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目的解决缓冲气囊的研制周期长、成本高而设计效果却不够理想的问题。方法针对这个问题,对缓冲气囊的着陆缓冲过程进行解析建模,然后通过参数的无量纲化,将缓冲气囊的解析计算模型转化成无量纲动力学模型。借助缓冲气囊参数匹配图,根据试验需求对气囊缓冲系统进行匹配设计,然后采用有限元方法对气囊缓冲系统进行建模分析。结果搭建了气囊跌落缓冲试验系统,进行了气囊跌落缓冲试验,通过试验验证了参数匹配方法的有效性,并利用试验数据对有限元仿真计算结果进行了验证,配重平台最大加速度和气囊最大压强的误差分别为1.6%和3.1%。结论有限元仿真的精度可以满足分析要求,基本反映了实际的气囊缓冲特性。
Objective To solve the problem of long development cycle of buffer airbag, high cost and unsatisfactory design effect. Aiming at this problem, this paper analyzes and constructs the landing cushioning process of the buffer airbag, and then transforms the analytical model of the buffer airbag into a non-dimensional dynamic model through dimensionlessization of the parameters. With the matching chart of buffer airbag parameters, the airbag cushioning system was designed and matched according to the test requirements, and then the airbag cushioning system was modeled and analyzed by the finite element method. Results The airbag fall-off test system was built and the airbag drop-down test was carried out. The validity of the parameter matching method was verified by the test. The results of the finite element simulation were verified by the test data. The maximum acceleration of the weight platform and the maximum airbag pressure The errors are 1.6% and 3.1% respectively. Conclusion The accuracy of finite element simulation can meet the analytical requirements, basically reflecting the actual airbag cushioning properties.