A method for the optimum design of relatively small skin-rib-stringer structures is of significant importance for spacecraft instruments. This investigation attempted to develop a design method and establish a basic criteria for determining member sizes and spacing to provide minimum weight of such structures of any configuration. Of particular importance is the flexure of the ribs and stringers and the load carrying ability of the enclosing skin. The method developed attempted to include these considerations but the matrix formulated was ill-conditioned and no positive design results was achieved. (Author)
Optimum Design of Space Satellite Instrument Framework and Packaging
1967
83 pages
Report
No indication
English
Payload Packaging Design - Alouette Satellite
NTIS | 1963
|ENGINEERING NOTES Optimum Design of a Space Frame and its Application in Satellite Structure
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