论文部分内容阅读
为了提高固体火箭发动机衬管耐高温、耐冲刷的能力,解决发动机壳体烧蚀问题,对其复合材料衬管进行了热压罐成型工艺研究。优化其预浸料制备、缠绕预成型和热压罐固化成型等工艺过程及工艺参数,并对生产的衬管进行材料物理性能和力学性能检测,对装配发动机进行发动机使用性能的考核试验。试验结果表明,按热压罐成型工艺生产的复合材料衬管完全能够满足其材料性能要求和发动机的使用性能及质量要求,圆满解决了发动机耐烧蚀的关键技术问题。
In order to improve the heat resistance and scour resistance of the solid rocket motor liner and to solve the ablation problem of the engine case, the autoclave forming process of the composite liner was studied. Optimize its prepreg preparation, pre-winding and autoclave curing molding process and process parameters, and the production of liner material physical and mechanical properties of the test, the assembly of the engine engine performance test. The test results show that the composite liner produced by the autoclave molding process can fully meet the material performance requirements and engine performance and quality requirements, and satisfactorily solve the key technical problems of engine ablation resistance.