摘要
提出了一种有限推力下主动航天器在完成轨道转移的同时形成相对目标航天器绕飞的方法。根据以改进春分点轨道根数表示的非奇异轨道摄动方程,用变分方法将问题转化为经典的最优控制,由相对运动动力学获得主动航天器实现绕飞须满足的终端约束条件,再用非线性规划求解。给出了求解模型。理论分析和仿真结果表明,该方法理论上可行,但为减少干扰产生的偏差,还需对绕飞形成过程中的导引率进行研究。
A control method to form relative fly-orbit directly under finite thrust while the chaser was arriving at the vicinity of the target was put forward in this paper. Based on the modified equinoctial elements, the control problem was converted into a classical optimal control by variation. The terminal dynamic constraints were derived from relative dynamics, which was solved by the nonlinear programming. The model was established. The theoretical analysis and simulation results showed that this method was feasible. But to reduce the error caused by the disturbance, the guidance law during the forming of the relative flying should be studied.
出处
《上海航天》
北大核心
2007年第4期13-16,22,共5页
Aerospace Shanghai
关键词
相对绕飞
轨道机动
非奇异根数
有限推力
非线性规划
Relative fly-around
Orbital maneuver
Nonsingular elements
Finite thrust
Nonlinear programming
