固体火箭发动机尾喷管用耐高温复合堵盖设计及性能研究

Design and performance of composite closure withhigh-temperature resistance for SRM nozzle

简要对比国内外固体火箭发动机常见的不同形式尾喷管堵盖设计方案,指出耐高温尾喷管堵盖在高超声速导弹固体火箭发动机上的发展方向,并基于此设计了一种耐高温尾喷管复合堵盖,详细介绍了其设计方法,并利用ABAQUS有限元软件对其进行了打开、受力和隔热性能三维数值仿真分析,且结合地面试验及飞行转级试验对其工作可靠性进行验证。结果表明:该复合堵盖地面冷流打开压强值处于1.65~1.85 MPa之间;在文中所述热环境工况下,复合堵盖倒角处的应力最大值为39.2 MPa,最高背温为38.5℃,设计方案可以满足某型号导弹对固体火箭发动机尾喷管堵盖结构和性能的使用要求,同时也可为其他有类似工况的高超声速导弹上的应用提供参考。

In this paper,designing schemes of different types of nozzle closure for solid rocket motor(SRM)at home and abroad were briefly compared,it is indicated that the closure with high-temperature resistance is the design direction for SRM nozzle of hypersonic missile.A kind of composite closure with high-temperature resistance for SRM nozzle was designed and the design scheme was introduced specifically.Meanwhile,opening,stress and heat insulation performance of the composite closure were 3D numerically simulated by means of ABAQUS finite element software.The reliability of composite closure was verified by the ground test and the flight test.The results show that opening pressure of composite closure is from 1.65 MPa to 1.85 MPa under cold flow ground test;Under the thermal environment conditions described in this paper,the maximum stress at the chamfer of composite closure is 39.2 MPa;the highest back temperature is 38.5℃;The closure design scheme can meet the requirements of structure and performance for nozzle closure of a certain missile.It can also provide some reference for the application of other hypersonic missiles under similar working conditions.