Page 203 - 《爆炸与冲击》2026年第11期

第 46 卷 第 11 期 爆 炸 与 冲 击 Vol. 46, No. 11
2026 年 11 月 EXPLOSION AND SHOCK WAVES Nov., 2026

DOI：10.11883/bzycj-2025-0148

大载重吊落式缓冲气囊设计及多目标优化 *

翟政博 ，杨 臻 ，王端奇 ，刘 斌 ，李茂林 ，刘万川 4
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（1. 中北大学，山西 太原 030051；
2. 杭州智元研究院有限公司，浙江 杭州 310013；
3. 中国北方车辆研究所，北京 100072；
4. 建设工业集团（云南）股份有限公司，重庆 404100）
摘要： 针对大载重无人平台吊落式着陆的冲击防护问题，设计了一种实现安全着陆的缓冲气囊系统。基于理论
模型初步确定气囊几何参数和排气孔面积，利用控制体积法建立有限元仿真模型，模拟气囊缓冲过程。通过单参数分
析，揭示了排气孔尺寸、临界排气压力、气囊底面积及高度对缓冲性能的影响规律，发现上述参数在降低最大过载与
提升比吸能之间存在冲突。为解决此问题，采用最优拉丁超立方设计采样，结合神经网络构建目标函数代理模型，并
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集成 NSGA-Ⅱ遗传算法进行多目标优化。优化结果表明，当排气孔面积为 3 952 mm 、临界排气压力为 158 kPa、气囊底
面积为 1.08 m 时，最大过载从 16.8g 降至 14.5g，比吸能保持在 1 529 J/kg。试验显示最大过载试验值为 15.2g，与仿真结
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果误差仅为 4.8%，证实了优化方案的有效性。
关键词： 大载重无人平台；缓冲气囊；冲击动力学；多目标优化
中图分类号： O389; TH122 国标学科代码： 13035 文献标志码： A

Design and multi-objective optimization of heavy-load lifting buffer airbag

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ZHAI Zhengbo , YANG Zhen , WANG Duanqi , LIU Bin , LI Maolin , LIU Wanchuan 4
（1. North University of China, Taiyuan 030051, Shanxi, China;
2. Zhiyuan Research Institute, Hangzhou 310013, Zhejiang, China;
3. China North Vehicle Research Institute, Beijing 100072, China;
4. Jianshe Industry Group (Yunnan) Co., Ltd., Chongqing 404100, China）

Abstract: To address the challenges of rapid deployment for heavy-duty unmanned platforms and impact protection during
drop-landing, a buffer airbag system was designed to ensure the safe landing of the unmanned platform. First, theoretical
modeling was used to preliminarily determine the geometric parameters of the buffer airbag and the size of the vent holes. A
finite element simulation model that included the buffer airbag, the unmanned platform and the ground was established using
the control volume method (CVM) to simulate the cushioning process of the airbag. The impact dynamics response during the
landing attenuation process was analyzed, and the specific energy absorption (SEA) of the buffer airbag system was introduced
to evaluate its cushioning performance. The analysis results indicate that during the landing buffer process, the unmanned
platform reached a maximum overload value of 16.8g at 0.06 s, and the platform velocity reached a post-rebound maximum of
0.79 m/s at 0.1 s. At 0.18 s, the platform shifted laterally due to the center of gravity, and one side of the platform first
contacted the ground. This led to fluctuations in overload value and velocity, but the overall landing process remained stable.
The calculated SEA of the buffer airbag system was 1 527 J/kg. Using the control variable method, the influence of key
parameters on the buffer performance of the airbag was analyzed, revealing the effects of vent hole size, critical exhaust

* 收稿日期： 2025-05-21；修回日期： 2025-10-10
基金项目： 瞬态冲击技术重点实验室基金（JCKY2023209C003）
第一作者： 翟政博（2000－ ），男，硕士研究生，sf20230102@st.nuc.edu.cn
通信作者： 杨 臻（1965－ ），男，博士，教授，yzhen@nuc.edu.cn

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