考虑摄动影响的连续推力轨道修正制导方法研究  

Study on Continuous Thrust Orbit Correction Guidance Considering the Perturbations

作　　者：周姜滨[1] 叶松[1] 张华明[1] Zhou Jiangbin;Ye Song;Zhang Huaming(Beijing Aerospace Automatic Control Institute,Beijing 100584,China)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2018年第4期19-22,共4页Aerospace Control

摘　　要：为较好地消除在轨空间飞行器的轨道偏差,提出了一种考虑摄动影响的连续推力轨道修正制导方法。将轨道修正问题转换为二体假设条件下的兰伯特变轨问题,求解所需要的速度增量,考虑地球非球形引力、大气阻力、日月引力及太阳光压等摄动因素计算在与该速度增量等效的连续推力作用下空间飞行器的实际位置,利用实际位置与目标位置的偏差构造虚拟目标点,通过迭代计算给出连续推力轨道修正制导指令,空间飞行器接收并执行该指令进行轨道修正。仿真表明该轨道修正制导方法制导精度较高。In order to effectively eliminate the orbit error of on-orbit spacecraft,a continuous thrust orbit correction guidance approach is proposed in this paper. Firstly,the orbit correction problem is treated as two-body Lambert problem to obtain the corresponding velocity increment. Secondly,the actual position of the spacecraft is computed under the continuous thrust which is equivalent to the velocity increment by considering the perturbations,such as the non-spherical gravitation,the atmospheric drag,the third body gravitation and the solar radiation pressure,and then a virtual object point is constructed by using the error between the actual position and the object position. Finally,continuous thrust orbit correction guidance is completed by iterative computation by utilizing the virtual object point. Simulation results show the high guidance precision of the proposed approach.

关 键 词：连续推力 轨道修正 兰伯特问题 制导方法 

分 类 号：V448.234[航空宇航科学与技术—飞行器设计]