摘要
研究带两帆板航天器的三维再定向与振动抑制问题 ,执行机构为反作用轮。建立了柔性空间飞行器三轴耦合姿态动力学模型和四元数姿态运动学模型 ,建模时考虑了帆板的弯曲变形和扭转变形。采用拟欧拉角及角速度作为反馈信号 ,设计了一种PD控制律。该控制律可以用于对任意目标姿态的再定向而形式保持不变。用Lyapunov方法证明了姿态的渐近稳定性和模态振动的衰减性。非线性闭环系统的仿真结果验证了所设计控制律不仅能够使航天器完成对任意目标姿态的再定向 。
Three axis reorientation and Vibration suppression of flexible spacecraft using reaction wheels are investigated.Three dimension attitude dynamical model with consideration of bending and torsional deformations of the flexible appendages is derived by using quasi coordinate LaGrange' equations,and attitude kinetic model is described by quaternion.Based on angular rates and quasi Euler angles,which are derived by using a quaternion matrix transformation,a control law with flexible parameters in the control gains is presented.Analysis with Lyapunov direct and indirect method indicates that the control law is able not only to stabilize the spacecraft attitude but also to suppress vibtations of the fiexible appendages.Attitude convergence of large angle reorientation is also discussed.Simulation results illustrate that the control law drives the three axis attitudes along a shorter path to the target attutudes and damps out the vibration energy of the flexible appendages.
出处
《宇航学报》
EI
CSCD
北大核心
2000年第4期31-40,共10页
Journal of Astronautics
基金
国家自然科学基金
关键词
柔性航天器
姿态再定向
振动
带两帆板航天器
Flexible spacecraft\ Attitude dynamics\ Three axis attitude reorientation\ Attitude maneuver\ Vibration suppression\ Reaction wheels
