固体火箭发动机喷管组件过盈装配强度分析

为使各个组件间的间隙大小和均匀度得到保障,对固体火箭发动机喷管组件过盈装配强度进行分析.基于工程应用背景,对某标准试验发动机喉衬与喷管座过盈压配过程进行仿真分析,采用有限元模拟方法,对喷管体在加热和不加热两种情况下进行动力学和热力学分析.结果表明:采用对喷管体先加热后装配的方法,其装配面接触应力更小,更利于控制装配过盈量,保证喷管组件的装配质量.

Strength Analysis on Interference Assembling of Solid-propellant Rocket Engine Nozzle Component

In order to ensure the clearance and uniformity of the components, the interference assembly strength of the nozzle components of the rocket engine was analyzed. Based on the background of engineering application, the process of interference mounting between nozzle body and throat liner of certain type standard test engine is simulated and analyzed. Carry out the dynamic and thermodynamic analysis of the nozzle components under the conditions of heated and unheated by finite element method. The results show that the contact stress of the assembly surface is smaller, which is more conductive to control the assembly interference and ensure the assembly quality of the nozzle assembly if the nozzle body is heated before assembling.