摘要
研究带有转动载荷和挠性附件的卫星姿态控制问题.基于具有广义坐标形式的牛顿-欧拉方法建立了卫星姿态动力学模型和转动载荷力矩模型,研究载荷产生的动不平衡力矩和静不平衡力矩的机理和特点.分析载荷干扰对卫星姿态的影响特性,给出基于传递函数进行拉氏变换以估算姿态抖动量的方法.分析卫星姿态控制系统设计干扰补偿控制器的条件,给出了控制器的工程设计方法.验证结果表明该方法有效且能提高卫星姿态精度.
The attitude control of satellite with flexible appendage and rotatable payload is investigated. Attitude dynamics equations and rotatable payload torque model are presented on the basis of Newton-Euler method with generalized coordinates. The theory and characteristics on imbalance torque of rotatable payload are analyzed. Secondly, the influence of payload disturbance characteristics on attitude of satellite is studied, and the estimation method of attitude jitter is illustrated based on Laplace transform of transfer equation. Finally, the condition of a disturbance reduction controller is developed, which is applied to the satellite attitude control system, and the controller engineering application method is presented. The verification results show the effectiveness of the proposed approach, and the accuracy of satellite attitude is improved.
作者
王新民
褚永辉
张俊玲
袁军
WANG Xinmin CHU Yonghui ZHANG Junling YUAN Jun(Beijing Institute of Control Engineering, Beijing 100190, China Science and Technology on Space Intelligent Control Laboratory, Beijing 100190, China)
出处
《空间控制技术与应用》
CSCD
北大核心
2016年第5期14-18,共5页
Aerospace Control and Application
基金
国家重大科技专项基金资助项目
关键词
静不平衡
动不平衡
转动载荷
干扰补偿
static imbalance
dynamic imbalance
rotatable payload
disturbance compensation
