摘要
细长体结构卫星的自旋运动是不稳定的,章动有发散趋势,须进行实时的章动监视,且章动角的测量值包含有误差。通过引入一个离散控制过程的系统,介绍了卡尔曼滤波器的基本原理,建立了自旋卫星自旋运动简化的动力学模型,给出了运动方程和观测方程,详细地推导了适用于自旋卫星章动控制的卡尔曼滤波处理过程,利用该模型对某自旋卫星章动进行仿真计算,并对姿态章动联合控制和应急章动控制情况下的章动控制应用情况进行分析,得出结论:基于卡尔曼滤波的卫星章动角计算的方法正确、结果准确。
The nutation of spin-stabilized satellites should be monitored in realtime because the spin movement of long satellite body is unsteady, the nutation is dispersive and there are errors in measurement of the nutation angle. A discrete control process system is used and the basic theory of Kalman filter is introduced. A simplified dynamics model of satellite spin motion is established. A movement equation and an observation equation are presented. We deduced in detail the Kalman filter process that is fit for nutation control for spin-stabilized satellites. The model was used in simulation and computation of the nutation of a spin-stabilized satellite and application of nutation control was analyzed under the conditions of united attitude and nutation control and emergency nutation control. The re- sults show that the nutation angle calculation method based on Kalman filter is correct.
出处
《飞行器测控学报》
CSCD
2014年第6期525-529,共5页
Journal of Spacecraft TT&C Technology
关键词
章动
卡尔曼滤波
动力学模型
自旋卫星
nutation
Kalman filter
dynamic model
spin-stabilized satellite
