Slewing flexible spacecraft with deflection-limiting input shaping

被引:127
作者
Singhose, WE [1 ]
Banerjee, AK [1 ]
Seering, WP [1 ]
机构
[1] LOCKHEED PALO ALTO RES LABS,DYNAM & CONTROL LAB,PALO ALTO,CA 94304
关键词
D O I
10.2514/2.4036
中图分类号
V [航空、航天];
学科分类号
08 [工学]; 0825 [航空宇航科学与技术];
摘要
A control scheme is described for slewing flexible spacecraft with both suppression of deflection during the slew and elimination of residual oscillations. The method minimizes the maneuver time subject to constraints on residual vibration magnitude, sensitivity to modeling errors, rest-to-rest slew distance, and the transient deflection amplitude. Furthermore, a solution is sought that provides inherent fuel efficiency. The feasibility of the approach is demonstrated with linear and nonlinear computer simulations.
引用
收藏
页码:291 / 298
页数:8
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