit torque command vectors at a minimum rate of 20 Hz via a CAN bus interface with command resolution of 0.001 Nm. | — | interface, aocs, session-178 |
| IFC-INTERFACEDEFINITIONS-007 | The interface between the GNSS Receiver and the Onboard Data Handling Subsystem SHALL provide a 1 PPS timing pulse with accuracy better than 100 ns and a serial NMEA/proprietary message stream at 1 Hz carrying position, velocity, and time data. | — | interface, aocs, session-178 |
| IFC-INTERFACEDEFINITIONS-008 | The interface between the Solar Array Assembly and the Power Control and Distribution Unit SHALL transfer unregulated DC power via redundant harness pairs rated for a maximum current of 40 A per string at voltages ranging from 60 V to 120 V across the full solar array operating temperature range of -150 C to +110 C. | — | interface, eps, session-179 |
| IFC-INTERFACEDEFINITIONS-009 | The interface between the Battery Assembly and the Power Control and Distribution Unit SHALL support bidirectional current flow of up to 30 A charge and 50 A discharge via a dedicated battery bus with continuous battery voltage, current, and temperature telemetry sampled at a minimum rate of 1 Hz. | — | interface, eps, session-179 |
| IFC-INTERFACEDEFINITIONS-010 | The interface between the Power Management Software and the Onboard Data Handling Subsystem SHALL use the spacecraft MIL-STD-1553B data bus for exchange of power telemetry packets, load shedding commands, and battery state of health parameters at a minimum update rate of 1 Hz. | — | interface, eps, session-179 |
| IFC-INTERFACEDEFINITIONS-011 | The interface between the Onboard Computer and the SpaceWire Network Router SHALL use ECSS-E-ST-50-12C SpaceWire protocol at 200 Mbps link rate with RMAP (Remote Memory Access Protocol) for register-level access to all connected nodes. | — | interface, obdh, session-180 |
| IFC-INTERFACEDEFINITIONS-012 | The interface between the SpaceWire Network Router and the Mass Memory Unit SHALL support sustained bulk data transfer at 800 Mbps using SpaceWire packet protocol with hardware flow control to prevent buffer overrun during continuous payload recording. | — | interface, obdh, session-180 |
| IFC-INTERFACEDEFINITIONS-013 | The interface between the SpaceWire Network Router and each Remote Terminal Unit SHALL operate at a minimum link rate of 10 Mbps using SpaceWire packet protocol, with each RTU addressable via a unique logical address for targeted housekeeping queries and command relay. | — | interface, obdh, session-180 |
| IFC-INTERFACEDEFINITIONS-014 | The interface between the S-Band Antenna Assembly and the S-Band Transponder SHALL use 50-ohm coaxial connections with SMA connectors, supporting the full 2025-2290 MHz band with insertion loss below 0.5 dB and VSWR below 1.3:1. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-015 | The interface between the S-Band Transponder and the Baseband Data Processor SHALL use a synchronous serial link at 1 Mbps for TM/TC baseband data exchange, with CCSDS transfer frame boundaries delimited by attached sync markers. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-016 | The interface between the Baseband Data Processor and the X-Band Transmitter SHALL use parallel LVDS signalling at a clock rate matching the selected symbol rate, with frame-aligned data valid assertion to synchronise modulator acquisition. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-017 | The interface between the X-Band Transmitter and the X-Band High-Gain Antenna SHALL use WR-112 rectangular waveguide with a maximum insertion loss of 0.3 dB across the 8.025-8.4 GHz band. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-018 | The interface between the Baseband Data Processor and the Mass Memory Unit SHALL use SpaceWire operating at 200 MHz link speed, supporting sustained payload data readout at 800 Mbps via dual redundant links with automatic failover. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-019 | The interface between the S-Band Transponder and the Onboard Computer SHALL use SpaceWire for telecommand packet delivery and telemetry source packet collection, with command latency from RF reception to OBDH delivery below 50 ms. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-020 | The interface between the Onboard Computer and the X-Band High-Gain Antenna gimbal controller SHALL use a CAN bus at 1 Mbps for antenna pointing commands, providing target azimuth and elevation angles at a minimum update rate of 10 Hz during ground station passes. | — | interface, ttc, session-182 |
| IFC-INTERFACEDEFINITIONS-021 | The interface between the Pulse-Tube Cryocooler and the Focal Plane Array SHALL use a flexible copper thermal strap with a conductance of at least 0.5 W/K to thermally isolate cryocooler vibrations from the detector mount. | — | interface, thermal-control, session-183 |
| IFC-INTERFACEDEFINITIONS-022 | The interface between the Thermostatically Controlled Heater System and the Power Control and Distribution Unit SHALL draw a maximum of 180 W from the unregulated 28 V bus for survival heaters during eclipse. | — | interface, thermal-control, session-183 |
| IFC-INTERFACEDEFINITIONS-023 | The interface between the Deployable Cryocooler Radiator and the Pulse-Tube Cryocooler SHALL use two flexible loop heat pipes with ammonia working fluid, each capable of transporting 50 W over a 1 m length. | — | interface, thermal-control, session-183 |
| IFC-INTERFACEDEFINITIONS-024 | The interface between the Heat Pipe Network and equipment mounting panels SHALL provide mechanical mounting provisions for at least 14 constant-conductance and 4 variable-conductance heat pipes with a total transport capacity exceeding 400 W. | — | interface, thermal-control, session-183 |
| IFC-INTERFACEDEFINITIONS-025 | The interface between the Launch Vehicle Adapter and the Primary Structure SHALL be a 1194 mm diameter bolt-circle with 24 M8 titanium bolts providing a minimum axial load capacity of 200 kN and a lateral load capacity of 75 kN. | — | interface, structure-mechanisms, session-184 |
| IFC-INTERFACEDEFINITIONS-026 | The interface between the Antenna Deployment Boom and the X-Band High-Gain Antenna gimbal SHALL provide a mechanical mounting flange with three-axis alignment accuracy of 0.1 degrees and a harness feedthrough for gimbal motor power and encoder signals. | — | interface, structure-mechanisms, session-184 |
| IFC-INTERFACEDEFINITIONS-027 | The interface between the Solar Array Deployment Mechanism and the Remote Terminal Unit SHALL provide discrete telemetry signals indicating hold-down status (stowed/released) and deployment latch engagement for each wing via redundant micro-switches. | — | interface, structure-mechanisms, session-184 |
| IFC-INTERFACEDEFINITIONS-028 | The interface between the Thruster Assembly and the AOCS Flight Software SHALL provide thruster on/off commanding via discrete pulse signals with a minimum pulse width of 20 ms and a maximum command latency of 10 ms from AOCS command issue to valve actuation. | — | interface, propulsion, session-184 |
| IFC-INTERFACEDEFINITIONS-029 | The interface between the Propellant Management Assembly and the Remote Terminal Unit SHALL provide analog telemetry of tank pressure (0-30 bar, 0.25% FSO accuracy), latch valve position status, and catalyst bed temperature for each thruster pair. | — | interface, propulsion, session-184 |
| IFC-INTERFACEDEFINITIONS-030 | The interface between the Propellant Tank and the Primary Structure SHALL provide a mounting bracket capable of supporting the filled tank mass of 53 kg under 8g axial and 3g lateral loads with thermal isolation standoffs limiting heat leak to less than 2 W. | — | interface, propulsion, session-184 |
| Ref | Requirement | V&V | Tags |
|---|---|---|---|
| ARC-ARCHITECTUREDECISIONS-001 | The Propulsion Subsystem SHALL use a monopropellant hydrazine blowdown system rather than bipropellant or electric propulsion. Rationale: hydrazine blowdown provides the simplest architecture for the 150 m/s delta-V budget, avoids oxidiser handling complexity, and offers heritage from ESA LEO missions. Electric propulsion was rejected due to the long thrust durations conflicting with imaging duty cycle requirements. | — | architecture, propulsion, session-186 |
| ARC-ARCHITECTUREDECISIONS-002 | The Onboard Data Handling Subsystem SHALL employ SpaceWire (ECSS-E-ST-50-12C) as the primary high-speed data bus interconnecting payload, mass memory, and platform subsystems. Rationale: SpaceWire provides deterministic latency, time-code distribution, and sufficient bandwidth (200 Mbps per link) for the 800 Mbps aggregate payload data rate when parallelised. MIL-STD-1553B was rejected for insufficient bandwidth; Ethernet-based alternatives lack sufficient spaceflight heritage for this mission class. | — | architecture, obdh, session-186 |
