直升机安全气囊约束系统仿真及试验研究

安全气囊作为降低直升机坠落伤亡风险的主要技术，能有效减轻飞行员在坠撞过程中的二次伤害。本文以某型号直升机为研究对象，参照汽车碰撞相关试验要求，开展气囊折叠及约束系统匹配设计，建立驾驶舱整机有限元仿真模型，通过气囊静态起爆试验和直升机整机跌落碰撞试验验证模型的有效性。通过灵敏度分析确定主要结构优化参数，并设计四因素四水平正交试验完成约束系统优化。结果表明，飞行员综合损伤值WIC减少8.91%，对飞行员的保护效果提高，为直升机被动安全领域提供研究基础。

Simulation and Experimental Research of Helicopter Airbag Restraint System

As the main technology to reduce the risk of casualties in helicopter crash, airbag can effectively reduce the secondary injuries of pilots in the process of crash. In this paper, a certain type of helicopter is taken as the research object, and the matching design of airbag folding and restraint system is carried out according to the requirements of automobile crash test, and the finite element simulation model of cockpit complete machine is established. The effectiveness of the model is verified by airbag static initiation test and helicopter complete machine drop crash test. The main structural optimization parameters were determined by sensitivity analysis, and four-factor and four-level orthogonal tests were designed to optimize the constraint system. The results show that the comprehensive damage value WIC of pilots is reduced by 8.91%, and the protective effect of pilots is improved, which provides the research basis for the passive safety field of helicopters.