轨道交会、悬停及绕飞控制的解析解方法

Analytical Solution Method for Orbit Rendezvous,Hovering and Fly-Around Control

面向航天器交会对接、编队伴飞以及在轨操控等空间应用的需求,分别对近圆、椭圆轨道上航天器间的相对运动进行了分析与建模,在常值推力作用假设下进行了相对运动的解析求解。采用模型预测的方法获得航天器相对位置和相对速度的预期偏差。通过广义逆变换构造关于预期偏差的最小范数、最小二乘全状态反馈控制器。提出了一种普遍适用于近圆、椭圆轨道,可以实现轨道交会、相对悬停保持和循迹绕飞,对相对位置和相对速度进行同步控制的高精度、高稳定度相对制导律。仿真结果校验了方法的可行性和有效性。

According to the requirements of space applications such as spacecraft RVD, formation flight and on-orbit operation, the relative motion between spacecraft is analyzed and modeled. Under the assumption of the constant thrust action, the relative motion is solved analytically. The expected deviation of the relative position and relative velocity of the spacecraft is obtained by using the model prediction method. A full state feedback controller about minimum norm and least square of the expected deviation is constructed based on the generalized inverse transformation. A guidance law generally applicable to nearly circular orbit and elliptical orbit is proposed, which can realize orbital rendezvous, hovering and fly- around with high precision and high stability by the synchronous control of the relative position and velocity. The simulation results verify the feasibility and effectiveness of the proposed method.