| 4.4.6-6-1 Ensure reliability engineering analyses demonstrate design life and mean mission duration requirements are satisfied |
Phase B |
Phase C |
Phase D1 |
|
Ensure worst-case analyses, component stress levels, failure mode and effects critical analysis and reliability analyses support mission life. Ensure independent risk assessment performed of all identified single point failures. Evaluate electrical and mechanical worst case design for boxes/components. Ensure preliminary results reported at Preliminary Design Review, and updated/final results reported at Critical Design Review.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Mission Assurance Guide, TOR-2007(8546)-6018, Rev B
|
| 4.4.6-6-2 Ensure subsystem specific analyses demonstrate that design requirements are satisfied |
Phase B |
Phase C |
Phase D1 |
|
Ensure performance of design reference cases (demonstrations that system will perform to specification in a worst case scenario for the space system).
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Mission Assurance Guide, TOR-2007(8546)-6018, Rev B
|
| 4.4.6-6-3 Ensure independent modeling and simulation applicable to the subsystem design are performed |
Phase A |
Phase B |
Phase C |
Phase D1 |
|
Ensure areas of design and/or operational risk in the subsystem are identified which would benefit from an independent analysis or simulations to validate contractor predictions and tradeoffs. Examples are circuit analysis, thermal, coupled loads analysis.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Mission Assurance Guide, TOR-2007(8546)-6018, Rev B
|
| 4.4.6-6-4 Ensure thermal models used to predict temperatures within electronic boxes are adequate and complete |
Phase B |
Phase C |
|
Ensure thermal growth capability is adequate. Ensure worst case assumptions are used.
|
NA
|
NA
|
Spacecraft Thermal Control Handbook
|