Page 204 - 《爆炸与冲击》2026年第11期

第 46 卷 翟政博，等： 大载重吊落式缓冲气囊设计及多目标优化 第 11 期

pressure, airbag base area and airbag height on the performance of the buffer. The study found that the influence of airbag
height on the two key indicators (maximum overload and SEA) was consistent, presenting no optimization conflict. However,
after the height exceeded 0.37 m, a diminishing returns effect appeared. When the other three variables were changed
individually, they caused a conflict between the goals of minimizing maximum overload and maximizing SEA, making it
impossible to improve both simultaneously through independent optimization. To resolve this issue, an optimal latin hypercube
design was used for sampling, and a three-layer neural network was employed to construct proxy models for the objective
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functions. The root mean square error (RMSE) and coefficient of determination (R ) of these two types of proxy models were
calculated to evaluate their regression performance. The NSGA-Ⅱ genetic algorithm was integrated for multi-objective
optimization. The results showed that for the proxy models predicting maximum overload and SEA, the RMSEs were 0.489 5
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and 0.726 2, and the R values were 0.983 3 and 0.936 4, respectively. All R values were greater than the industry benchmark
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of 0.9, indicating high reliability of the proxy models. When the vent hole area was 3 952 mm , the critical exhaust pressure, the
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airbag base area were 158 kPa and 1.08 m , respectively. Meanwhile, the maximum overload was reduced from 16.8g to 14.5g,
and the SEA remained stable at 1 529 J/kg. Based on the characteristics of the airbag's buffer process, a gantry crane-based
simulation test method for unmanned platform airdrop and lifting was designed. A piezoelectric IEPE acceleration sensor was
used to measure the overload value of the unmanned platform. Experimental verification showed that the measured maximum
overload value was 15.2g, with a mere 4.8% error compared to the simulation result, confirming the correctness of the
optimization scheme. This research provides efficient and low-cost design technical support for the soft landing systems of
unmanned platforms, enhancing the safety and efficiency of operational deployment.
Keywords: heavy load unmanned platform; buffer airbag; impact dynamics; multi-objective optimization

作为一种可空投的独立武器系统，集智能化、通信技术与信息处理能力于一体的模块化无人平台，
其快速部署能力及安全着陆保障对作战效能提升至关重要。鉴于无人平台难以承受高过载冲击，且需
快速部署于关键战区，因此设计一种吊落式缓冲气囊，以解决着陆冲击防护问题提升作战部署的安全性
与效率，具有关键意义。
在缓冲气囊的研发初期，为应对试验验证环节的高成本问题，工程领域通常优先采用数值仿真技术
对其缓冲效能及设计可行性进行预测分析。Wang 等 [1] 提出了控制体积法（control volume method,
CVM），并将其应用于缓冲气囊的充气展开和受力分析。He 等 [2] 利用结构有限元模型与冲击动力学有
限元模型开发了一种回收模块和缓冲气囊系统有限元模型的分层更新方案。Wang 等 [3] 建立了某车辆
缓冲气囊系统有限元模型并进行试验验证。Zhou 等 [4] 提出了一种新型圆柱形缓冲气囊折叠方法，并通
过有限元分析验证了该方法的正确性。Dmitri 等 [5] 使用任意拉格朗日-欧拉方法和 CVM 模拟了胸部气
囊冲击人体的测试。
学者对气囊的缓冲性能进行了大量研究，杨占华等 [6] 和石坚等 [7] 建立了某空投车辆缓冲气囊有限
元仿真模型，研究了正常工况和极限工况下的着陆缓冲过程，分析了着陆缓冲过程中车辆的冲击动力学
特性和气囊缓冲性能。张鹏飞等 [8-9] 对大载重航天器组合式缓冲气囊的缓冲过程进行了有限元仿真分
析，采用最优拉丁超立方选取仿真样本点，进行了多目标遗传优化设计，优化了气囊的初始设计参数。
Liu 等 [10] 建立了缓冲气囊座椅的数值模型并进行试验验证，构建了基于概率和区间混合模型的多目标可
靠性设计优化，并利用遗传算法求解，提出一种基于概率和区间模型的缓冲气囊座椅缓冲特性可靠性设
计优化方法。洪煌杰等 [11] 基于有限元法和 CVM 对缓冲气囊开展了有限元仿真分析，通过拉丁超立方设
计构建代理模型，利用多目标遗传算法对气囊高度、宽度及排气孔面积进行了参数优化。鲁超宇等 [12] 对
圆柱形组合气囊进行了多工况仿真并与传统气囊对比分析，分析了单参数对气囊缓冲性能的影响，采用
因子法优化了内气囊直径和外气囊排气孔面积。付新华等 [13] 对战车载人空投缓冲气囊进行有限元仿真
分析并通过空投试验校验，开展复杂着陆工况仿真分析，评估了复杂着陆情况下对人体各部位损伤。可
以看出，目前对车辆、航天器、缓冲座椅着陆过程中冲击动力学响应特性、气囊缓冲性能或优化气囊参

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