| ARC-ARCHITECTUREDECISIONS-003 | The Telemetry Tracking and Command Subsystem SHALL implement a dual-band architecture using S-band for telecommand uplink and housekeeping telemetry, and X-band for high-rate payload data downlink. Rationale: S-band provides reliable, near-omnidirectional coverage for commanding in all spacecraft attitudes including safe mode. X-band enables the 800 Mbps downlink rate required to empty the 2 Tbit mass memory within available ground station contact windows (typically 10 minutes per pass at 700 km altitude). A single-band approach cannot satisfy both the robust commanding and high-throughput data delivery requirements simultaneously. | — | architecture, ttc, session-186 |
| ARC-ARCHITECTUREDECISIONS-004 | The Thermal Control Subsystem SHALL use a pulse-tube cryocooler with a deployable radiator to cool the SWIR focal plane array, rather than passive radiative cooling or Stirling-cycle coolers. Rationale: the 150 K operating temperature required by the HgCdTe SWIR detector at 700 km sun-synchronous orbit cannot be reliably achieved by passive radiators alone due to Earth albedo and infrared flux. Pulse-tube cryocoolers provide vibration-free operation essential for sub-arcsecond pointing stability, unlike Stirling coolers which export significant mechanical disturbance at the drive frequency. | — | architecture, thermal-control, optical-payload, session-186 |
| ARC-ARCHITECTUREDECISIONS-005 | The Onboard Data Handling Subsystem SHALL employ a centralised radiation-hardened onboard computer with distributed remote terminal units for subsystem I/O acquisition, rather than a federated processing architecture. Rationale: a centralised OBC simplifies FDIR implementation and software qualification. Remote terminal units provide analogue and discrete I/O at each subsystem, reducing harness mass and EMI by keeping analogue signals short. The 400 MIPS processing budget is sufficient for all platform management tasks when payload image processing is handled by a dedicated IPU within the Optical Payload Subsystem. | — | architecture, obdh, session-186 |
| ARC-ARCHITECTUREDECISIONS-006 | The Attitude and Orbit Control Subsystem SHALL use a four-wheel reaction wheel assembly in a tetrahedral configuration with magnetorquer-based momentum unloading, rather than control moment gyroscopes or thruster-based attitude control. Rationale: reaction wheels provide the sub-arcsecond pointing stability and 0.001 deg/s stability required for 10 m GSD imaging. Magnetorquer unloading avoids propellant consumption for routine momentum management, preserving the hydrazine budget for orbit maintenance. CMGs were rejected as oversized for this satellite class. The tetrahedral four-wheel geometry provides single-fault tolerance against any one wheel failure. | — | architecture, aocs, session-186 |
| ARC-ARCHITECTUREDECISIONS-007 | The end-to-end data handling chain from payload to ground SHALL comply with CCSDS standards: CCSDS 122.0 for image compression, CCSDS AOS for transfer frame assembly, and CCSDS proximity-1 for command authentication. Rationale: CCSDS compliance ensures interoperability with existing ESA and partner ground station networks without bespoke protocol adapters. This architectural choice constrains the Baseband Data Processor and Image Processing Unit designs but eliminates ground segment development risk and enables multi-mission ground segment reuse. | — | architecture, obdh, ttc, session-186 |
| Ref | Requirement | V&V | Tags |
|---|---|---|---|
| VER-VERIFICATIONMETHODS-001 | The Telescope Assembly clear aperture and optical design SHALL be verified by inspection of manufacturing drawings and measurement of the as-built aperture diameter. | — | verification, optical-payload, session-177 |
| VER-VERIFICATIONMETHODS-002 | The Focal Plane Array spectral response and quantum efficiency SHALL be verified by test using a calibrated monochromator source across each specified wavelength band at the component acceptance level. | — | verification, optical-payload, session-177 |
| VER-VERIFICATIONMETHODS-003 | The Image Processing Unit compression performance SHALL be verified by test using representative scene data sets, confirming lossless reconstruction and achieved compression ratio. | — | verification, optical-payload, session-177 |
| VER-VERIFICATIONMETHODS-004 | The Calibration System absolute radiometric accuracy SHALL be verified by analysis of pre-launch calibration data and comparison with ground-truth reference targets during the commissioning phase. | — | verification, optical-payload, session-177 |
| VER-VERIFICATIONMETHODS-005 | The Star Tracker Assembly accuracy requirement (SUB-SUBSYSTEMREQUIREMENTS-010) SHALL be verified by test using a star field simulator projecting known catalogue patterns onto the tracker optics and comparing output quaternions against truth data across the full operational temperature range. | — | verification, aocs, session-178 |
| VER-VERIFICATIONMETHODS-006 | The Reaction Wheel Assembly micro-vibration requirement (SUB-SUBSYSTEMREQUIREMENTS-016) SHALL be verified by test using a dynamometric test bench measuring disturbance torque spectral density across the 0.1-500 Hz band at representative wheel speeds and confirming compliance against the image quality allocation budget. | — | verification, aocs, session-178 |
| VER-VERIFICATIONMETHODS-007 | The AOCS safe mode transition requirement (SUB-SUBSYSTEMREQUIREMENTS-015) SHALL be verified by analysis and test using a hardware-in-the-loop simulation injecting fault scenarios into each AOCS sensor and actuator channel and measuring the time from fault injection to stable Sun-pointing safe mode attitude. | — | verification, aocs, session-178 |
| VER-VERIFICATIONMETHODS-008 | The Solar Array Assembly beginning-of-life power output SHALL be verified by test: illuminated I-V curve measurement of each solar panel wing under calibrated AM0 solar simulator conditions at the panel acceptance review, with margin analysis confirming 2500 W EOL orbital average. | — | verification, eps, session-179 |
| VER-VERIFICATIONMETHODS-009 | The Power Management Software autonomous load shedding response SHALL be verified by test: simulated battery SOC ramp-down on the EPS engineering model with measurement of load disconnection timing and sequence against the configurable load priority table, confirming response within 500 ms. | — | verification, eps, session-179 |
| VER-VERIFICATIONMETHODS-010 | The Solar Array to PCDU interface current and voltage characteristics SHALL be verified by test: end-to-end harness continuity and insulation resistance measurement followed by powered functional test across the full voltage range at qualification temperature extremes. | — | verification, eps, session-179 |
| VER-VERIFICATIONMETHODS-011 | The Onboard Computer radiation hardness and computational throughput SHALL be verified by inspection of manufacturer datasheets for total ionising dose rating and by benchmark test executing representative flight software loads on the qualification unit. | — | verification, obdh, session-180 |
| VER-VERIFICATIONMETHODS-012 | The Mass Memory Unit storage capacity and error correction performance SHALL be verified by test filling the complete memory with known data patterns, reading back with injected single-bit and double-bit errors, and confirming corrected readback accuracy. | — | verification, obdh, session-180 |
| VER-VERIFICATIONMETHODS-013 | The OBDH Software FDIR capability SHALL be verified by fault injection test on the software validation facility, injecting each fault type listed in the requirement and measuring detection latency against the 500 millisecond threshold. | — | verification, obdh, session-180 |
| VER-VERIFICATIONMETHODS-014 | The S-Band Transponder receiver sensitivity and data rate performance (SUB-SUBSYSTEMREQUIREMENTS-034) SHALL be verified by test using a calibrated RF signal generator and bit error rate tester in an EMC-shielded chamber, measuring BER at the specified sensitivity threshold across the uplink band. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-015 | The X-Band Transmitter output power and modulation quality (SUB-SUBSYSTEMREQUIREMENTS-036) SHALL be verified by test using a spectrum analyser and power meter at the antenna port, measuring output power, spectral mask compliance, and EVM at each selectable data rate. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-016 | The Baseband Data Processor throughput and FEC coding (SUB-SUBSYSTEMREQUIREMENTS-038, SUB-SUBSYSTEMREQUIREMENTS-039) SHALL be verified by test using a hardware-in-the-loop testbed with simulated SpaceWire payload data input at 800 Mbps, verifying zero frame loss over a 15-minute sustained transfer and correct Reed-Solomon and convolutional encoding by decoding the output with a reference CCSDS decoder. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-017 | The X-Band High-Gain Antenna gain and gimbal pointing accuracy (SUB-SUBSYSTEMREQUIREMENTS-040, SUB-SUBSYSTEMREQUIREMENTS-041) SHALL be verified by test in an antenna measurement range, measuring gain pattern at 8.2 GHz, and by test of the gimbal servo system using optical encoders to verify pointing accuracy and slew rate under simulated orbital pass dynamics. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-018 | The S-Band Antenna Assembly coverage requirement (SUB-SUBSYSTEMREQUIREMENTS-042) SHALL be verified by analysis of the antenna radiation pattern measured in an anechoic chamber, integrated with a spacecraft structural model to account for blockage, confirming minimum gain over 95% of the sphere. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-019 | The S-Band safe mode telemetry capability (SUB-SUBSYSTEMREQUIREMENTS-044) SHALL be verified by test during spacecraft-level thermal vacuum testing, transitioning to safe mode and confirming sustained 4 kbps telemetry transmission with the transponder on low-power settings and reduced bus voltage. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-020 | The Baseband Data Processor to Mass Memory Unit SpaceWire interface (IFC-INTERFACEDEFINITIONS-018) SHALL be verified by test using protocol analysers on both SpaceWire links, confirming sustained 800 Mbps throughput with automatic failover to the redundant link within 100 ms of primary link fault injection. | — | verification, ttc, session-182 |
