STRUCTURAL DESIGN AND TEST FACTORS OF SAFETY FOR SPACEFLIGHT HARDWARE
|Publication Date:||5 October 2016|
The purpose of this NASA Technical Standard is to establish NASA structural design and test factors, as well as service life factors to be used for spaceflight hardware development and verification. The primary objective of this NASA Technical Standard is to define factors which ensure safe and reliable structural designs. The secondary objective is to reduce space project costs and schedules by enhancing the commonality of use of hardware designs among NASA flight projects, Centers, and their contractors. The criteria in this NASA Technical Standard are to be considered as minimum acceptable values unless adequate engineering risk assessment is provided that justifies the use of lower values
This NASA Technical Standard defines engineering practices for NASA programs and projects.
This NASA Technical Standard is approved for use by NASA Headquarters and NASA Centers and Facilities and may be cited in contract, program, and other Agency documents as a technical requirement. It may also apply to the Jet Propulsion Laboratory and other contractors only to the extent specified or referenced in applicable contracts.
Verifiable requirements are numbered and indicated by the word "shall"; this NASA Technical Standard contains 65 requirements. Explanatory or guidance text is indicated in italics beginning in section 4. To facilitate requirements selection and verification by NASA programs and projects, a Requirements Compliance Matrix is provided in Appendix A.
[FSR 1] NASA programs and projects that do not meet the provisions of this NASA Technical Standard shall be assessed by the NASA Program Manager for the associated risk to the success of the planned NASA mission and approved by the responsible Technical Authority.
[FSR 2] This NASA Technical Standard shall not supersede applicable laws and regulations unless a specific exemption has been obtained by the Office of the NASA Chief Engineer.
The criteria in this NASA Technical Standard are applicable to launch vehicle payloads and launch vehicle structures (including propellant tanks and solid rocket motor (SRM) cases). These criteria apply to flight hardware that is utilized for NASA missions. This NASA Technical Standard presents acceptable minimum factors of safety for use in analytical assessment and test verification of structural adequacy of the flight hardware. Designs are generally to be verified by both structural analyses and tests.
Criteria are specified for design and test of flight articles when the actual flight hardware is tested (protoflight), and when qualification tests are conducted on a separate (prototype) article. In general, no distinction is made between "human-rated" and "robotic" missions. Structures of human-rated flight systems may be subjected to additional verification and/or safety requirements (e.g., fracture control) that are consistent with the established risk levels for mission success and flight crew safety
Specifically excluded from this NASA Technical Standard are requirements for design loads determination and fracture control. Also excluded are the design and test factors for engines, rotating hardware, solid propellant, insulation, ground support equipment, and facilities. This NASA Technical Standard also does not cover specific configuration factors such as fitting factors, buckling knockdown factors, and load uncertainty factors.