To support focused science and engineering missions, spacecraft bus designs should minimize mass and maximize design flexibility without reducing capability. This requires a highly efficient spacecraft structure to maintain the required stiffness with a minimal mass.
Thermo-mechanical design of honeycomb panel with fully-potted inserts used for spacecraft design
2013-06-01
1342187 byte
Conference paper
Electronic Resource
English
Methods for installation of potted inserts having a latch mechanism
European Patent Office | 2017
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