运载火箭子级空中捕获仿真分析

doi:10.12305/j.issn.1001-506X.2026.10.27

系统工程与电子技术 ›› 2026, Vol. 48 ›› Issue (10): 3573-3579.doi: 10.12305/j.issn.1001-506X.2026.10.27

• 制导、导航与控制 • 上一篇

运载火箭子级空中捕获仿真分析

郭祖华¹^,², 翟建舒¹, 贺卫亮¹

1. 北京航空航天大学宇航学院，北京 102206
2. 天地往返高效运输技术全国重点实验室，北京 102206

收稿日期:2025-07-28 出版日期:2026-10-25 发布日期:2026-09-30
通讯作者: 郭祖华
作者简介:翟建舒（2001—），女，硕士研究生，主要研究方向为运载火箭总体设计
贺卫亮（1964—），男，研究员，博士，主要研究方向为伞翼飞行器技术
基金资助:
重大自然灾害监测预警与防范重点专项（2019YFC1510900）资助课题

Simulation analysis of capturing a launch vehicle stage in the air

Zuhua Guo¹^,², Jianshu Zhai¹, Weiliang He¹

1. School of Astronautics，Beihang University，Beijing 102206，China
2. State Key Laboratory of High-Efficiency Reusable Aerospace Transportation Technology，Beijing 102206，China

Received:2025-07-28 Online:2026-10-25 Published:2026-09-30
Contact: Zuhua Guo

摘要/Abstract

摘要：

针对运载火箭子级可能影响空中回收直升机飞行安全的问题，通过仿真研究了在空中钩取运载火箭子级时直升机飞行轨迹和缆绳拉力的变化情况。首先，建立直升机及火箭子级的运动模型；然后，设计直升机升力和缆绳拉力反馈控制，并采用粒子群优化（particle swarm optimal, PSO）算法在给定约束条件下整定反馈参数；最后，通过仿真求得了钩取过程中缆绳拉力的变化和直升机飞行轨迹的扰动。空中钩取时直升机的飞行速度是影响缆绳最大拉力和长度的主要因素；主动控制缆绳的收放，能够有效缓冲空中钩取导致的冲击载荷，缆绳越长，最大拉力越小。研究结果表明，文中提出的钩取方法可以保证直升机飞行安全。

关键词: 运载火箭回收, 空中捕获, 空中回收, 控制参数优化, 动力学仿真

Abstract:

In view of the potential issue that launch vehicle stages may affect the flight safety of aerial retrieval helicopters, the changes of helicopter flight trajectory and pull force of the rope when hooking a launch vehicle stage in air are studied by simulation. Firstly, motion equations of helicopter and rocket stage in flight profile are built. Secondly, feedback control laws for helicopter left force and pull force of rope are designed. The feedback parameters are optimized under given constraints by the particle swarm optimization （PSO） algorithm. Finally, the variations in pull force of rope and disturbances in helicopter trajectory during the hooking process are obtained by simulation. The helicopter flight velocity is the key factor for maximum rope pull force and length when hooking in the air. The impact load acting on helicopter when hooking in the air can be effectively eliminated through actively controlling the length of rope. The longer the rope, the smaller the maximum pulling force. Research results indicate that the hooking method proposed in the paper can ensure the safety of the helicopter flight.

Key words: launch vehicle recovery, aerial capturing, mid-air retrieval, control parameter optimization, dynamics simulation

中图分类号:

V 475.1

郭祖华, 翟建舒, 贺卫亮. 运载火箭子级空中捕获仿真分析[J]. 系统工程与电子技术, 2026, 48(10): 3573-3579.

Zuhua Guo, Jianshu Zhai, Weiliang He. Simulation analysis of capturing a launch vehicle stage in the air[J]. Systems Engineering and Electronics, 2026, 48(10): 3573-3579.

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参数	初值
$ {X_0} $/m	0
$ {Y_0} $/m	1 050
$ {V_{X0}} $/（m/s）	20
$ {V_{Y0}} $/（m/s）	0
$ {x_0} $/m	0
$ {y_0} $/m	1 000
$ {v_{x0}} $/（m/s）	0
$ {v_{y0}} $/（m/s）	−10

运载火箭子级空中捕获仿真分析

Simulation analysis of capturing a launch vehicle stage in the air

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