目的 对一代伞兵战车缓冲气囊进行优化，设计出满足二代伞兵战车着陆安全的缓冲气囊。方法 基于现用的缓冲气囊，结合有限元仿真、试验设计，建立以气囊参数为设计变量、战车着陆冲击加速度峰值为目标函数的支持向量回归（SVR）模型。用遗传算法对现有气囊的宽度、高度、排气孔面积、排气孔爆破压强进行参数优化。结果 优化后的缓冲气囊系统将二代伞兵战车的冲击加速度峰值降低了73.4%，着陆减速过程变得平稳顺滑。结论 成功地对现有缓冲气囊的参数进行了优化改进，得到了适用于二代伞兵战车的缓冲气囊，并且为决策者提供了多种气囊设计方案。

The work aims to optimize the air bag of the first generation of airborne vehicle and design the air bag for the safe landing of the second generation of airborne vehicle. Based on the existing air bag and combined with the finite element simulation and experiment design, the support vector regression (SVR) model with the air bag parameters as design variables and the impact acceleration peak value for vehicle landing as objective function was established. Genetic algorithm was used to optimize the parameters of the existing air bag, including its width, height, exhaust vent area and burst pressure of exhaust vent. The optimized air bag reduced the impact acceleration peak of the second generation of airborne vehicle by 73.4% and made the deceleration process of landing smoother. Parameters of the current air bag have been optimized and improved successfully to get the air bag suitable for the second generation of airborne vehicle. In addition, lots of air bag design schemes have been provided for the decision-maker.