充液柔性航天器非线性姿态动力学及再定向姿态机动  

NONLINEAR ATTITUDE DYNAMICS AND REORIENTATIOH MANEUVER FOR COMPLETELY LIQUID-FILLED FLEXIBLE SPACECRAFT

作　　者：岳宝增[1] 

机构地区：[1]北京理工大学宇航学院力学系,北京100081

出　　处：《动力学与控制学报》2010年第1期74-79,共6页Journal of Dynamics and Control

基　　金：国家自然科学基金(10572022;10772026);教育部博士点基金(20080070011);教育部留学归国人员基金(20080732040);北京市重点学科建设项目资助~~

摘　　要：研究全充液柔性航天器大角度姿态机动中非线性姿态动力学及姿态再定向问题.采用Lagrange方法推导了液-柔耦合系统动力学方程并对系统进行了相空间动力学研究.由于能量耗散及柔性附件振动对系统产生扰动并由此引起混沌姿态运动,经历姿态转换后的航天器最终姿态定向不能预先确定.本文研究表明,通过一对互为反向的脉冲推进可以完成预期的姿态再定向机动.给出了实现姿态再定向机动的控制策略,并对控制前后的姿态本体轨迹及主角动量分量时间响应历程进行了数值仿真.This paper investigated the problem of chaotic attitude and reorientation maneuver for completely viscous liquid-filled spacecraft with flexible appendage. All the equations of motion were derived by using Lagrang jan mechanics and transformed into the form consisting of an unperturbed part plus perturbed term in order to exploit the system＇ nonlinear characteristics in phase space. We emphases on the chaotic attitude dynamics produced from certain sets of the physical parameter values of the spacecraft when energy dissipation acts to derive the body from minor to major axis spin. The orientation of the spacecraft relative to the inertially fixed angular momentum vector is unpredictable because of the occurrence of chaotic dynamics during spin-axis transition. This paper demonstrated that the desired reorientation maneuver was guaranteed by using a pair of thruster impulses. The control strategy for reorientation maneuver was designed, and the numerical simulation results were presented for both the uncontrolled and controlled spins transition.

关 键 词：非线性姿态机动 姿态再定向 控制策略 充液航天器 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]