航空航天发动机自锁螺母结构研究

Study on Structure of Self-locking Nut of Aerospace Engine

为解决航空航天紧固件的锁紧技术问题,分别从自锁螺母收口形式、工况下紧固连接件的受力情况开展理论分析。通过对自锁螺母结构采取不同的收口变形方式及变形量的对比分析,获得适合紧固件使用的最优收口工艺参数。采用有限元分析对自锁螺母在结构设计及变形受力分布情况进行模拟。研究结果表明,采用单面最大误差±0.035 mm与加工1/3控制原则对比进行选用是比较科学的方法。

In order to solve the locking technical problems of aerospace fasteners,theoretical analysis was carried out from the closing form of self-locking nuts and the force of fastening connectors under working conditions.The optimum closing process parameters for fasteners were obtained by comparing and analyzing different closing deformation modes and deformation quantities of self-locking nut structure.The finite element analysis model was used for distribution of self-locking nuts.The results show that it is a scientific method to select and compare the maximum error of single side±0.035mm with the control principle of 1/3 of machining.