Optimal Spacecraft Attitude Maneuvers via Adjoint Method

被引:0
|
作者
Guo, Jian [1 ]
Yao, Yu [1 ]
He, Fenghua [1 ]
Yang, Baoqing [1 ]
Wang, Xingdan [1 ]
机构
[1] Harbin Inst Technol, Harbin 150006, Peoples R China
来源
关键词
Attitude Maneuver; Spacecraft; Optimization; Adjoint Method;
D O I
10.4028/www.scientific.net/AMM.275-277.778
中图分类号
T [工业技术];
学科分类号
08 ;
摘要
This paper studies the spacecraft attitude maneuver optimization problem. The maneuver aim is to avoid fuel cost by only using CMGs in the maneuver course. The nonlinear dynamic equations of the attitude system are established, the attitude maneuver optimization is depicted into a two point boundary value problem (TPBVP). The adjoint method is used to convert the TPBVP into the initial value problem. Numerical results indicate that the adjoint method is efficiently capable for attitude maneuver optimization.
引用
收藏
页码:778 / 781
页数:4
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