摘要
研究带有大型单翼太阳帆板的三轴稳定卫星在稳态运行期间姿态精确定向问题。计算了卫星运行空间的环境干扰力矩,分析了传统控制方法的局限性,并给出一种新的卫星姿态高精度动态补偿控制算法。推导了卫星的挠性动力学模型,在此基础上通过仿真比较了此方法和传统方法的实际效果。结果表明,该方法可以显著提高姿态控制的响应速度和精度。
The precise attitude control of 3-axis stable satellite with huge single flexible battery array for steady state operation was studied in this paper. The most important four environmental disturbance torques during satellite operation was analyzed in detail to present a mathematical model describing their dynamic behavior. In view of the limitation of traditional attitude control appreach, we proposed a novel high precision feedforward compensating attitude control algorithm. The flexible satellite dynamic model was derived, based on which the simulation was carried out to compare the performance of two methods. Simulation results shows that the algorithm proposed in this paper outperforms the traditional one remarkably both in respondent time and steady state precision.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2006年第6期1393-1396,共4页
Journal of Astronautics
关键词
姿态控制
环境干扰力矩
挠性振动
Attitude control
Environmental disturbance torques
Flexible vibration