| VER-VERIFICATIONMETHODS-021 | The Pulse-Tube Cryocooler temperature stability (SUB-SUBSYSTEMREQUIREMENTS-046) SHALL be verified by test: operate cryocooler in thermal-vacuum chamber over simulated orbital thermal cycling for 48 hours, measuring cold-finger temperature with calibrated Cernox sensor at 1 Hz sampling. | — | verification, thermal-control, session-183 |
| VER-VERIFICATIONMETHODS-022 | The survival heater autonomous operation (SUB-SUBSYSTEMREQUIREMENTS-047) SHALL be verified by test: simulate OBC failure in thermal-vacuum, confirm heater controller maintains battery and propellant temperatures above limits using thermostat-only control for 3 consecutive eclipse cycles. | — | verification, thermal-control, session-183 |
| VER-VERIFICATIONMETHODS-023 | The OSR radiator heat rejection capacity (SUB-SUBSYSTEMREQUIREMENTS-048) SHALL be verified by analysis: thermal mathematical model correlation to thermal-balance test data, demonstrating 600 W rejection at EOL absorptance with 10% margin. | — | verification, thermal-control, session-183 |
| VER-VERIFICATIONMETHODS-024 | The Primary Structure structural margins (SUB-SUBSYSTEMREQUIREMENTS-054) SHALL be verified by analysis: finite element model correlated with static test results at qualification load levels, followed by review of positive margins on all load-bearing members. | — | verification, structure-mechanisms, session-184 |
| VER-VERIFICATIONMETHODS-025 | The Primary Structure natural frequency requirements (SUB-SUBSYSTEMREQUIREMENTS-055) SHALL be verified by test: modal survey on the flight-representative structural model measuring first axial and first lateral modes. | — | verification, structure-mechanisms, session-184 |
| VER-VERIFICATIONMETHODS-026 | The Solar Array Deployment Mechanism deployment time and telemetry requirements (SUB-SUBSYSTEMREQUIREMENTS-056) SHALL be verified by test: gravity-compensated deployment tests with flight hardware, measuring deployment duration and confirming micro-switch telemetry within 5 seconds. | — | verification, structure-mechanisms, session-184 |
| VER-VERIFICATIONMETHODS-027 | The Thruster Assembly thrust and specific impulse (SUB-SUBSYSTEMREQUIREMENTS-061) SHALL be verified by test: hot-fire acceptance test measuring thrust and Isp at beginning-of-blowdown and end-of-blowdown pressures. | — | verification, propulsion, session-184 |
| VER-VERIFICATIONMETHODS-028 | The Propellant Management Assembly isolation capability (SUB-SUBSYSTEMREQUIREMENTS-065) SHALL be verified by test: leak test of each latch valve at MEOP confirming external leakage below 1E-6 scc/s helium and internal leakage below 1E-3 scc/s helium. | — | verification, propulsion, session-184 |
flowchart TB n0["component<br>AOCS Flight Software"] n1["component<br>Star Tracker Assembly"] n2["component<br>Reaction Wheel Assembly"] n3["component<br>Magnetorquer System"] n4["component<br>GNSS Receiver"] n5["component<br>AOCS Flight Software"] n6["component<br>Star Tracker Assembly"] n7["component<br>Reaction Wheel Assembly"] n8["component<br>Magnetorquer System"] n9["component<br>GNSS Receiver"] n6 -->|attitude quaternions| n5 n9 -->|orbit PVT| n5 n5 -->|torque commands| n7 n5 -->|dipole commands| n8
Attitude and Orbit Control Subsystem — Internal
flowchart TB n0["system<br>Electrical Power Subsystem"] n1["component<br>Solar Array Assembly"] n2["component<br>Battery Assembly"] n3["component<br>Power Control and Distribution Unit"] n4["component<br>Solar Array Drive Mechanism"] n5["component<br>Power Management Software"] n1 -->|Unregulated DC power| n3 n3 -->|Charge/discharge current| n2 n5 -->|MPPT and load commands| n3 n5 -->|Array pointing commands| n4 n3 -->|28V regulated bus| n0
Electrical Power Subsystem — Internal
flowchart TB n0["component<br>Onboard Computer"] n1["component<br>Mass Memory Unit"] n2["component<br>SpaceWire Network Router"] n3["component<br>Remote Terminal Unit"] n4["component<br>OBDH Software"] n4 -->|Flight software executes on processor| n0 n0 -->|Commands and telemetry packets| n2 n2 -->|Payload and housekeeping data| n1 n2 -->|Sensor queries and actuator commands| n3 n0 -->|Store and retrieve commands| n1
Onboard Data Handling Subsystem — Internal
flowchart TB n0["component<br>S-Band Antenna Assembly"] n1["component<br>S-Band Transponder"] n2["component<br>Baseband Data Processor"] n3["component<br>X-Band Transmitter"] n4["component<br>X-Band High-Gain Antenna"] n5["external<br>Onboard Computer"] n6["external<br>Mass Memory Unit"] n7["actor<br>Ground Station"] n7 -->|S-band uplink/downlink RF| n0 n0 -->|S-band RF via coax| n1 n1 -->|TM/TC baseband data| n2 n2 -->|CCSDS frames via LVDS| n3 n3 -->|X-band RF via waveguide| n4 n4 -->|X-band downlink RF| n7 n6 -->|Payload data via SpaceWire| n2 n5 -->|HK telemetry and scheduling| n2 n1 -->|TC packets via SpaceWire| n5 n5 -->|Antenna pointing commands| n4
Telemetry Tracking and Command Subsystem — Internal
flowchart TB n0["component<br>Pulse-Tube Cryocooler"] n1["component<br>MLI Blankets"] n2["component<br>OSR Radiator Panels"] n3["component<br>Heat Pipe Network"] n4["component<br>Heater System"] n5["component<br>Deployable Cryo Radiator"] n6["external<br>Focal Plane Array"] n7["external<br>PCDU"] n0 -->|150K cooling| n6 n0 -->|waste heat| n5 n3 -->|conducted heat| n2 n4 -->|heater power| n7
Thermal Control Subsystem — Internal Block
| Entity | Hex Code | Description |
|---|---|---|
| Antenna Deployment Boom | CE951018 | Deployable carbon-fibre boom for the X-band high-gain antenna on a LEO Earth observation satellite. Single-hinge deployment with torsion spring actuator and viscous fluid damper. Stowed length 0.4 m, deployed length 1.8 m. Carries the 0.6 m parabolic reflector and two-axis gimbal assembly (total tip mass 3.2 kg). Boom stiffness requirement: first deployed frequency >5 Hz to avoid coupling with AOCS control bandwidth. Hold-down via fusible wire with redundant heater elements. Includes thermal knife backup release. Must survive thermal cycling -120C to +100C without permanent deformation. |
| AOCS Flight Software | 41F73B18 | Attitude and orbit control flight software running on the AOCS processor within an Earth observation satellite. Implements attitude determination algorithms (extended Kalman filter fusing star tracker, gyro, and magnetometer data), guidance profiles for imaging/slew/safe modes, and closed-loop control laws commanding reaction wheels and magnetorquers. Manages mode transitions, fault detection, and orbit propagation. |
| Attitude and Orbit Control Subsystem | 55F73218 | Satellite pointing and orbit maintenance subsystem comprising reaction wheels, magnetorquers, star trackers, sun sensors, GPS receiver, and propulsion thrusters for precise attitude determination and control in low Earth orbit. |
| Baseband Data Processor | 51F57008 | Digital signal processing unit responsible for CCSDS transfer frame assembly, virtual channel multiplexing, forward error correction encoding (convolutional + Reed-Solomon for X-band, BCH for S-band), and modulation baseband signal generation. Receives payload data from the Mass Memory Unit via SpaceWire at rates up to 800 Mbps and housekeeping telemetry from the Onboard Computer. Implements AOS (Advanced Orbiting Systems) protocol stack per CCSDS 732.0. Manages downlink scheduling, prioritising real-time imaging data over stored data replay. FPGA-based architecture for deterministic throughput. Power consumption 25W. |
| Battery Assembly | D6D51218 | Lithium-ion battery pack providing eclipse power for an earth observation satellite. Sized for 35-minute eclipse duration at full operational load. Includes cell modules, battery management electronics, thermal sensors, and heater circuits. Minimum 60000 charge-discharge cycles over 7-year mission life. |
