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目的研究航天服关节气密层的失效形式,分析并试验研究气密层成型工艺、材料、结构形态对气密层活动寿命的影响。方法观察气密层破损处的电镜扫描结果与气密层运动状态分析失效形式,利用对比试验分析各个因素对关节寿命影响,对各个因素的影响程度利用Bayes公式进行修正。结果气密层破损处位于褶皱产生处,周边无明显摩擦痕迹,冷粘接、热合成型样件活动寿命3万次左右,整体成型样件寿命达到10万次。结论得到了样件的活动寿命,气密层失效形式为弯折挤压失效,对气密层寿命影响因素的先验影响程度进行了矫正,结构形态的影响占有更大比例。验证了聚氨酯整体成型工艺的可行性,为先进舱外航天服关节研制提供气密层设计依据。
Aim To study the failure modes of airtight joint of a spacesuit joint, analyze and test the influence of the airtight layer forming process, material and structure on the service life of the airtight joint. Methods Electron microscopy results of the airtight layer damage and failure modes of the airtight layer motion state were observed. The influence of each factor on the life of the joint was analyzed by the comparative test. The degree of influence on each factor was corrected by the Bayes formula. Results The airtight layer is located at the place where folds occur. There is no obvious friction mark on the periphery. The life of cold bonding and hot composite samples is about 30,000 times, and the life of the whole forming sample reaches 100,000 times. Conclusions The active life of the sample is obtained. The failure mode of the airtight layer is the bending and extrusion failure. The a priori influence degree of the life of the airtight layer is corrected, and the influence of the structural morphology occupies a larger proportion. The feasibility of the polyurethane molding process was verified, and the inner liner was designed to provide the basis for the development of advanced spacecraft suits.