以某储运发射箱为研究对象,为降低其空投着陆过程火箭弹冲击过载、避免推进剂损伤,确定了适用于发射箱空投的排气型气囊缓冲方式,并进行气囊参数设计与改进,研究其不同着陆姿态下的缓冲效果。基于气囊有限元算法(CV法)和空投过程基本假设建立含气囊缓冲空投系统有限元模型。分析其在不同着陆姿态下系统安全性,通过与无缓冲计算结果对比,进行缓冲效果评估。计算结果表明,采用气囊缓冲后,火箭弹最大过载下降87%左右,缓冲气囊能量效率满足设计要求,经推进剂裂纹计算,未出现裂纹扩展现象,缓冲效果明显。

The launch canister is designed to reduce the impact damage of the air drop rocket, and the launch canister is designed to reduce the impact damage of the air drop rocket. Based on the airbag finite element algorithm (CV method) and the basic assumptions of the airdrop process, established the finite element model of the airdrop system with airbag cushion. The system safety under different landing attitude is analyzed, and the buffer effect is evaluated by comparing with the calculation results without buffer. The calculation results show that after using air bag buffer, the maximum overload of rocket decreases by about 87%, and the energy efficiency of buffer air bag meets the design requirements. Through the calculation of propellant crack, there is no crack propagation, and the buffer effect is obvious.