中国空间科学技术

中国空间科学技术 ›› 2026, Vol. 46 ›› Issue (2): 82-89.doi: 10.16708/j.cnki.1000-758X.2026.0026

• 载人月球探测专刊 • 上一篇    下一篇

梦舟载人飞船气囊缓冲过程着陆稳定性提升方法

王国庆1,2,*，竺梅芳1,2，苏浩东1,2，贾贺1,2，雷江利1,2，贡伊明1,2   

  1. 1.北京空间机电研究所，北京100094
    2.中国航天科技集团有限公司航天进入、减速与着陆技术实验室，北京100094
  • 收稿日期:2025-10-17 修回日期:2025-12-11 录用日期:2025-12-26 发布日期:2026-03-20 出版日期:2026-03-31

Methods for improving landing stability during airbag buffering process of Mengzhou manned spacecraft

WANG Guoqing1,2,*，ZHU Meifang1,2，SU Haodong1,2，JIA He1,2，LEI Jiangli1,2，GONG Yiming1,2   

  1. 1.Beijing Institute of Space Mechanics & Electricity，Beijing 100094,China
    2.Laboratory of Aerospace Entry, Descent and Landing Technology，Beijing 100094,China
  • Received:2025-10-17 Revision received:2025-12-11 Accepted:2025-12-26 Online:2026-03-20 Published:2026-03-31

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摘要： 为提升梦舟载人飞船气囊缓冲过程的着陆稳定性，从而提高任务的可靠性、安全性，开展相关机理及提升方法研究。基于LS-DYNA建立组合式缓冲气囊与返回舱的有限元模型，采用控制体积法仿真模拟气囊缓冲时内部气体压缩做功过程；对气囊缓冲过程开展动力学机理分析，进一步明确对于着陆稳定性产生主要影响的因素；提出基于差异化主动控制的过载压力联合控制新方法，以减小缓冲过程中产生的倾倒力矩；通过多工况仿真对比与全尺寸模型试验相结合的方式，对该方法的有效性进行了验证。通过有限元仿真结果明确了缓冲过程中返回舱着陆稳定性的主要影响因素，即前后气囊压力差和气囊对舱体的拉力，宏观表现为：在其他条件固定的前提下，“抬头”角度越大着陆稳定性越差；设计了3种新控制方案，并与传统过载控制方案开展多工况对比分析，据此选取最优方案，实现在 “抬头”着陆工况下舱体最大倾斜角度下降10.4%~18.2%。深入分析了气囊缓冲过程着陆稳定性主要影响因素及趋势，并基于气囊缓冲过程机理对传统过载控制方案进行了优化，显著提升不同条件下的着陆稳定性，可为后续大型载人飞船气囊缓冲系统着陆稳定性设计优化提供参考。

关键词: 梦舟载人飞船, 缓冲气囊, 着陆稳定性, 差异化主动控制, 过载-压力控制, 全尺寸模型试验

Abstract: To improve the landing stability of the Mengzhou manned spacecraft during the airbag buffering process, thereby enhancing the reliability and safety of the mission, relevant research on the underlying mechanisms and improvement methods is conducted. A finite element model (FEM) of the combined buffer airbag and the spacecraft reentry module is established based on LS-DYNA. The control volume method (CVM) is adopted to simulate the process of internal gas compression and work done during airbag buffering. Furthermore, a dynamic mechanism analysis of the airbag buffering process is conducted; combined with simulation results, the main factors affecting landing stability are further clarified. A novel overloadpressure combined control method based on differentiated active control is proposed: on the basis of the traditional overload control scheme, pressure data are incorporated, and the overturning moment generated during the buffering process is reduced through differentiated active control. Finally, the effectiveness of the proposed method is verified by the combination of multi-condition simulation comparison and full-scale model tests. The finite element simulation model of the reentry module-airbag assembly is obtained. The main factors affecting the landing stability of the reentry module during the buffering process are clarified, namely the pressure difference between the front and rear airbags and the tensile force of the airbags on the module. This is macroscopically manifested as: with other conditions fixed, the larger the noseup angle, the worse the landing stability. Three new control schemes are designed, and multi-condition comparative analysis is conducted between the traditional overload control scheme and the three new ones, followed by the selection of the optimal scheme. This scheme achieves a reduction in the maximum tilt angle of the module by 10.4%-18.2% respectively under the nose-up conditions, and the effectiveness of the new control scheme is verified through tests. An in-depth analysis is conducted on the main influencing factors and their tendencies regarding landing stability during the airbag buffering process. Based on the mechanism of the airbag buffering process, the traditional overload control scheme is optimized, which significantly improves the landing stability under various conditions. This research can provide reference for the design and optimization of landing stability in the airbag buffering system of subsequent large-scale crewed spacecraft.

Key words: Mengzhou manned spacecraft, buffering airbag, landing stability, differentiated active control, overload-pressure combined control, full-scale model test