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Document NASA NASA-STD-5001 is offered by IHS as part of an online subscription. This subscription contains many documents on the same topic.
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NASA NASA-STD-5001 Document Information:
Title
STRUCTURAL DESIGN AND TEST FACTORS OF SAFETY FOR SPACEFLIGHT HARDWARE
NASA - National Aeronautics and Space Administration
Publication Date:
Aug 5, 2008
Scope:
Purpose
The purpose of this standard is to establish NASA structural
strength design and test factors, as well as service life factors
to be used for spaceflight hardware development and verification.
It is intended to reduce space project costs and schedules by
enhancing the commonalty of use of hardware designs among NASA
flight projects, Centers, and their contractors. While it is true
that structural designs are sometimes governed by criteria other
than strength, the criteria in this document are to be considered
as minimum acceptable values unless adequate engineering risk
assessment is provided which justifies the use of lower values.
Applicability
This standard recommends engineering practices for NASA programs
and projects. It may be cited in contract, program, and other
Agency documents as a technical requirement. Requirements are
numbered and indicated by the word "shall." Explanatory text or
guidance is indicated in italics beginning in section 4.
Tailoring of this standard for application to a specific program
or project shall be formally documented as part of program/project
requirements and approved by the assigned Technical Authority.
Determining the suitability of this standard and its provisions
is the responsibility of program/project management and the
performing organization. Project-specific tailoring may generate
other project-specific requirements that are derivatives of this
standard.
NASA programs and projects that do not meet the provisions of
this document shall be assessed by the NASA Program Manager for the
associated risk to the success of the planned NASA mission and
approved by the assigned Technical Authority.
This document 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 standard are applicable to 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. The standard presents
acceptable minimum factors of safety for use in analytical
assessment and test verification of structural adequacy of the
flight hardware. Designs must generally be verified by both
structural strength analyses and tests.
The factors shall be multiplied by the limit stresses (including
additive thermal stresses), and the products shall be verified not
to exceed material allowable stresses (yield and ultimate) under
the expected temperatures and other operating conditions.
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 "manned" and
"unmanned" missions. Structures of manned 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.
The requirements specifically excluded from this standard are
design loads determination, fracture control, engines, rotating
hardware, solid propellant, insulation, ground support equipment,
and facilities. Also excluded are specific configuration factors,
such as fitting factors, buckling knockdown factors, and load
uncertainty factors.
Keywords:
- Acceptance test
- Factors of safety
- Proof test
- Protoflight test
- Prototype test verification
- Qualification test
- Spaceflight hardware
- Standard
- Structural design criteria
- Test factors
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