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Global nonlinear optimization of spacecraft protective structures designThe global optimization of protective structural designs for spacecraft subject to hypervelocity meteoroid and space debris impacts is presented. This nonlinear problem is first formulated for weight minimization of the space station core module configuration using the Nysmith impact predictor. Next, the equivalence and uniqueness of local and global optima is shown using properties of convexity. This analysis results in a new feasibility condition for this problem. The solution existence is then shown, followed by a comparison of optimization techniques. Finally, a sensitivity analysis is presented to determine the effects of variations in the systemic parameters on optimal design. The results show that global optimization of this problem is unique and may be achieved by a number of methods, provided the feasibility condition is satisfied. Furthermore, module structural design thicknesses and weight increase with increasing projectile velocity and diameter and decrease with increasing separation between bumper and wall for the Nysmith predictor.
Document ID
Document Type
Technical Memorandum (TM)
Mog, R. A.
(NASA Marshall Space Flight Center Huntsville, AL., United States)
Lovett, J. N., Jr.
(Alabama Univ. Huntsville., United States)
Avans, S. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:100387
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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