Optimal asteroid deflection using low-thrust propulsion

被引：0
|
作者：
Abu-Saymeh, MS [1 ]
Kluever, CA [1 ]
机构：
[1] Univ Missouri, Kansas City, MO 64110 USA
来源：
GUIDANCE AND CONTROL 1999 | 1999年 / 101卷
关键词：
D O I：
暂无
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A direct trajectory optimization method is used to investigate optimal low-thrust asteroid deflection. This method replaces the optimal control problem with a nonlinear programming problem, which in turn is solved by using sequential quadratic programming. A fixed trajectory sequence of a single powered are is set. The feasibility of deflecting a fictional asteroid is investigated, and the optimal maximum deflection is computed for two electric propulsion thrusters. In addition the corresponding propellant mass required is computed for different solar power levels.
引用
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页码：51 / 61
页数：11
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