交会对接寻的段水平双脉冲交会轨道精确求解

Exact Solution of the Rendezvous Orbit of Horizontal Double Impulses for the Homing Phase of Spacecraft Rendezvous and Docking

基于考虑摄动影响的精确轨道动力学模型,对交会对接寻的段水平双脉冲交会轨道的精确求解方法进行了研究。提出了将控制脉冲的俯仰角近似转化为控制时刻的轨道幅角,从而调整脉冲控制时刻以消除径向速度增量的方法,精确求解首末水平双脉冲的启控时刻;引入导引终点位置偏差的比例控制方法,精确求解水平双脉冲的精确控制量。仿真结果表明,2轮整体迭代可获得首末水平脉冲控制时刻和控制量的精确值,脉冲水平特性达到俯仰角小于1°,导引终点相对位置精度达到10m,验证了该方法的正确性。

Based on an accurate orbit dynamics model taking into consideration perturbation factors, exact solution of the rendezvous orbit of horizontal double impulses for the homing phase of spacecraft rendezvous and docking is studied. To obtain the control times of the start and end horizontal double impulses, an algorithm is put forward and it eliminates the radial vectors of double impulses by adjusting the impulse control times with pitch angles translated into orbit arguments. A scale algorithm for proportional control of the end-point position bias for homing phase guidance is introduced to calculate the exact control values of horizontal double impulses. Simulation indicates that the proposed solution is correct and the exact control times and magnitudes of the horizontal double impulses can be obtained through two-round iterations while the pitch angle accuracy of horizontal characteristics of impulses is with- in 1° and the relative position accuracy of homing guidance end-point is within 10 m.