Publication Date:
2019-07-13
Description:
This analysis pertains to the applicability of optimal sensitivity information to aerospace vehicle design. The present analysis demonstrates that post-optimality information generated through first-order computations can be used to accurately predict file effect of constraint and parameter perturbations on the optimal solution. This assessment is based on the solution of an aircraft design problem in which the post-optimality estimates are shown to be within a few percent of the true solution over the practical range of constraint and parameter variations. Through solution of a reusable, single-stage-to-orbit, launch vehicle design problem, this optimal sensitivity information is also shown to improve the efficiency of the design process. For a hierarchically decomposed problem, this computational efficiency is realizable by estimating the main-problem objective gradient through optimal sensitivity calculations. By reducing the need for finite differentiation of a re-optimized subproblem, a significant decrease in the number of objective function evaluations required to reach the optimal solution is obtained.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 93-3932
,
; 13 p.|AIAA, Aircraft Design, Systems and Operations Meeting; Aug 11, 1993 - Aug 13, 1993; Monterey, CA; United States
Format:
text
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