APPROXIMATE FINITE-THRUST TRAJECTORY OPTIMIZATION

被引:18
作者
JOHNSON, FT
机构
[1] The Boeing Company, Space Technology, Seattle, WA
关键词
D O I
10.2514/3.5265
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A method which rapidly computes optimum finite-thrust space trajectories is presented. The approach is based on the approximation of the state time history by a polynomial. Differentiation and integration are performed in closed form and the problem is reduced to one of ordinary calculus. The technique is applied to constant power, variable-thrust trajectories, and results are presented for Earth-Mars transfers. Apparently the method is an order of magnitude faster than standard techniques. The method is not restricted to low-thrust levels or to transfers between nearby orbits. © 1969 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
引用
收藏
页码:993 / &
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