补偿型航天器分离装置设计
Design of Compensated Spacecraft Separation Device
丁星 1尚宇晴 1张晓宏 1张兴勇 1华洲1
作者信息
- 1. 上海机电工程研究所,上海 201109
- 折叠
摘要
为了满足新一代航天器小型化及分离姿态可控的需求,确保航天器的可靠分离,提出了一种补偿型航天器分离装置设计方法.通过ADAMS软件建立了分离装置动力学模型,对其分离特性进行了研究及试验验证,评估了该分离装置对分离姿态的补偿效果.研究结果表明:合理调整各弹簧装置的空间分布位置,可完全补偿弹簧推力偏差、航天器质心偏移带来的分离扰动,有效调节航天器分离姿态.相比于常规分离装置,其质量及占用空间可降低30%以上.研究结果对小型航天器分离装置设计具有重要的工程参考价值.
Abstract
In order to meet the needs of miniaturization and controllable separation attitude of the new generation of spacecraft,ensure the reliable separation of spacecraft,a compensated spacecraft separation device is proposed.The dynamic model of the separation device is established by ADAMS software,its separation characteristics are studied and tested,and the compensation effect of the separation device on the separation attitude is evaluated.The results show that the separation disturbance caused by spring thrust deviation and centroid deviation of spacecraft can be significantly reduced by adjusting the spatial distribution position of spring device,so as to effectively adjust the separation attitude.Compared with the conventional separation device,its mass and space occupancy can be reduced by more than 30%.The research results have important engineering reference value for the design of small spacecraft separation device.
关键词
分离装置/小型航天器/分离姿态/补偿Key words
separation device/small spacecraft/separation attitude/compensation引用本文复制引用
基金项目
国家重点研发计划(2022YFB3705304)
中国航天科技集团钱学森青年创新基金(QXSCXJJ2023-048)
出版年
2024
NETL
NSTL
万方数据