| 4.5.6-4-1 Ensure payload technology readiness and risk burn-down plan have been assessed |
Phase 0 |
Phase A |
Phase B |
Phase C |
|
Ensure payload system 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.
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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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| 4.5.6-4-2 Ensure that the antenna array concept is fully worked out and that an advanced procurement schedule which allows for at least two iterations of the array fabrication cycle has been generated |
Phase A |
Phase B |
Phase C |
Phase D1 |
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Ensure array far field performance is well understood.
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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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| 4.5.6-4-3 Ensure payload design including units, assemblies, sub-assemblies and parts meets the mission performance requirements |
Phase 0 |
Phase A |
Phase B |
Phase C |
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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 payload requirements in terms of the overall mission operability. The payload must be validated against how the components will be used for that particular application.
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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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| 4.5.6-4-4 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 |
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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. Disseminate and document/archive results of the trade studies.
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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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| 4.5.6-4-5 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.
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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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| 4.5.6-4-6 Ensure payload hardware and software (as applicable) functions are described in the payload 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.
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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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| 4.5.6-4-7 Ensure payload 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.
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NA
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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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| 4.5.6-4-8 Ensure adequate margins for SW memory, bandwidth, and processing capabilities |
Phase B |
Phase C |
|
Ensure assessment of predicted worst case loading on hardware and software subsystems and appropriate amount of margin necessary in the baseline design.
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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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| 4.5.6-4-9 Ensure telemetry content and sampling is adequate to diagnose state-of-health |
Phase B |
Phase C |
|
Ensure sufficient telemetry points, content, and sampling resolution are designed into the monitoring subsystem to adequately assess the state of health of the PL and to allow troubleshooting of anomalies from the ground. Ensure that all self correcting (on-board automatic anomaly resolution software) processes provide adequate telemetry fidelity of the anomaly as well as an option to shut the autonomy off, if it becomes necessary for ground controllers to take over manual commanding.
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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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| 4.5.6-4-10 Ensure that a complete tolerance analysis is presented |
Phase B |
Phase C |
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Ensure the tolerance analysis should distributes design, fabrication, alignment, and environmentally induced errors according to an error budget so that the as-built and as-used optical system is likely to meet top-level image quality requirements. the budget should include allocations for optical design residual, component fabrication errors, alignment errors, launch vibration, gravity release, on-orb thermal effects, jitter, and temporal stability effects. Ensure with design review that the CAD ray trace and analysis of the optical design is in compliance with packaging volume constraints, first-order optical properties, image quality and radiometric performance and that these specifications are met with margin appropriate to the maturity of the design.
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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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| 4.5.6-4-11 Ensure that all alignment variables are addressed |
Phase B |
Phase C |
|
Ensure that the on-orbit alignment (focus) compensators mechanisms are reliable. Ensure that estimated tolerances on parts and alignments are feasible and within the reach of the alignment methods and measurement metrology being used. Ensure that component and assembly drawings and other contractor specifications are ready prior to procurement, and that the nominal constructional parameters and tolerances are consistent with the top-level tolerance budget. Ensure that the alignment methods and procedures meet the required tolerances. Ensure that the design approach includes a small number of orthogonal alignment compensators, including an ability to adjust focus on-orbit.
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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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| 4.5.6-4-12 Ensure that the materials list has been reviewed for vacuum compatibility and high energy radiation susceptibility |
Phase B |
Phase C |
|
Ensure that the materials list (optical substrates, coatings, adhesives, and paints for stray light and thermal control) have been reviewed for vacuum compatibility (out gassing properties) and high energy radiation susceptibility. Ensure that materials experts perform this review and that tests for material vacuum compatibility are conducted on samples prior to integration of parts with the flight hardware for critical components.
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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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| 4.5.6-4-13 Ensure that the contamination levels required to meet stray-light specifications are determined |
Phase B |
Phase C |
|
Ensure that the optical transmittance of the system is evaluated using realistic coating and material transmittances data while including polarization dependencies (when important).Ensure that any surface treatments are identified and space qualified before applying them to flight hardware. Ensure that stray light analysis includes allocations for surface contamination in its Bi Directional Reflectance Distribution Function (BRDF) models.
|
NA
|
NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
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| 4.5.6-4-14 Ensure backward compatibility of all signals generated and transmitted by the navigation payload |
Phase B |
Phase C |
|
Ensure that the signal transmitted from the satellite is compatible with previously deployed receivers for bit structure, timing, power, and other critical signal characteristics before delivery of the first satellite.
|
NA
|
NA
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Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494
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| 4.5.6-4-15 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.
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NA
|
NA
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NA
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| 4.5.6-4-16 Ensure functional, electrical, mechanical, and data flow block diagrams are baselined from system to unit level and are static |
Phase C |
|
Ensure that suballocation of program requirements down to payload hardware and software subsystems and unit level are appropriate and monitored throughout the program lifecycle. The responsible POC for Navigation Payload Systems Engineering coordinates with Program Systems Engineering to ensure that issues that arise through design, production and testing phases are flowed upwards against any impacted higher level requirements. Ensure that the most current and/or effective versions of designs are in use, utilizing program liens as necessary in the event of discrepancies. Ensure requirements monitoring encompasses supporting documentation, including but not limited to functional hardware and software block diagrams, detailed electrical and mechanical interfaces, detailed data flow, and interface compatibility.
|
NA
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NA
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Space Vehicle Systems Engineering Handbook (TOR-2006(8506)-4494)
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