摘要
针对小卫星在大型航天器上分离空间受限的问题,采用了小卫星垂直向下开展分离试验的方法。利用小卫星在大型航天器上开展垂直向下的分离试验,获得高速摄影靶标的坐标,推导建立了计算零重力下小卫星有关分离参数的函数模型,得到了零重力下小卫星的分离速度、分离角速度及姿态角。基于蒙特卡罗法开展了小卫星分离运动学仿真分析,仿真数据与试验计算数据能够相吻合,验证了上述函数模型的正确性及试验方法的有效性,该分离试验方法可用于同类型的小卫星。
A method for the vertical downward separation experiment of small satellites is adopted to solve the problem of limited space for the separation of a small satellite from a large spacecraft.Based on the coordinates of highspeed photographic target obtained from the vertical downward separation experiment of a small satellite on a large spacecraft,a calculation model for the separation parameters of the small satellite under zero gravity is derived and established,and the separation velocity,separation angular velocity,and attitude angle of the small satellite are obtained.Based on the Monte Carlo method,a simulation analysis for the separation kinematics of the small satellite is carried out.The simulation results obtained are consistent with the separation experiment data,which verifying the correctness of the calculation model and the effectiveness of the experiment method.This separation experiment method can be used for similar small satellites.
作者
易凌宇
余运锋
杜善亮
王巍
袁勇
慕忠成
吴树范
YI Lingyu;YU Yunfeng;DU Shanliang;WANG Wei;YUAN Yong;MU Zhongcheng;WU Shufan(Aerospace System Engineering Shanghai,Shanghai 201109,China;School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China)
出处
《上海航天(中英文)》
2025年第3期80-87,共8页
Aerospace Shanghai(Chinese&English)
基金
国家重大工程专项资助项目(22GFB-KG08-689)。
关键词
小卫星
大型航天器
分离试验
零重力
分离参数
分离运动学
small satellite
large spacecraft
separation experiment
zero gravity
separation parameter
separation kinematics
