| 4.4.8-10-1 Ensure all units and components have met their requirements and verification evidences are documented |
Phase B |
Phase C |
Phase D1 |
|
Ensure reworked units are tested in accordance with applicable specifications and standards. Ensure verification progress is tracked using the verification ledger/matrix.
|
NA
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End Item Data Package (EIDP)
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
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| 4.4.8-10-2 Ensure subsystem has met all of its requirements and evidences are documented |
Phase D1 |
|
Ensure that unit-to-bus system level testing verifies performance at temperatures and other environmental extremes at all levels of testing. Ensure that unit level testing stresses the unit as built to reveal issues at the lowest level of build and test. Ensure verification progress is tracked using the verification ledger/matrix.
|
NA
|
NA
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Space Vehicle Test and Evaluation Handbook, TOR-2011(8591)-2
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| 4.4.8-10-3 Ensure hardware and software requirement buy-offs are completed as appropriate for subsystem |
Phase D1 |
|
Ensure requirements are verified to the lowest level. Ensure any exceptions are addressed prior to approval. Ensure all requirement buy-off packages are documented. For propulsion systems where end-to-end flight-like testing cannot be performed, ensure the impact of approved unit or subsystem deviations have been evaluated.
|
NA
|
End Item Data Package (EIDP)
|
Space Vehicle Test and Evaluation Handbook, TOR-2011(8591)-2
|
| 4.4.8-10-4 Ensure all subsystem development anomalies and failures are documented and dispositioned in accordance to approved processes |
Phase D1 |
|
Ensure that all components related to the anomaly are evaluated for overstress, including Acceptance Data Packages, Qualification Test Reports and raw test data when available. Ensure that any cross-program systemic issue is submitted to problem alerting processes.
|
NA
|
NA
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Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, ITE chapter.
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| 4.4.8-10-5 Ensure review of all verification and corrective action data for all developed hardware and software |
Phase D1 |
|
Ensure all stakeholders review all test data and discrepancy documentation and have an opportunity to provide comments and recommendations for corrective action.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Mission Assurance Guide, TOR-2007(8546)-6018, Rev B
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| 4.4.8-10-6 Ensure that system recovery and failure modes perform as anticipated |
Phase D1 |
|
Ensure baseline, thermal-vacuum and factory acceptance testing of subsystem includes entry into, and successful exit from, safe-modes. Ensure results of testing are analyzed for expected subsystem responses.
|
NA
|
NA
|
Space Vehicle Test and Evaluation Handbook, TOR-2011(8591)-2
|
| 4.4.8-10-7 Ensure thruster test results match predicted performance |
Phase B |
Phase C |
Phase D1 |
|
An example for chemical systems is specific impulse versus pressure. Ensure that ground acceptance test data for flight units match the qualification unit behavior. Example 2: Ensure that thermal conditions for flight units (e.g. heat shields) were represented in tests
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.8-10-8 Ensure appropriate propellant leak tests were performed properly |
Phase B |
Phase C |
Phase D1 |
|
Leak tests are appropriate at the unit, subsystem, and system level for any unit or system type that relies upon an internal fluid or pressure. The specific type of test varies according to application with guidance provided in ATR-2015-01994.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Design and Test Requirements for Space Flight Pressurized Systems, TR-RS-2015-00005; Application Guidelines for Pressure Components, Pressure Systems, Leak and Pressure Test Requirements in TR-RS-2014-00016, ATR-2015-01994
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| 4.4.8-10-9 Ensure appropriate life testing for high cycle components |
Phase B |
Phase C |
Phase D1 |
|
High cycle components include: valve electrical and mechanical components, catalyst beds, etc.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.8-10-10 Ensure thermal vacuum or thermal balance test data for component temperatures and heater usage are evaluated |
Phase B |
Phase C |
Phase D1 |
|
A thermal model of the propulsion system is required as TVAC and other tests do not fully simulate flight conditions. This model should be correlated to the thermal tests.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|