| 4.4.4.5-10-1 Ensure each Moving Mechanical Assembly (MMA) design was subjected to a qualification test |
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Ensure each MMA qualification unit is produced with production equipment and procedures, subjected to environmental qualification levels to verify satisfactory performance, and tested in launch or on-orbit configuration corresponding to environment being simulated.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-2 Ensure qualification test program includes required performance measurements |
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Phase C |
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Ensure quantitative measurements (e.g. torque-vs.-theta, time-vs.-theta, or equivalent linear measurements) are made during functional and environmental qualification testing. Measurements should be made under ambient and qualification level hot/cold temperatures. All performance requirements (such as force margins) should be met.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-3 Ensure high and low energy pyro performance demonstrated in qualification testing |
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Phase C |
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Ensure one-time release test conducted in fully assembled configuration using explosive charge loading of 80% to demonstrate actuation margin. Ensure one-time release test conducted in fully assembled configuration using explosive charge loading of 120% to evaluate possibility of structural damage.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-4 Ensure proper functional operation is demonstrated after qualification testing |
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Ensure functional testing is performed following all qualification tests (including life test), to demonstrate no degradation has occurred.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-5 Ensure a life test is performed during qualification to demonstrate life cycle adequacy |
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Phase C |
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Ensure life test MMA is produced with production equipment and procedures. Significant interface masses, loads, and stiffnesses should be flight-like, and thermal blankets, cabling, harnesses, hoses, etc., should be included. The test should be performed using the operational environments and motion profile, including range of travel and number of reversals.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-6 Ensure appropriate number of cycles utilized for the life test |
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Phase C |
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Ensure low-cycle MMAs (e.g. release devices, spring driven deployables) are tested for at least 2X life (ground testing + flight); 50 cycles is typical minimum test requirement. Ensure high-cycle MMAs (e.g. solar array drives, momentum wheels, tracking gimbals) are tested for at least 1.5X times life (ground testing + flight); 2X life is preferred. Accelerated test techniques must reflect on-orbit operational conditions (bearing lubrication regime, etc). Ensure stops are tested for at least 2X total duty cycles expected in operational use plus component and vehicle tests, regardless of whether or not limit switches prevent contacting stops in normal operation.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-7 Ensure adequate life of brushes and slip rings |
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Phase C |
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Ensure design verification testing of brushes and commutator or slip-ring assemblies demonstrates the lubricant is not significantly deteriorated or driven from proper areas, and that wear rates, wear debris, electrical noise level, friction torque, and lubricant loss are compatible with requirements. Tests should be conducted with representative levels of electrical current at the rated voltage across the interface.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-8 Ensure each Moving Mechanical Assembly (MMA) flight unit was subjected to an acceptance test |
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Phase C |
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Ensure each MMA flight unit is subjected to acceptance level environments to verify satisfactory performance, and tested in the launch or on-orbit configuration corresponding to the environment being simulated.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-9 Ensure acceptance test program includes required performance measurements |
Phase B |
Phase C |
Phase D1 |
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Ensure quantitative measurements (e.g. torque-vs.-theta, time-vs.-theta, or equivalent linear measurements) made during run-in, functional, and environmental acceptance testing. Measurements should be made under ambient and acceptance level hot/cold temperatures. All performance requirements (such as force margins) should be met.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-10 Ensure all swaged ends on rods or cables are 100% proof tested during acceptance |
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Phase C |
Phase D1 |
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All flight rod and cable ends should be proof tested as part of acceptance testing.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-11 Ensure run-in testing is performed during acceptance |
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Ensure run-in test performed before further acceptance testing, unless detrimental to performance and/or reliability. Test should consist of at least five cycles or 5% of total expected service life cycles, whichever is greater, unless capability to perform in a consistent and controlled manner is demonstrated with fewer cycles.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-12 Ensure functional tests are performed before and after environmental exposure during acceptance |
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Determine whether damage or degradation in performance has occurred. Functional tests should be conducted in appropriate environment to demonstrate performance (ambient is usually adequate).
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-13 Ensure first motion test was performed during vehicle level acceptance testing |
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Ensure release of all deployables using flight or flight-like devices. First motion test, where possible, should be included as part of space vehicle thermal testing to verify release at acceptance level cold/hot temperature, whichever has a larger excursion relative to ambient.
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NA
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NA
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AIAA S-114-2005
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| 4.4.4.5-10-14 Ensure critical clearance verification is performed in final flight configuration |
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Phase C |
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Ensure critical clearances are verified by a range of motion test, either assisted or autonomous. Verification should include all blankets, harnesses, and other hardware, installed in flight configuration.
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NA
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NA
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AIAA S-114-2005
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