Strength and stiffness analyses are presented for two different interface structural configurations selected in the phase 1 study based on mission types. The configurations are a conical structure for the geosynchronous mission spacecraft, and a honeycomb platform attached to a flanged separation ring for the low earth orbit spacecraft. Both configurations use beryllium as the main load carrying material. In the analyses the detailed dimensions (optimized within the design restraints for minimum structural mass), associated stress levels, deflections, fundamental frequencies, and response were calculated for each structural configuration.
Study of an Interface Structure Design, Phase 2
1974
244 pages
Report
Keine Angabe
Englisch
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