椭圆轨道交会、悬停与绕飞的全状态反馈控制

发布时间：2018-12-11 15:19

【摘要】：面向大椭圆轨道航天器交会对接、编队伴飞以及在轨操控等空间应用的需求,对大椭圆轨道上航天器间的相对运动进行了分析与建模,采用幂级数法分别在脉冲推力和常值推力作用两种情况下对系统进行了近似求解。通过对系统解的变换以及对系统状态的重构,给出了大椭圆轨道上的三种交会制导律。脉冲推力作用假设下的脉冲制导类似近圆轨道的Hill制导方法。常值推力作用假设下的全状态反馈制导律则在交会制导、相对悬停和循迹绕飞控制的过程中实现了对相对位置和相对速度的同步控制。通过构造新的系统状态,改进的变系数全状态反馈制导律提高了相对速度的制导精度,降低了相对制导过程中的最大轨控加速度。三种制导律的制导效果通过数学仿真进行了校验和比较,文中给出的方法实现了椭圆轨道上相对交会制导、悬停保持和循迹绕飞控制。
[Abstract]:In order to meet the requirements of space applications such as rendezvous and docking of large elliptical orbit spacecraft, formation tracking and in-orbit control, the relative motion of spacecraft in large elliptical orbit is analyzed and modeled. The power series method is used to approximate the system in the case of impulse thrust and constant thrust respectively. By transforming the solution of the system and reconstructing the state of the system, three kinds of rendezvous guidance laws on the large elliptic orbit are given. The impulsive guidance under the assumption of impulse thrust is similar to the Hill guidance method of near-circular orbit. The full state feedback guidance law under the assumption of constant thrust effect realizes synchronous control of relative position and relative velocity in rendezvous guidance, relative hovering and tracking flight control. By constructing a new system state, the improved variable coefficient full-state feedback guidance law improves the guidance accuracy of relative velocity and reduces the maximum orbit control acceleration in the relative guidance process. The results of three guidance laws are compared with each other by mathematical simulation. The methods given in this paper are used to control the relative rendezvous guidance hovering and tracking flight in elliptical orbit.
【作者单位】：上海航天控制技术研究所;上海市空间智能控制技术重点实验室;
【分类号】：V448.2

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