| Calibration System | 54F73218 | Onboard radiometric and spectral calibration system for Earth observation satellite payload. Includes solar diffuser panel for absolute calibration and internal LED sources for relative calibration. Provides traceable reference measurements over 7-year mission lifetime. |
| Deployable Cryocooler Radiator | CE851018 | Single-panel deployable radiator dedicated to pulse-tube cryocooler waste heat rejection. 0.8 m² white-painted aluminium honeycomb panel deployed by a hinge mechanism after launch. Rejection capacity: 100W at -40°C panel temperature, providing adequate margin for 75W EOL cryocooler waste heat. Connected to cryocooler compressor via two 1m flexible loop heat pipes with ammonia working fluid. Deployed panel has dedicated MLI backside insulation and sun shield. |
| Earth Observation Satellite | DDF75219 | A low-Earth-orbit satellite system for remote sensing and Earth observation, carrying multispectral imaging payloads, with onboard data processing, attitude control, power generation, thermal management, and ground communication capabilities. |
| Electrical Power Subsystem | 54D73218 | Satellite power generation, storage, and distribution subsystem with deployable solar arrays, lithium-ion battery packs, power conditioning and distribution unit, and solar array drive mechanisms for continuous power supply through eclipse and sunlit orbital phases. |
| Focal Plane Array | D4D51018 | Multispectral detector array for Earth observation satellite optical payload. Contains CCD and CMOS sensors covering visible, near-infrared, and shortwave infrared bands. Converts focused photons into electrical signals. Requires cryogenic cooling for SWIR channels. |
| Harness Assembly | C6851018 | Complete satellite electrical harness for a 2000 kg LEO Earth observation satellite. Approximately 45 kg of cabling comprising power distribution harness (28V regulated bus, up to 80A peak), SpaceWire data harness (shielded twisted pair), pyrotechnic firing harness (isolated, shielded, with safe/arm switching), and RF coaxial cables (semi-rigid and flexible segments). Connectors are space-qualified micro-D and D-sub with EMI backshells. Harness routing designed for minimum EMI coupling between power, signal, and pyro circuits with >50mm separation and dedicated grounding scheme. All cables are radiation-resistant polyimide-insulated with ETFE jackets. |
| Heat Pipe Network | C6D51008 | Aluminium-ammonia axially grooved heat pipe network distributing thermal loads between equipment mounting surfaces and radiator panels. 14 constant-conductance heat pipes (CCHP) embedded in honeycomb equipment panels, plus 4 variable-conductance heat pipes (VCHP) with nitrogen charge for temperature regulation during eclipse. Transport capacity: 20-40W per pipe over 0.5-1.2m lengths. Operating temperature range: -20°C to +50°C. Flight heritage: Sentinel-2 platform. |
| Image Processing Unit | 50F53008 | Onboard electronics unit for Earth observation satellite payload data processing. Performs radiometric correction, geometric correction, lossless and lossy compression, and formats data into CCSDS packets for downlink. Implements FPGA-based processing pipeline. |
| Launch Vehicle Adapter | CE851018 | Clampband separation system interfacing the Earth observation satellite to the launch vehicle payload adapter. 1194 mm bolt-circle diameter (compatible with Vega-C Type-2 and Falcon 9 15-inch adapter). Marman clampband with pyrotechnic bolt cutters (redundant initiation) providing clean separation with tip-off rates below 1 deg/s. Separation springs sized for 0.5 m/s relative velocity. Includes separation confirmation micro-switches and umbilical disconnect for ground support equipment. Adapter cone is machined aluminium 7075-T6, mass 12 kg. |
| Magnetorquer System | 54F53208 | Three-axis magnetorquer system within an Earth observation satellite AOCS. Uses electromagnetic coils interacting with Earth's magnetic field to generate low-level control torques for momentum desaturation of reaction wheels. Also provides coarse attitude control during safe mode and initial acquisition. Driven by the AOCS flight software based on modelled geomagnetic field. |
| Mass Memory Unit | D4851018 | Solid-state mass data recorder for an Earth observation satellite. Stores payload imagery, housekeeping telemetry, and science data between ground station passes. NAND flash based with EDAC protection, providing FIFO and random-access retrieval for downlink scheduling. |
| Multi-Layer Insulation Blankets | C6851018 | Spacecraft thermal insulation consisting of 20-layer aluminised Kapton/Dacron MLI blankets covering all external surfaces except radiator panels and optical aperture. Effective emittance: 0.02. Total coverage area: ~12 m². Provides primary thermal isolation from solar flux and deep-space sink. Includes specialised cutouts and closeout details around harness penetrations, deployment mechanisms, and thruster nozzles. Grounding provisions for ESD protection. |
| Onboard Computer | D1F77018 | Central flight processor for an Earth observation satellite data handling subsystem. Radiation-hardened processor executing flight software, managing command decoding, telemetry formatting, and autonomous operations scheduling. Interfaces with all subsystems via SpaceWire data bus. |
| Onboard Data Handling Software | 41F77B18 | Flight software for the onboard data handling subsystem of an Earth observation satellite. Manages command reception and validation, telemetry packet generation, autonomous fault detection isolation and recovery (FDIR), operations scheduling, and data routing between subsystems. Runs on the radiation-hardened onboard computer. |
| Onboard Data Handling Subsystem | 51F77018 | Satellite central computing and data management subsystem with radiation-hardened processors, solid-state mass memory for image storage, SpaceWire data bus, flight software, and command sequencing for autonomous operations and payload data compression. |
| Optical Payload Subsystem | D4C51018 | Multispectral imaging instrument package for an Earth observation satellite, including visible, near-infrared, and shortwave infrared sensors, focal plane assemblies, and optical telescope assembly for capturing high-resolution Earth imagery. |
| Optical Solar Reflector Radiator Panels | C6851008 | Four body-mounted OSR radiator panels providing passive heat rejection for spacecraft bus electronics. Total radiating area: 3.2 m² on anti-sun and Earth-facing panels. Silver-backed quartz OSR tiles with solar absorptance 0.08 BOL (0.15 EOL after 7 years UV degradation), IR emittance 0.80. Embedded aluminium-ammonia axially grooved heat pipes distribute thermal load across each panel. Rejects 600W orbit-average to deep space at panel temperature 0-20°C. |
| Power Control and Distribution Unit | D7F71008 | Central power electronics unit for an earth observation satellite. Regulates unregulated solar array input to a 28V regulated bus. Performs maximum power point tracking, battery charge/discharge regulation, load switching via latching current limiters, and power telemetry acquisition. Radiation-hardened design for LEO environment. |
| Power Management Software | 41B77B18 | Flight software module executing on the onboard computer that controls the Electrical Power Subsystem of an earth observation satellite. Implements battery charge regulation algorithms, autonomous load shedding in under-power conditions, solar array MPPT control commands, fault detection and safe mode power configuration, and power telemetry formatting for downlink. |
| Primary Structure | CE851018 | Honeycomb aluminium sandwich panel bus structure for a 2000 kg LEO Earth observation satellite. Box-frame configuration approximately 2.0m x 1.8m x 1.5m with 25mm thick Al-5056 honeycomb core panels bonded to 0.5mm CFRP facesheets on equipment-facing sides. Provides mounting surfaces for all subsystem electronics, payload, and propulsion equipment. Internal shear panels carry launch loads through to the launch vehicle adapter interface ring. Design loads: 8g axial, 3g lateral quasi-static with 1.25 safety factor. First natural frequency constraints: >25 Hz axial, >10 Hz lateral. Total structural mass budget 280 kg. |
| Propellant Management Assembly | D6851018 | Fluidic control components for a monopropellant hydrazine propulsion system on a 2000 kg LEO satellite. Comprises two normally-closed latch valves (series-redundant for propellant isolation), a 10-micron sintered metal filter upstream of the thruster valves, fill-and-drain valve with capped service port, pressure transducer (0-30 bar, 0.25% FSO accuracy) on the pressurant side, and a bleed valve for ground servicing. All wetted materials compatible with hydrazine (Ti-6Al-4V, 304L stainless). Latch valves have independent heaters for thermal control during cold-case operations. |
