北京大学学报自然科学版 ›› 2025, Vol. 61 ›› Issue (3): 411-419.DOI: 10.13209/j.0479-8023.2024.037

上一篇    下一篇

非对称构型的大倾角星箭弹簧分离装置动力学研究

刘佳佳1,2, 李嘉权3, 王雪峰3, 高利军2, 龚林辉2, 刘才山3,†   

  1. 1. 西北工业大学无人系统技术研究院, 西安 710072 2. 北京宇航系统工程研究所, 北京 100076 3. 北京大学工学院航空航天工程系, 湍流与复杂系统国家重点实验室, 北京 100871
  • 收稿日期:2024-03-29 修回日期:2024-05-04 出版日期:2025-05-20 发布日期:2025-05-20
  • 通讯作者: 刘才山, E-mail: liucs(at)pku.edu.cn
  • 基金资助:
    国家自然科学基金(U24B6005)资助

Dynamics Study on Spring Separation Device of the Asymmetric Satellite-Rocket with Large Inclination

LIU Jiajia1,2, LI Jiaquan3, WANG Xuefeng3, GAO Lijun2, GONG Linhui2, LIU Caishan3,†   

  1. 1. Unmanned System Research Institute, Northwestern Polytechnical University, Xi’an 710072 2. Beijing Institute of Aerospace Systems Engineering, Beijing 100076 3. State Key Laboratory of Turbulence and Complex Systems, Department of Aeronautics and Astronautics, College of Engineering, Peking University, Beijing 100871
  • Received:2024-03-29 Revised:2024-05-04 Online:2025-05-20 Published:2025-05-20
  • Contact: LIU Caishan, E-mail: liucs(at)pku.edu.cn

PDF

摘要：

为更好地控制卫星运动状态并实现精确入轨, 评估卫星火箭分离过程中卫星对系统物理参数的敏感性, 针对捷龙三号遥二卫星发射任务中的星箭非轴对称构型布局, 建立星箭弹簧分离装置的二维简化动力学模型, 将复杂的三维动力学问题简化为平面动力学问题, 降低系统的自由度, 简化了模型计算难度。仿真结果表明, 通过适当配置内置弹簧的预紧力和界面摩擦性质, 可以有效地控制卫星入轨的初始姿态。研究结果可为星箭弹簧分离装置的优化设计提供理论指导。

关键词: 星箭分离, 非对称构型, 弹簧分离装置, 动力学建模

Abstract:

In order to better control the motion state of the satellite and achieve precise orbit insertion, it is necessary to assess the sensitivity of the satellite to the physical parameters of the system during the satellite rocket separation process. This paper proposes a simplified two-dimensional dynamic model for the complex layout scheme of separation of large angle asymmetric star rocket joint surfaces, which simplifies the complex three-dimensional dynamic problem into a planar dynamic problem, reduces the system’s degrees of freedom, and greatly simplifies the computational difficulty of the model. The simulation results indicate that by appropriately configuring the preload of built-in springs and interface friction properties, the initial attitude of satellite orbit insertion can be effectively controlled. The research results can provide guidance for the parameter design of satellite-rocket separation devices.

Key words: satellite-rocket separation, asymmetric configuration, spring separation device, dynamic modeling

版权所有 © 《北京大学学报（自然科学版）》编辑部
技术支持：北京玛格泰克科技发展有限公司