有连续推力控制的卫星轨道确定算法

连续推力轨道控制跟踪过程，观测量中包含推力加速度信息，反映轨道机动过程中卫星动力学的模型误差。以跟踪和精确定位空间机动目标为目的，给出基于地面雷达观测，实时估计推力加速度，修正卫星动力学模型的轨道确定算法。建立连续推力控制过程变质量动力学模型，给出常推力变加速度满足的运动学微分方程；建立变加速度估计系统状态方程和扩展卡尔曼滤波轨道确定算法；并给出连续推力控制过程中卫星运动状态关于变加速度的变分运动方程。实际飞行控制中应用表明，通过离散观测数据，实时估计连续推力变加速度，解决连续推力过程轨道精确确定问题是可行的。

On-line orbit determinative method for satellites with continuous thrust acceleration

This paper focuses on the continuous constant low thrust maneuver, which has drawn extensive interests in current space research activities due to its efficiency and flexibility in realizing the maneuver of space vehicles. It is required to estimate the acceleration that applies to maneuvering a vehicle to determine the motion parameters in order to pick up the maneuvering satellite and interfere in maneuver process in case of emergency. In this paper, an elegant differential equation is derived for variable acceleration which is chosen as a state variable, and measurement equations are built to reflect the relationship between the state space and measurement sampling space. The variation equations for the measurement vector to acceleration are put forward in order to linearize the discrete-time measurement equations. The algorithm has  successfully applied to maneuver process in commanding LEO satellite into geo-stationary orbit. The mission real flight scenery shows the algorithm developed here can estimate the acceleration and determine the orbital parameters during the continuous thrust maneuver process.