摘要
为降低卫星定轨中摄动运动方程计算的复杂性,根据低轨卫星动力学模型,在考虑二体作用力和地球非球形引力J2项摄动条件下,以拟合函数表示其余的摄动力,并采用扩展卡尔曼滤波(EKF)算法,提出了一种基于拟合摄动力函数的低轨卫星自主定轨滤波算法。仿真结果表明,该法可明显减少计算量,缩短滤波收敛时间,提高卫星的实时处理能力。定轨精度为:位置方向70.7 m(1σ),速度方向0.16 m/s(1σ),可满足一般低轨卫星的精度要求。
To decrease the computation complex of perturbing formulae in satellite orbit determination, an autonomous orbit determination filtering algorithm based on base function under the consideration of two-body applied force and J2 force, and other residual perturbing forces fitted by a function was put forward according to the dynamic model of low earth orbit satellite in this paper, in which the extended Kalman filter was adpoted. The simulation results showed that this method could reduce the computation amount, shorten filtering time and improve the real-time processing ability of the satellite. The orbit determination accuracy would be 70.7 m （1 σ） for position and 0.16 m/s （1σ） for velocity, which could meet the requirement for general LEO satellite.
出处
《上海航天》
北大核心
2006年第2期10-14,41,共6页
Aerospace Shanghai
关键词
低轨卫星
定轨方法
动力学模型
摄动力
拟合函数
扩展卡尔曼滤波
Low earth satellite
Orbit determination
Dynamic model
Perturbing force
Fit function
Extended Kalman filter