| Propellant Tank | CE851018 | Titanium diaphragm propellant tank for a monopropellant hydrazine system on a LEO Earth observation satellite. Ti-6Al-4V shell, 480mm diameter sphere, MEOP 24 bar with burst factor 2.0. Elastomeric diaphragm (AF-E-332) separating pressurant (GN2) from 45 kg hydrazine propellant. Expulsion efficiency >98%. Operating temperature range 10-50C maintained by spacecraft thermal control. Mass 8 kg empty. Tank mounted at spacecraft centre of mass on the Primary Structure central panel to minimise slosh-induced attitude disturbances. |
| Pulse-Tube Cryocooler | D6D51018 | Thales LPT9310 single-stage pulse-tube cryocooler providing 1.5W cooling at 150K for HgCdTe SWIR focal plane detectors. Input power: 55W at beginning of life, 75W end of life. Compressor lifetime: >60,000 hours. Cold finger interfaces to detector cold plate via flexible copper thermal strap. Waste heat (55-75W) rejected via dedicated deployable radiator panel. Vibration export: <100mN at drive frequency, managed by active vibration cancellation using back-to-back compressor configuration. |
| Reaction Wheel Assembly | D6F51018 | Four-wheel reaction wheel assembly in a redundant tetrahedral configuration within an Earth observation satellite AOCS. Provides fine three-axis torque for precision pointing and slew manoeuvres. Each wheel stores up to 50 Nms angular momentum, driven by brushless DC motors with closed-loop speed control. Used for agile imaging and maintaining pointing stability during payload operations. |
| Remote Terminal Unit | D5F57008 | Distributed I/O module for an Earth observation satellite data handling subsystem. Acquires analog and digital sensor data from thermal, power, and structural health sensors, digitises readings, and transmits housekeeping telemetry packets to the onboard computer via SpaceWire. Also relays discrete commands to actuators and heaters. |
| S-Band Antenna Assembly | C6851018 | Dual hemispherical S-band antenna assembly providing near-omnidirectional coverage for TM/TC links. Consists of two quadrifilar helix antennas mounted on opposing faces of the spacecraft bus, each with approximately 5 dBi peak gain and greater than -3 dBi over the hemisphere. Right-hand circular polarisation. Frequency range 2025-2290 MHz covering both uplink and downlink bands. Connected to the S-Band Transponder via coaxial cables and a hybrid coupler/diplexer network. Passive components with no active electronics — designed for 7+ year LEO lifetime without degradation. |
| S-Band Transponder | D4F57018 | Full-duplex S-band transponder operating at 2025-2110 MHz uplink and 2200-2290 MHz downlink, providing CCSDS-compatible telecommand reception at up to 64 kbps and telemetry transmission at up to 512 kbps. Handles ranging tones for orbit determination. Implements coherent turnaround mode for two-way Doppler measurements. Interfaces with the Onboard Data Handling Subsystem via SpaceWire for TM/TC data exchange and with the RF distribution network via coaxial connectors. Power consumption approximately 15W in transmit mode. Radiation-hardened to 100 krad TID for 7-year LEO mission. |
| Solar Array Assembly | CEC51018 | Deployable solar panel wings using GaAs triple-junction photovoltaic cells for an earth observation satellite. Generates 2500W+ end-of-life orbital average power in sun-synchronous LEO orbit. Includes substrate panels, cell strings, bypass diodes, and deployment hinges. |
| Solar Array Deployment Mechanism | CED51218 | Hold-down and release mechanism for two deployable solar array wings on a LEO Earth observation satellite. Each wing is a 3-panel fold-out configuration using spring-driven hinges with viscous dampers for controlled deployment. Hold-down uses Frangibolt actuators (redundant pair per wing) rated at 22 kN. Deployment sequence initiated by OBDH command, completes within 120 seconds. Must survive launch vibration without premature release (positive margin against 3-sigma random vibe). Includes deployment status micro-switches for telemetry confirmation. Total mechanism mass per wing: 4.5 kg. |
| Solar Array Drive Mechanism | DFF71208 | Single-axis rotary drive mechanism that orients solar array wings toward the Sun to maximise power generation on an earth observation satellite. Includes stepper motor, harmonic drive gearbox, slip ring assembly for power transfer, and angular position encoder. Must operate continuously for 7+ years in LEO thermal cycling environment. |
| SpaceWire Network Router | D4E57018 | High-speed data network router for an Earth observation satellite onboard data handling subsystem. Provides deterministic packet routing between onboard computer, payload instruments, attitude sensors, and telemetry subsystem via SpaceWire protocol. Supports time-code distribution for synchronisation. |
| Spectral Filter Mechanism | D6951008 | Electromechanical filter selection mechanism for Earth observation satellite multispectral imager. Contains dichroic beam splitters and bandpass filters to separate incoming radiation into discrete spectral channels. Stepper motor driven filter wheel with position encoding. |
| Star Tracker Assembly | D5F73218 | Optical star tracker sensor unit within an Earth observation satellite AOCS. Uses CCD or CMOS detector to image star fields, performs on-chip star pattern matching against an onboard catalogue, and outputs inertial attitude quaternions at 10 Hz with arcsecond-class accuracy. Operates autonomously after initial acquisition. |
| Structure and Mechanisms Subsystem | CE851018 | Primary load-bearing and deployment subsystem for a 2000 kg-class LEO Earth observation satellite in sun-synchronous orbit at 700 km altitude. Comprises the central bus structure (honeycomb aluminium panels forming a box configuration), solar array deployment and hold-down mechanisms, X-band high-gain antenna deployment boom and gimbal mount, launch vehicle adapter ring (1194 mm diameter compatible with Vega-C or Falcon 9 ESPA), and the satellite separation system. Must withstand quasi-static launch loads of 8g axial and 3g lateral, acoustic environment up to 140 dB OASPL, and provide mounting interfaces for all subsystem equipment with thermal and electrical isolation where required. First natural frequency above 25 Hz axial and 10 Hz lateral. |
| Telemetry Tracking and Command Subsystem | 54E57018 | Satellite communication subsystem for ground segment link, including S-band transponders for telemetry and command, X-band transmitter for high-rate payload data downlink, antennas, and RF switching network. |
| Telescope Assembly | CE851018 | Primary and secondary mirror assembly with focal optics for an Earth observation satellite. Collects and focuses incoming electromagnetic radiation onto the focal plane detector array. Korsch three-mirror anastigmat design providing wide field of view with minimal optical aberration. |
| Thermal Control Subsystem | 51D71208 | Satellite thermal management subsystem using passive techniques (multilayer insulation, radiators, heat pipes, thermal coatings) and active heaters to maintain all components within operational temperature limits through extreme orbital thermal cycling between sunlit and eclipse phases. |
| Thermostatically Controlled Heater System | 55F73008 | Distributed heater system with 48 Kapton-film heaters (2W to 20W each) and 96 platinum resistance temperature sensors (Pt1000). Managed by a dedicated heater controller unit with 32 thermostat channels providing proportional-integral control. Total survival heater power budget: 180W during eclipse. Protects batteries (>0°C), propellant lines (>5°C), and star trackers (>-30°C) during eclipse and safe-mode. Autonomous operation independent of OBC for survival heaters. |
| Thruster Assembly | D6C53018 | Four 1N monopropellant hydrazine thrusters (Shell 401 catalyst) for orbit maintenance and deorbit of a 2000 kg LEO Earth observation satellite. Two redundant pairs mounted on the anti-velocity face, canted 10 degrees off-axis to balance thrust torques. Each thruster provides 0.9-1.1N thrust over the blowdown pressure range (22-5.5 bar), specific impulse 220s nominal. Minimum impulse bit 50 mN-s for fine orbit adjust. Catalyst bed heaters (redundant, 10W each) maintain bed temperature above 150C. Valve response time <20ms. Qualified for 50000 pulses and 10 hours cumulative firing. |
| X-Band High-Gain Antenna | DEC51018 | Steerable X-band parabolic reflector antenna with 0.5m aperture diameter providing 34 dBi gain at 8.2 GHz for high-rate payload data downlink. Two-axis gimbal mechanism allows ±90 degree steering to track ground stations during LEO passes. Pointing accuracy better than 0.3 degrees. Right-hand circular polarisation with axial ratio below 1.5 dB. Connected to the X-Band Transmitter via waveguide. Gimbal motors and angle encoders interface with the Onboard Data Handling Subsystem for antenna pointing control during ground station passes. Mass approximately 8 kg including gimbal. |
