摘要
针对多星近距离绕飞观测任务,建立了相对姿态轨道动力学模型,分别考虑了在椭圆、空间圆绕飞轨道上观测卫星的两种期望三角形编队构型,以观测卫星视线始终指向目标为期望姿态,采用基于四元数和角速度误差反馈的比例-微分控制律以及一种改进的基于人工势场法的制导方法相结合,对相对姿态及轨道进行控制。仿真结果表明:在控制律的作用下,绕飞过程中各观测卫星均能够有效地跟踪期望相对姿态和期望相对轨道;在空间圆绕飞轨道构型中,各观测卫星从初始同一位置出发后,在任意时刻3颗观测卫星构成的编队构型始终为正三角形,且正三角形的边长从零逐渐增大,最终等于期望正三角形构型的边长。
Aiming at the observation mission of multi-satellite proximity operation, dynamics models of relative attitude and orbit are established. Two kinds of desired triangular formation configurations of observation satellites in elliptical and space circular orbits are considered respectively. The desired attitude is designed that the observation satellite’s line of sight always points to the target satellite. The proportional-differential control law based on the quaternion and angular velocity error feedback and an improved guidance method based on artificial potential field method are used to control the relative attitude and orbit. The simulation results show that all observation satellites can effectively track the desired relative attitude and desired relative orbit under the action of the control law. In the triangular formation configuration of space circular orbit, after starting from the same initial position, the formation configuration of three observation satellites always keeps a regular triangle. Moreover, the side length of the regular triangle increases gradually from zero to finally the desired value.
作者
徐影
张进
于沫尧
许丹丹
XU Ying;ZHANG Jin;YU Moyao;XU Dandan(School of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;School of Aviation and Mechanical Engineering,Aviation Maintenance NCO Academy,Xinyang 464000,China)
出处
《中国空间科学技术》
EI
CSCD
北大核心
2019年第6期21-29,共9页
Chinese Space Science and Technology
基金
上海航天科技创新基金(SAST2017015)
国防科技大学科研计划(ZK17-03-21)
空间智能控制技术重点实验室开放基金(ZDSYS-2017-02)
关键词
多星
近距离观测
姿态控制
轨道控制
正三角形编队
multi-satellite
proximity observation
attitude control
orbit control
regular triangle formation
