Nonlinear dynamics in the attitude control system of a flexible spacecraft

被引：0
|
作者：
Avanzini, G [1 ]
de Matteis, G
机构：
[1] Politecn Torino, Dept Aerosp Engn, I-10129 Turin, Italy
[2] Univ Roma La Sapienza, Dept Mech & Aeronaut, I-00184 Rome, Italy
来源：
THIRD INTERNATIONAL CONFERENCE ON NONLINEAR PROBLEMS IN AVIATION AND AEROSPACE, VOLS 1 AND 2, PROCEEDINGS | 2002年
关键词：
attitude dynamics; spacecraft; bifurcation;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
Attitude dynamics of a flexible spacecraft with nonlinearities in control system elements is analyzed by bifurcation theory. Continuation of equilibrium points of Poincare map is carried out because the controller structure varies depending on pitch error amplitude and, consequently, the phase-flow is not continuous. The complex dynamical behavior of the system is investigated when the interaction with the elastic degree-of-freedom is taken into consideration. Bifurcation diagrams show the effects of design and operational parameters on the pointing accuracy of the vehicle.
引用
收藏
页码：55 / 62
页数：8
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