| X-Band Transmitter | D4E55018 | High-power X-band transmitter operating at 8.025-8.4 GHz for payload data downlink. Supports selectable data rates from 150 Mbps to 800 Mbps using OQPSK modulation with CCSDS convolutional and Reed-Solomon coding. Output RF power of 8W at antenna port. Accepts formatted CCSDS transfer frames from the Baseband Data Processor via parallel LVDS interface. Includes solid-state power amplifier (SSPA), upconverter, and local oscillator. Power consumption 45W nominal. Designed for LEO Earth observation missions with typical ground station pass durations of 8-12 minutes. |
| Component | Belongs To |
|---|---|
| Optical Payload Subsystem | Earth Observation Satellite |
| Attitude and Orbit Control Subsystem | Earth Observation Satellite |
| Electrical Power Subsystem | Earth Observation Satellite |
| Telemetry Tracking and Command Subsystem | Earth Observation Satellite |
| Onboard Data Handling Subsystem | Earth Observation Satellite |
| Thermal Control Subsystem | Earth Observation Satellite |
| Telescope Assembly | Optical Payload Subsystem |
| Focal Plane Array | Optical Payload Subsystem |
| Image Processing Unit | Optical Payload Subsystem |
| Spectral Filter Mechanism | Optical Payload Subsystem |
| Calibration System | Optical Payload Subsystem |
| Star Tracker Assembly | Attitude and Orbit Control Subsystem |
| Reaction Wheel Assembly | Attitude and Orbit Control Subsystem |
| Magnetorquer System | Attitude and Orbit Control Subsystem |
| GNSS Receiver | Attitude and Orbit Control Subsystem |
| AOCS Flight Software | Attitude and Orbit Control Subsystem |
| Solar Array Assembly | Electrical Power Subsystem |
| Battery Assembly | Electrical Power Subsystem |
| Power Control and Distribution Unit | Electrical Power Subsystem |
| Solar Array Drive Mechanism | Electrical Power Subsystem |
| Power Management Software | Electrical Power Subsystem |
| Onboard Computer | Onboard Data Handling Subsystem |
| Mass Memory Unit | Onboard Data Handling Subsystem |
| SpaceWire Network Router | Onboard Data Handling Subsystem |
| Remote Terminal Unit | Onboard Data Handling Subsystem |
| Onboard Data Handling Software | Onboard Data Handling Subsystem |
| S-Band Transponder | Telemetry Tracking and Command Subsystem |
| X-Band Transmitter | Telemetry Tracking and Command Subsystem |
| S-Band Antenna Assembly | Telemetry Tracking and Command Subsystem |
| X-Band High-Gain Antenna | Telemetry Tracking and Command Subsystem |
| Baseband Data Processor | Telemetry Tracking and Command Subsystem |
| Pulse-Tube Cryocooler | Thermal Control Subsystem |
| Multi-Layer Insulation Blankets | Thermal Control Subsystem |
| Optical Solar Reflector Radiator Panels | Thermal Control Subsystem |
| Heat Pipe Network | Thermal Control Subsystem |
| Thermostatically Controlled Heater System | Thermal Control Subsystem |
| Deployable Cryocooler Radiator | Thermal Control Subsystem |
| Structure and Mechanisms Subsystem | Earth Observation Satellite |
| Primary Structure | Structure and Mechanisms Subsystem |
| Solar Array Deployment Mechanism | Structure and Mechanisms Subsystem |
| Launch Vehicle Adapter | Structure and Mechanisms Subsystem |
| Antenna Deployment Boom | Structure and Mechanisms Subsystem |
| Harness Assembly | Structure and Mechanisms Subsystem |
| Thruster Assembly | Propulsion Subsystem |
| Propellant Tank | Propulsion Subsystem |
| Propellant Management Assembly | Propulsion Subsystem |
| From | To |
|---|---|
| Telescope Assembly | Spectral Filter Mechanism |
| Spectral Filter Mechanism | Focal Plane Array |
| Focal Plane Array | Image Processing Unit |
| Calibration System | Focal Plane Array |
| Star Tracker Assembly | AOCS Flight Software |
| GNSS Receiver | AOCS Flight Software |
| AOCS Flight Software | Reaction Wheel Assembly |
| AOCS Flight Software | Magnetorquer System |
| Solar Array Assembly | Power Control and Distribution Unit |
| Battery Assembly | Power Control and Distribution Unit |
| Power Management Software | Power Control and Distribution Unit |
| Power Management Software | Solar Array Drive Mechanism |
| Onboard Computer | SpaceWire Network Router |
| Onboard Computer | Mass Memory Unit |
| SpaceWire Network Router | Remote Terminal Unit |
| Onboard Data Handling Software | Onboard Computer |
| SpaceWire Network Router | Mass Memory Unit |
| S-Band Antenna Assembly | S-Band Transponder |
| S-Band Transponder | Baseband Data Processor |
| Baseband Data Processor | X-Band Transmitter |
| X-Band Transmitter | X-Band High-Gain Antenna |
| Baseband Data Processor | Mass Memory Unit |
| Baseband Data Processor | Onboard Computer |
| S-Band Transponder | Onboard Computer |
| X-Band High-Gain Antenna | Onboard Computer |
| Image Processing Unit | Mass Memory Unit |
| Pulse-Tube Cryocooler | Focal Plane Array |
| Pulse-Tube Cryocooler | Deployable Cryocooler Radiator |
| Heat Pipe Network | Optical Solar Reflector Radiator Panels |
| Thermostatically Controlled Heater System | Power Control and Distribution Unit |
| Launch Vehicle Adapter | Primary Structure |
| Solar Array Deployment Mechanism | Primary Structure |
| Antenna Deployment Boom | X-Band High-Gain Antenna |
| Primary Structure | Optical Payload Subsystem |
| Harness Assembly | Power Control and Distribution Unit |
| Harness Assembly | SpaceWire Network Router |
| Propellant Tank | Propellant Management Assembly |
| Propellant Management Assembly | Thruster Assembly |
| Thruster Assembly | Primary Structure |
| Propellant Tank | Primary Structure |
| Thruster Assembly | AOCS Flight Software |
| Propellant Management Assembly | Remote Terminal Unit |
| Solar Array Assembly | Solar Array Deployment Mechanism |
| Solar Array Assembly | Solar Array Drive Mechanism |
| Component | Output |
|---|---|
| Telescope Assembly | focused optical beam |
| Focal Plane Array | raw digital image data |
| Image Processing Unit | compressed CCSDS image packets |
| Spectral Filter Mechanism | spectrally filtered radiation |
| Calibration System | radiometric calibration reference |
| Star Tracker Assembly | inertial attitude quaternions |
| Reaction Wheel Assembly | three-axis control torque |
| Magnetorquer System | magnetic desaturation torque |
| GNSS Receiver | orbit position-velocity-time solution |
| AOCS Flight Software | actuator command profiles |
| Solar Array Assembly | unregulated DC power from photovoltaic conversion |
| Battery Assembly | regulated eclipse power and transient load buffering |
| Power Control and Distribution Unit | 28V regulated bus power and load switching commands |
| Solar Array Drive Mechanism | optimal solar array sun-pointing orientation |
| Power Management Software | charge control commands and load shedding decisions |
| Onboard Computer | command execution and telemetry formatting |
| Mass Memory Unit | stored payload and housekeeping data for downlink |
| SpaceWire Network Router | deterministic packet routing and time-code distribution |
| Remote Terminal Unit | digitised sensor telemetry and discrete actuator commands |
| Onboard Data Handling Software | FDIR decisions, operations schedules, and command validation |
| S-Band Transponder | CCSDS telecommand packets and ranging turnaround signals |
| X-Band Transmitter | modulated X-band RF carrier for payload data downlink |
| S-Band Antenna Assembly | omnidirectional S-band RF coverage for TM/TC |
| X-Band High-Gain Antenna | high-gain directed X-band beam for payload downlink |
| Baseband Data Processor | FEC-encoded CCSDS transfer frames and modulation baseband |
| Telescope Assembly | diffraction-limited image at focal plane |
| Focal Plane Array | raw multi-spectral pushbroom pixel data at 2.4 Gbps |
| Spectral Filter Mechanism | spectrally separated VNIR and SWIR optical channels |
| Image Processing Unit | radiometrically corrected compressed image segments |
| Calibration System | calibration reference illumination and dark frames |
| Pulse-Tube Cryocooler | 150K cold-tip temperature for SWIR detector cooling |
| Multi-Layer Insulation Blankets | passive thermal isolation from external environment |
| Optical Solar Reflector Radiator Panels | passive heat rejection of 600W bus electronics dissipation |
| Heat Pipe Network | isothermal equipment panel temperature distribution |
| Thermostatically Controlled Heater System | survival and operational temperature maintenance during eclipse |
| Deployable Cryocooler Radiator | 100W cryocooler waste heat rejection at -40C |
| Primary Structure | structural load path from all equipment to launch vehicle interface |
| Solar Array Deployment Mechanism | deployed solar array wings in operational configuration |
| Launch Vehicle Adapter | mechanical and electrical interface to launch vehicle |
| Antenna Deployment Boom | deployed antenna platform with required stiffness and alignment |
| Harness Assembly | electrical power and signal interconnection between all subsystems |
| Thruster Assembly | thrust for orbit maintenance and deorbit manoeuvres |
| Propellant Tank | pressurised hydrazine propellant supply to thrusters |
| Propellant Management Assembly | regulated propellant flow and system health telemetry |
| Solar Array Assembly | raw photovoltaic electrical power at 60-100V DC |
| Source | Target | Type | Description |
|---|---|---|---|
