摘要
在建立卫星姿态运动学方程与姿态动力学方程的基础上,设计了姿态控制器,仿真结果表明该控制系统具有较好的动态和稳态性能;结合有效载荷的两维伺服控制系统模型,提出了卫星运动补偿方案。使用高精度星敏感器与陀螺组合姿态确定的软件,在各种干扰力矩作用下,对卫星运动补偿进行了数学仿真。结果表明,该方案可以提高有效载荷光轴指向精度和指向稳定度。
In this paper, based on dynamic and kinetic equations of satellite attitude, the Attitude controller is designed. The simulation results show that the attitude control system have better dynamics performance and steady state performance. Considering the servosystem model of payload, compensation scheme satellite motion is introduced. Using software of high star sensor and Gyro integrated attitude determination, underlying all disturbance, an numerical simulation is provided to show that the compensation satellite motion have better Line-of-Sight (LOS) Point precision and stability.
出处
《宁波职业技术学院学报》
2008年第2期1-5,共5页
Journal of Ningbo Polytechnic
关键词
姿态控制器
卫星运动补偿
姿态确定
光轴指向精度
Attitude controller
compensation satellite motion
attitude determination
LOS point precision