尾翼封闭腔体抽铆可行性试验研究

Feasibility Test Research on Riveting Closed Cavity of Empennage

针对火箭尾翼封闭腔体难操作的问题,开展单面抽芯铆接可行性试验研究。通过剪切、拉脱和剥离试验的验证,将3.2单面抽芯铆钉与3铝合金铆钉的载荷进行对比分析。研究发现,采用单面抽芯铆钉连接的试件最大剪切拉载荷高于尾翼现用铆钉的连接试件。尾翼在使用过程中主要承受飞行法向压力载荷和飞行过载,单面抽芯铆钉的连接强度和铆接质量能够满足使用要求。

Aiming at the problem of difficult operation of rocket empennage enclosed cavity,a feasibility test study of single-sided blind riveting was carried out.Through the verification of shearing,pull-off and peeling tests,the load of3.2 single-sided blind rivets and3 aluminum alloy rivets are compared and analyzed.The study found that the maximum shear tensile load of the specimens connected by single-sided blind rivets is higher than that of the specimens connected by empennage’s current rivets.Empennage is mainly subjected to flight normal pressure load and flight overload during use.The connection strength and riveting quality of single-sided blind rivets can meet the requirements of use.