| 4.5.4-6-1 Ensure reliability engineering analyses demonstrate design life and mean mission duration requirements are satisfied |
Phase B |
Phase C |
Phase D1 |
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Ensure worst-case analyses, component stress levels, failure mode and effects critical analysis and reliability analyses support mission life. Ensure independent risk assessment performed on 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. For RF components with minimum frequency of 5 MHz and local internal RF voltages greater than 5V peak, multifactor breakdown analysis must be included.
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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; Standard/Handbook for Radio Frequency (RF) Breakdown Prevention in Spacecraft Components (TOR-2014)-02198
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| 4.5.4-6-2 Ensure payload specific analyses demonstrate that design requirements are satisfied |
Phase B |
Phase C |
Phase D1 |
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Ensure that engineering analyses results are reviewed by technical experts and compared against appropriate verification requirements. Examples of payload-specific analyses include derating, worst case, closed loop, gain and noise budget, linearity, distortion, spurious, cavity mode and isolation, digital timing, interface compatibility, power supply ripple rejection, power supply loading, loading, current density, electrical stress, RF compliance. mechanical, thermal, PMP, reliability, fault isolation.
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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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| 4.5.4-6-3 Ensure independent modeling and simulation applicable to the payload design are performed |
Phase A |
Phase B |
Phase C |
Phase D1 |
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Ensure areas of design and/or operational risk in the payload are identified which would benefit from an independent analysis or simulations to validate contractor predictions and tradeoffs. Examples are signal degradation and analysis due to imperfect hardware components, circuit analysis, thermal, coupled loads analysis.
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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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| 4.5.4-6-4 Ensure EMI / EMC / RF susceptibility, and RF interference analyses are adequate and complete |
Phase A |
Phase B |
Phase C |
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Ensure that engineering analyses results relating to EMI/EMC/Susceptibility and RF Interference are reviewed by EMI/EMC experts and compared against appropriate verification requirements.
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NA
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NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
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| 4.5.4-6-5 Ensure ESD and radiation survivability analyses are adequate and complete |
Phase A |
Phase B |
Phase C |
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Ensure that engineering analyses results relating to Survivability are reviewed by survivability experts and compared against appropriate verification requirements. Ensure new materials and units that are exposed to space environment are analyzed and tested for space-related issues including discharge, Electrostatic Discharge (ESD) (charging) susceptibility, solar radiation (thermal) susceptibility. Ensure that the payload is adequately shielded from radiation. Ensure that sufficient analysis and test are provided to show with high confidence that the environmental risk is minimized and the payload will perform as expected at its End-of-Life (EOL) .
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NA
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NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
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| 4.5.4-6-6 Ensure all environmental analyses are adequate and complete |
Phase A |
Phase B |
Phase C |
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Ensure that analyses for all electrical stressing environments (radiation, scintillation, interference) and mechanical stressing environments (acoustic, shock, thermal, vibe, and pressure) are addressed considering appropriate margins.
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NA
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NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
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