| 4.4.5-6-1 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.
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NA
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NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Mission Assurance Guide, TOR-2007(8546)-6018, Rev B
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| 4.4.5-6-2 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
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NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Mission Assurance Guide, TOR-2007(8546)-6018, Rev B
|
| 4.4.5-6-3 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; Electrical Power Systems for Unmanned Spacecraft, AIAA S-122-2007
|
| 4.4.5-6-4 Ensure adequacy of solar array and battery sizing analyses, given a baseline load and battery charging profile, including applicable source contingency and load margins required |
Phase B |
Phase C |
Phase D1 |
|
Ensure an accurate Day In The Life power balance analysis is performed and the load power is updated on a regular basis. Ensure analyses completed by PDR, updated at CDR and includes thermal structural stress analysis for cell to substrate, interconnects, radiation and ESD effects and mechanical and thermal induced environmental stresses, as examples of required efforts.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Electrical Power Systems for Unmanned Spacecraft, AIAA S-122-2007
|
| 4.4.5-6-5 Ensure system has been adequately analyzed to show that fusing scheme is robust, sized properly, and protects against failure propagation |
Phase B |
Phase C |
Phase D1 |
|
Ensure sufficient fuse blow capability to isolate failed or shorted component in sufficient time to keep bus in regulation. Ensure the complete load current path is evaluated - wiring, fuse, FET, PCB traces, etc. Ensure adequacy of fault clearing and fuse sizing analyses.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Design Advisory DA-2014-01; Electrical Power Systems for Unmanned Spacecraft, AIAA S-122-2007
|
| 4.4.5-6-6 Ensure results of radiation analysis are delineated and show that units meet requirement |
Phase B |
Phase C |
|
Ensure that the radiation Hardness Assurance Plan requirements are flowed down to the power subsystem. Worst Case circuit analysis should include changes in electrical components due to radiation exposure - gain reduction, drift, value change, etc.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.5-6-7 Ensure energy balance for all mission phases has been adequately assessed |
Phase B |
Phase C |
Phase D1 |
|
Ensure Final Energy Balance Analyses for All Design Reference Cases Using Heater Power Levels from Thermal Balance Test, as Well as Final Measured Unit Power Consumptions. Ensure that the allocation of margin is accurate for the hardware design phase - paper design, PDU, CDR, Systems test. Also, the modeling of Li Ion charge and discharge characteristics is critical (they are different than for NiH2).
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Electrical Power Systems for Unmanned Spacecraft, AIAA S-122-2007
|
| 4.4.5-6-8 Ensure Adequacy of Power regulation simulation/analysis results, or description of where testing will be done |
Phase B |
Phase C |
Phase D1 |
|
Ensure analysis is checked or independent analysis is performed. Ensure that the unit level testing supports the analysis.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.5-6-9 Ensure a Preliminary FMEA at component and subsystem levels, with final by CDR |
Phase B |
Phase C |
|
Ensure summary and detailed report (for PDR, present what has been completed, or indicate a due date when the item will be completed).
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.5-6-10 Ensure power bus quality analyses, completed by PDR, updated by CDR |
Phase B |
Phase C |
Phase D1 |
|
Ensure summary and detailed report (for PDR, present what has been completed, or indicate a due date when the item will be completed).
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Electrical Power Systems for Unmanned Spacecraft, AIAA S-122-2007
|
| 4.4.5-6-11 Ensure adequacy of stress derating-electrical and thermal structural analyses |
Phase B |
Phase C |
|
Provide summary of, and detailed report (for PDR, present what has been completed, or indicate a due date when the item will be completed).
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.5-6-12 Ensure adequacy of power budget and energy balance analyses for orbital scenarios (design reference cases) |
Phase B |
Phase C |
Phase D1 |
|
Ensure these are updated and trended throughout the Program Development Phase. include Worst-Case Performance for Normal Operations at BOL and EOL, as well as transfer Orbit, Station keeping, Disposal, and Any Other Distinct Modes of Operation of the EPDS.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; Electrical Power Systems for Unmanned Spacecraft, AIAA S-122-2007
|
| 4.4.5-6-13 Ensure adequacy of shadow analysis (other appendages casting shadow onto the solar array) |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.5-6-14 Ensure power buses transient response and stability analysis and testing performed |
Phase B |
Phase C |
Phase D1 |
|
Ensure that EPDS satisfies bus stability and transient response (normal step loads and fault-clearing) requirements. Ensure EPDS testing includes measurement of stability and transient response in all operating modes over range of loading conditions.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|