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | IFC-INTERFACEDEFINITIONS-028 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | IFC-INTERFACEDEFINITIONS-030 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | IFC-INTERFACEDEFINITIONS-029 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | IFC-INTERFACEDEFINITIONS-001 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-002 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-003 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | IFC-INTERFACEDEFINITIONS-005 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-008 | IFC-INTERFACEDEFINITIONS-006 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | IFC-INTERFACEDEFINITIONS-007 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | IFC-INTERFACEDEFINITIONS-008 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | IFC-INTERFACEDEFINITIONS-009 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | IFC-INTERFACEDEFINITIONS-010 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-010 | IFC-INTERFACEDEFINITIONS-011 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | IFC-INTERFACEDEFINITIONS-012 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | IFC-INTERFACEDEFINITIONS-013 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-016 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-017 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-018 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | IFC-INTERFACEDEFINITIONS-014 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | IFC-INTERFACEDEFINITIONS-015 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | IFC-INTERFACEDEFINITIONS-019 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | IFC-INTERFACEDEFINITIONS-020 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | IFC-INTERFACEDEFINITIONS-021 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | IFC-INTERFACEDEFINITIONS-022 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | IFC-INTERFACEDEFINITIONS-023 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | IFC-INTERFACEDEFINITIONS-024 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | IFC-INTERFACEDEFINITIONS-001 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | IFC-INTERFACEDEFINITIONS-002 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | IFC-INTERFACEDEFINITIONS-003 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | IFC-INTERFACEDEFINITIONS-004 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | IFC-INTERFACEDEFINITIONS-005 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | IFC-INTERFACEDEFINITIONS-006 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | IFC-INTERFACEDEFINITIONS-007 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | IFC-INTERFACEDEFINITIONS-008 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | IFC-INTERFACEDEFINITIONS-009 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | IFC-INTERFACEDEFINITIONS-010 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | IFC-INTERFACEDEFINITIONS-011 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | IFC-INTERFACEDEFINITIONS-012 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | IFC-INTERFACEDEFINITIONS-013 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-014 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-015 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-016 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-017 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-018 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-019 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | IFC-INTERFACEDEFINITIONS-020 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | IFC-INTERFACEDEFINITIONS-025 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | IFC-INTERFACEDEFINITIONS-026 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | IFC-INTERFACEDEFINITIONS-027 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-001 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-013 | SUB-SUBSYSTEMREQUIREMENTS-055 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-013 | SUB-SUBSYSTEMREQUIREMENTS-054 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | SUB-SUBSYSTEMREQUIREMENTS-066 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | SUB-SUBSYSTEMREQUIREMENTS-065 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | SUB-SUBSYSTEMREQUIREMENTS-064 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | SUB-SUBSYSTEMREQUIREMENTS-063 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | SUB-SUBSYSTEMREQUIREMENTS-062 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-015 | SUB-SUBSYSTEMREQUIREMENTS-061 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-060 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-059 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-058 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-057 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-056 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-055 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-014 | SUB-SUBSYSTEMREQUIREMENTS-054 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-033 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-031 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-029 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-028 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | SUB-SUBSYSTEMREQUIREMENTS-032 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | SUB-SUBSYSTEMREQUIREMENTS-034 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | SUB-SUBSYSTEMREQUIREMENTS-038 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-012 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-011 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-006 | SUB-SUBSYSTEMREQUIREMENTS-013 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-045 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-044 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-043 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-042 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-041 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-040 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-039 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-038 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-037 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-036 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-035 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-034 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-027 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-010 | SUB-SUBSYSTEMREQUIREMENTS-026 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | SUB-SUBSYSTEMREQUIREMENTS-015 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | SUB-SUBSYSTEMREQUIREMENTS-030 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-025 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-024 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-023 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-022 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-021 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-020 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-019 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-018 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-008 | SUB-SUBSYSTEMREQUIREMENTS-016 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-014 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-010 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-009 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-008 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-007 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-006 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-005 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-004 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-003 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-002 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-001 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-002 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-001 | SUB-SUBSYSTEMREQUIREMENTS-006 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-002 | SUB-SUBSYSTEMREQUIREMENTS-001 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-002 | SUB-SUBSYSTEMREQUIREMENTS-009 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-004 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-005 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-010 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-008 | SUB-SUBSYSTEMREQUIREMENTS-011 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-008 | SUB-SUBSYSTEMREQUIREMENTS-012 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-006 | SUB-SUBSYSTEMREQUIREMENTS-013 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-014 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | SUB-SUBSYSTEMREQUIREMENTS-015 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-008 | SUB-SUBSYSTEMREQUIREMENTS-016 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-007 | SUB-SUBSYSTEMREQUIREMENTS-017 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-018 