Spacecraft structure analytical and test verification methods were reviewed. It is concluded that in general adequate verification capabilities exist to provide the required level of confidence in spacecraft projects. When optimal verification procedures are performed in a project low safety margins might be sufficient for the realization of the project. However, the employment of minimum safety margins, i.e., margins as requested by the launcher authorities, is not encountered in practice in the space industry because of user uncertainty as to launcher loads. To improve spacecraft design and verification activities better knowledge is required for launcher loads as they arise in reality. The recording of flight responses and loads during launch is essential for an overall improvement of design and verification activities. Such activities allow the employment of representative safety margins, and eliminate excessive margins currently employed to cover load uncertainties.
Development of Experimental/Analytical Concepts for Structural Design Verification
1985
139 pages
Report
Keine Angabe
Englisch
Microgravity Environment Compatibility of Payloads Analytical Concepts and Verification
SAE Technical Papers | 1994
|NTRS | 1967
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