一种空间飞行器多飞行剖面下的最优配重方案确定方法  

A Method for Determining the Optimal Counterweight Scheme of Spacecraft with Multiple Flight Profile

作　　者：杨勇 黄蔚 张群 杨自鹏 刘宇哲 Yang Yong;Huang Wei;Zhang Qun;Yang Zi-peng;Liu Yu-zhe(Beijing Institute of Astronautical Systems Engineering,Beijing,100076)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《导弹与航天运载技术（中英文）》2022年第6期64-67,132,共5页Missiles and Space Vehicles

摘　　要：空间飞行器的横向质心偏差对于整个飞行任务中的制导、姿态控制以及分离都有着显著的影响,因此需要通过配重的方法对空间飞行器的横向质心进行控制。对于多飞行剖面的空间飞行器,适应所有飞行剖面的最优配重位置往往难以通过作图方法得到。因此提出了一种递进扫描的方法,可用于确定多飞行剖面下空间飞行器的最优配重方案,并对该方法进行了仿真验证,仿真结果表明该方法能够快速有效地得到最优配重位置。For spacecrafts,the horizontal deviation of center of mass has a significant impact on guidance,attitude control and separation throughout the mission.So it is necessary to control the center of mass of the spacecraft by counterweight.For spacecraft with multiple flight profiles,it is often difficult to obtain the optimal counterweight location which used for all flight profiles through the drawing method.Therefore,a method proposed for determining the optimal counterweight scheme of spacecraft with multiple flight profile by progressive scanning,and the method is verified by simulation.Simulation results show that the method can get the optimal counterweight location quickly and effectively.

关 键 词：空间飞行器 飞行剖面 配重 

分 类 号：V475.4[航空宇航科学与技术—飞行器设计]