宇航学报 ›› 2022, Vol. 43 ›› Issue (9): 1152-1162.doi: 10.3873/j.issn.1000-1328.2022.09.003

• 飞行器设计与力学 • 上一篇    下一篇

索式火箭回收着陆系统缓冲装置设计与分析

张欢,张成,宋晓东   

  1. 1. 北京理工大学宇航学院,北京 100081; 2. 北京理工大学飞行器动力学与控制教育部重点实验室,北京 100081
  • 收稿日期:2022-03-02 修回日期:2022-05-15 出版日期:2022-09-15 发布日期:2022-09-15
  • 基金资助:
    国家自然科学基金(11872108);中国博士后科学基金资助项目(2021M690391)

Design and Analysis of Buffer Device of Cable System for Reusable Rocket Recovery and Landing

ZHANG Huan, ZHANG Cheng, SONG Xiaodong   

  1. 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2. Key Laboratory of Dynamics and Control of Flight Vehicle (Beijing Institute of Technology), Ministry of Education, Beijing 100081, China
  • Received:2022-03-02 Revised:2022-05-15 Online:2022-09-15 Published:2022-09-15

摘要: 针对索式火箭回收着陆系统中摩擦缓冲装置的缓冲能力和调节能力有限的问题,提出了一种基于最小二乘法和系统动力学特性的液压缓冲装置反问题设计方法。该方法通过对液压缓冲装置中控制阀凸轮外形和储能器初始压强的设计来调节着陆火箭运动学特性,使火箭按照特定的运动学特性在有限的缓冲位移内减速至静止稳定且缓冲加速度最小。对索式火箭回收着陆系统建立精准高效的多体动力学模型,并针对不同的工况进行仿真校验。仿真结果表明根据所提反问题设计方法设计的索式火箭回收着陆系统能够按照特定的运动学特性减速缓冲着陆火箭,具有较强的减速缓冲能力;针对不同质量和着陆位置偏差的着陆火箭,具有自动调整液压阻力保持火箭相同的运动学特性的能力。

关键词: 可重复使用火箭, 着陆系统, 多体动力学, 液压缓冲, 反问题设计

Abstract: In view of the limited buffer capacity and adjustment capacity of friction buffer in the cable system for the reusable rocket landing, an inverse problem design method of hydraulic buffer device based on least square method and system dynamic characteristics is proposed. This method can achieve the specific kinematic characteristics of the landing rocket by adjusting the cam shape of the control valve and the initial pressure of the accumulator in the hydraulic buffer device, enabling the rocket to land safely and stably under the limited buffer displacement and the minimum buffer acceleration. The accurate and efficient multibody dynamics model of the proposed system is established. The simulation calculations are carried out under different working conditions. The simulation results show that the hydraulic buffer device designed according to the proposed method can decelerate and buffer the landing rocket according to specific kinematic characteristics, and has strong deceleration and buffer ability. For the landing rocket with different mass and landing position deviation, it has the ability to automatically adjust hydraulic resistance to keep the same kinematic characteristics of the rocket.

Key words: Reusable rocket, Landing system, Multibody dynamics, Hydraulic buffer, Inverse problems

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