摘要
给出了超低轨卫星气动参数和转动惯量的在轨实时辨识方法。针对超低轨卫星所处的稀薄流环境,建立了镜面-漫反射模型稀薄流散射系数的傅里叶级数模型。根据卫星姿态动力学与运动学方程推导了傅里叶级数模型中各气动参数以及卫星转动惯量的线性观测模型。以采用气动主动控制方式的近地圆轨道纳星为仿真对象,用递推最小二乘法进行在轨实时辨识,辨识结果与设定值一致。方法对卫星在轨实时控制时需获取高精度的气动力矩和卫星真实转动惯量有重要的意义。
A real-time identification method of pneumatic parameters and inertia moment for the ultra-low orbit satellite was put forward in this paper. The Fourier series model of accommodation coefficient within time of the mirror diffuse reflection model in the environment of rarefied gas was established. The linear observation model of the pneumatic parameters and inertia moment of the satellite in Fourier series model was deduced based on the attitude dynamic and kinematic equation. The real-time determination on orbit using recursive least square method was simulated for a low earth circle orbit satellite using pneumatic active control. The results were consistent with the theoretical analysis. This method could be used in the situation which needed the high precision calculating of aerodynamics and true inertia moment.
出处
《上海航天》
2012年第5期20-24,40,共6页
Aerospace Shanghai
关键词
超低轨卫星
气动参数
转动惯量
实时辨识
Ultra-low orbit satellite
Pneumatic parameter
Inertia moment
Real-time identification
