| 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 |