Statement and mathematical formulation of extremum problem associated with optimum design of spacecraft impact limiters (payload plus energy dissipator) are presented; semigeometric solution is given; it is shown that, in general, practical rather than true maximum for objective function, developed as payload fraction, exists in solution domain; energy dissipators having high specific energy capacities (energy dissipated per pound of material) are best suited for achieving optimum system design. (11875)
Materials-design synthesis for optimum design of spacecraft energy-dissipating systems
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 10
1968
5 pages
Aufsatz (Zeitschrift)
Englisch
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Energy dissipating structures -- Structures-materials-design synthesis
Engineering Index Backfile | 1965
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