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-019 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-020 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-021 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-022 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-023 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-024 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-004 | SUB-SUBSYSTEMREQUIREMENTS-025 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-010 | SUB-SUBSYSTEMREQUIREMENTS-026 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-027 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | SUB-SUBSYSTEMREQUIREMENTS-030 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-012 | SUB-SUBSYSTEMREQUIREMENTS-029 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-010 | SUB-SUBSYSTEMREQUIREMENTS-027 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-005 | SUB-SUBSYSTEMREQUIREMENTS-032 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-034 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-036 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-038 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-039 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-040 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-003 | SUB-SUBSYSTEMREQUIREMENTS-043 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | SUB-SUBSYSTEMREQUIREMENTS-035 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | SUB-SUBSYSTEMREQUIREMENTS-044 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-009 | SUB-SUBSYSTEMREQUIREMENTS-045 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-046 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-047 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-048 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-049 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-050 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-051 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-052 | derives | |
| SYS-SYSTEM-LEVELREQUIREMENTS-011 | SUB-SUBSYSTEMREQUIREMENTS-053 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-013 | derives | |
| STK-STAKEHOLDERNEEDS-004 | SYS-SYSTEM-LEVELREQUIREMENTS-015 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-014 | derives | |
| STK-STAKEHOLDERNEEDS-001 | SYS-SYSTEM-LEVELREQUIREMENTS-001 | derives | |
| STK-STAKEHOLDERNEEDS-007 | SYS-SYSTEM-LEVELREQUIREMENTS-010 | derives | |
| STK-STAKEHOLDERNEEDS-007 | SYS-SYSTEM-LEVELREQUIREMENTS-005 | derives | |
| STK-STAKEHOLDERNEEDS-006 | SYS-SYSTEM-LEVELREQUIREMENTS-009 | derives | |
| STK-STAKEHOLDERNEEDS-006 | SYS-SYSTEM-LEVELREQUIREMENTS-003 | derives | |
| STK-STAKEHOLDERNEEDS-005 | SYS-SYSTEM-LEVELREQUIREMENTS-008 | derives | |
| STK-STAKEHOLDERNEEDS-005 | SYS-SYSTEM-LEVELREQUIREMENTS-007 | derives | |
| STK-STAKEHOLDERNEEDS-004 | SYS-SYSTEM-LEVELREQUIREMENTS-006 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-011 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-006 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-004 | derives | |
| STK-STAKEHOLDERNEEDS-002 | SYS-SYSTEM-LEVELREQUIREMENTS-009 | derives | |
| STK-STAKEHOLDERNEEDS-002 | SYS-SYSTEM-LEVELREQUIREMENTS-003 | derives | |
| STK-STAKEHOLDERNEEDS-001 | SYS-SYSTEM-LEVELREQUIREMENTS-002 | derives | |
| STK-STAKEHOLDERNEEDS-001 | SYS-SYSTEM-LEVELREQUIREMENTS-001 | derives | |
| STK-STAKEHOLDERNEEDS-002 | SYS-SYSTEM-LEVELREQUIREMENTS-012 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-011 | derives | |
| STK-STAKEHOLDERNEEDS-007 | SYS-SYSTEM-LEVELREQUIREMENTS-010 | derives | |
| STK-STAKEHOLDERNEEDS-006 | SYS-SYSTEM-LEVELREQUIREMENTS-009 | derives | |
| STK-STAKEHOLDERNEEDS-005 | SYS-SYSTEM-LEVELREQUIREMENTS-008 | derives | |
| STK-STAKEHOLDERNEEDS-005 | SYS-SYSTEM-LEVELREQUIREMENTS-007 | derives | |
| STK-STAKEHOLDERNEEDS-004 | SYS-SYSTEM-LEVELREQUIREMENTS-006 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-005 | derives | |
| STK-STAKEHOLDERNEEDS-003 | SYS-SYSTEM-LEVELREQUIREMENTS-004 | derives | |
| STK-STAKEHOLDERNEEDS-002 | SYS-SYSTEM-LEVELREQUIREMENTS-003 | derives | |
| STK-STAKEHOLDERNEEDS-001 | SYS-SYSTEM-LEVELREQUIREMENTS-002 | derives | |
| STK-STAKEHOLDERNEEDS-001 | SYS-SYSTEM-LEVELREQUIREMENTS-001 | derives |
| Requirement | Verified By | Type | Description |
|---|---|---|---|
| IFC-INTERFACEDEFINITIONS-018 | VER-VERIFICATIONMETHODS-020 | verifies | |
| IFC-INTERFACEDEFINITIONS-008 | VER-VERIFICATIONMETHODS-010 | verifies | |
| IFC-INTERFACEDEFINITIONS-018 | VER-VERIFICATIONMETHODS-020 | verifies | |
| IFC-INTERFACEDEFINITIONS-011 | VER-VERIFICATIONMETHODS-011 | verifies | |
| IFC-INTERFACEDEFINITIONS-008 | VER-VERIFICATIONMETHODS-010 | verifies | |
| IFC-INTERFACEDEFINITIONS-001 | VER-VERIFICATIONMETHODS-001 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-056 | VER-VERIFICATIONMETHODS-026 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-065 | VER-VERIFICATIONMETHODS-028 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-061 | VER-VERIFICATIONMETHODS-027 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-001 | VER-VERIFICATIONMETHODS-001 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-002 | VER-VERIFICATIONMETHODS-002 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-004 | VER-VERIFICATIONMETHODS-003 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-008 | VER-VERIFICATIONMETHODS-004 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-010 | VER-VERIFICATIONMETHODS-005 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-016 | VER-VERIFICATIONMETHODS-006 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-015 | VER-VERIFICATIONMETHODS-007 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-018 | VER-VERIFICATIONMETHODS-008 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-022 | VER-VERIFICATIONMETHODS-009 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-026 | VER-VERIFICATIONMETHODS-011 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-027 | VER-VERIFICATIONMETHODS-012 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-030 | VER-VERIFICATIONMETHODS-013 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-034 | VER-VERIFICATIONMETHODS-014 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-036 | VER-VERIFICATIONMETHODS-015 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-038 | VER-VERIFICATIONMETHODS-016 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-039 | VER-VERIFICATIONMETHODS-016 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-040 | VER-VERIFICATIONMETHODS-017 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-041 | VER-VERIFICATIONMETHODS-017 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-042 | VER-VERIFICATIONMETHODS-018 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-044 | VER-VERIFICATIONMETHODS-019 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-037 | VER-VERIFICATIONMETHODS-015 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-043 | VER-VERIFICATIONMETHODS-016 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-045 | VER-VERIFICATIONMETHODS-014 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-001 | VER-VERIFICATIONMETHODS-001 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-002 | VER-VERIFICATIONMETHODS-002 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-004 | VER-VERIFICATIONMETHODS-003 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-008 | VER-VERIFICATIONMETHODS-004 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-010 | VER-VERIFICATIONMETHODS-005 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-016 | VER-VERIFICATIONMETHODS-006 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-015 | VER-VERIFICATIONMETHODS-007 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-018 | VER-VERIFICATIONMETHODS-008 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-022 | VER-VERIFICATIONMETHODS-009 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-026 | VER-VERIFICATIONMETHODS-011 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-027 | VER-VERIFICATIONMETHODS-012 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-030 | VER-VERIFICATIONMETHODS-013 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-034 | VER-VERIFICATIONMETHODS-014 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-036 | VER-VERIFICATIONMETHODS-015 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-038 | VER-VERIFICATIONMETHODS-016 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-040 | VER-VERIFICATIONMETHODS-017 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-042 | VER-VERIFICATIONMETHODS-018 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-044 | VER-VERIFICATIONMETHODS-019 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-046 | VER-VERIFICATIONMETHODS-021 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-047 | VER-VERIFICATIONMETHODS-022 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-048 | VER-VERIFICATIONMETHODS-023 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-054 | VER-VERIFICATIONMETHODS-024 | verifies | |
| SUB-SUBSYSTEMREQUIREMENTS-055 | VER-VERIFICATIONMETHODS-025 | verifies |