某型固体火箭发动机喷管泄压结构设计与试验验证

Design and Experimental Verification of Pressure Relief Structure of Solid Rocket Motor Nozzle

针对固体火箭发动机喷管的泄压技术要求,提出了环向应力槽喷管泄压方案。首先利用ANSYS软件对泄压结构进行结构静力有限元分析;然后对泄压结构进行参数化优化设计,初步筛选了泄压方案的结构尺寸;最后,采用水压试验和动态点火试验对环向应力槽泄压结构进行了验证,最终确定了环向应力槽的几何结构尺寸,验证了固体火箭发动机喷管环向应力槽泄压结构的有效性。

According to the technical pressure relief requirements of solid rocket motor nozzle,a pressure relief scheme based on the circumferential stress groove nozzle is put forward in this paper.Firstly,the structural static finite element analysis is carried out by using ANSYS software;then the parameter optimization design of pressure relief structure is conducted;and the structural dimensions of the pressure relief scheme are preliminarily screened.Finally,the pressure relief structure of circumferential stress groove is verified by hydraulic pressure test and dynamic ignition test,thus the geometric dimensions of the circumferential stress groove are confirmed,which shows the validity of the pressure relief structure of the circumferential stress groove of the solid rocket motor nozzle.The conclusions above in this paper can provide some important guidance for design of the pressure relief structure of solid rocket motor nozzle.