| 4.4.6-4-1 Ensure subsystem design including units, assemblies, sub-assemblies and parts meets the mission performance requirements |
Phase A |
Phase B |
Phase C |
|
Pre-Phase A, as applicable, ensure the design satisfies the requirements under the conditions specified by the Design Reference Mission. There should be a realistic worst-case scenario to show that the requirements can be met with margin. Phase A onward, the derived CONOPS should be in a particular document (Flight Requirements and Ops documents) or operations working group products. Some mission concepts may not be directly translated to subsystem requirements in terms of the overall mission operability. The subsystem must be validated against how the components will be used for that particular application.
|
NA
|
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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| 4.4.6-4-2 Ensure trade studies were conducted and the design baseline satisfies mission requirements and the analysis of alternatives has identified the baseline as the best value |
Phase A |
Phase B |
Phase C |
|
Ensure that all trade studies are realizable in terms of technology used and conform to system requirement and physical constraints. Check that viable candidates received appropriate consideration.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-3 Ensure subsystem technology readiness and risk burn-down plan have been assessed |
Phase A |
Phase B |
Phase C |
|
Ensure subsystem technologies, including manufacturing, supplier readiness and programmatic readiness, are mature enough to support the development timeline. Check that the risk mitigation plans are sufficient, funded and conclude at the right time.
|
NA
|
NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-4 Ensure subsystem hardware and software (as applicable) functions are described in the subsystem specification |
Phase A |
Phase B |
Phase C |
|
Ensure that descriptive functions for subsystems and units (including software) are detailed enough for new personnel to understand how the unit or subsystem behaves both individually and within the system.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-5 Ensure subsystem hardware and software (as applicable) is identified as heritage, modified, or new |
Phase B |
Phase C |
|
Ensure heritage qualification adequacy is documented by analysis and test.
|
NA
|
NA
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Objective Criteria for Heritage Hardware Reuse, TOR-2010(8591)-19; Reuse of Hardware and Software Products, TOR-2009(8546)-8604
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| 4.4.6-4-6 Ensure all defined contract deliverables and relevant contractor data are complete and accurate to support design reviews |
Phase A |
Phase B |
Phase C |
|
Ensure all relevant data is readily available and delivered to support design reviews and design forums.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-7 Ensure EMC requirements are addressed and a control plan is generated |
Phase B |
Phase C |
|
Ensure that MA EMC spec are flowed down and that the EMC control plan is generated for the TCS subsystem with emphasis on EMC design and verification at the lowest level of build. Ensure EMC issues are identified and have appropriate mitigation plans.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-8 Ensure that adequate thermal uncertainty margins are demonstrated between thermal model predictions and acceptance limits |
Phase B |
Phase C |
|
This provides confidence that flight temperatures will be within model predictions.
|
NA
|
NA
|
Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; SMC-S-016 "Test Requirements for Launch, Upper-stage, and Space Vehicles 5 Sept 2014 or equivalent
|
| 4.4.6-4-9 Ensure that adequate control authority is demonstrated on all active thermal control hardware items |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
Spacecraft Thermal Control Handbook, Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; SMC-S-016 "Test Requirements for Launch, Upper-stage, and Space Vehicles 5 Sept 2014 or equivalent
|
| 4.4.6-4-10 Ensure that assumed optical properties for critical thermal control surfaces are within commonly accepted ranges, as recommended in standard handbooks and used by other programs |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
Spacecraft Thermal Control Handbook, Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-11 Ensure that assumed environmental constants for solar, albedo and earthshine heating agree with standard practices |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
Spacecraft Thermal Control Handbook, Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-12 Ensure that bonding, interface and material assumptions are conservative |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
Spacecraft Thermal Control Handbook, Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-13 Ensure that all part temperature predictions are within derated limits |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
Spacecraft Thermal Control Handbook, Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
|
| 4.4.6-4-14 Ensure temperature predictions and margins have been provided for worst-case conditions (testing, ground, launch, transfer orbit, operational, contingency) |
Phase B |
Phase C |
|
NA
|
NA
|
NA
|
TOR-2004(3909)-3360 Rev 1, Systems Engineer's Major Reviews for National Security Space System Programs
|
| 4.4.6-4-15 Ensure that any potentially systemic design issues are considered for a Design Advisory |
Phase B |
Phase C |
Phase D1 |
Phase D2 |
Phase D3 |
|
Any design or architecture issue that has severe, systemic, or widespread consequences is a potential candidate for a Design Advisory. Design Advisories provide the community with timely and interim notification of an important design issue which may ultimately be captured in a specification or standard.
|
NA
|
NA
|
NA
|