固体火箭发动机长尾喷管烧蚀实验研究  

Ablation test for tailpipe nozzle of solid rocket motor

作　　者：陈剑[1] 魏祥庚[1] 李江[1] 何国强[1] 

机构地区：[1]西北工业大学燃烧流动与热结构国家级重点实验室,西安710072

出　　处：《固体火箭技术》2010年第1期34-35,40,共3页Journal of Solid Rocket Technology

摘　　要：通过研究长尾喷管烧蚀机理,建立了一套模拟长尾喷管烧蚀的实验方法,设计了研究长尾喷管发动机烧蚀性能的实验装置,并进行了正常状态和过载状态下的长尾喷管烧蚀实验,同时获得了烧蚀实验数据及烧蚀形貌。通过建立的数值计算模型,开展了对长尾喷管烧蚀的数值计算研究。将实验结果与数值模拟结果进行了对比分析,两者在一定程度上吻合较好,从一个侧面验证了数值模拟的有效性。Based on researching the ablation mechanism of the tailpipe nozzle, a kind of test method was established, mean- while, a set of test device which can be used in studying on the ablation of the tailpipe nozzle was developed. Then the normal and overload ablation test were carried out, and test data and ablation images were achieved. On the other hand, numerical researches on the ablation of the tailpipe nozzle were done, and numerical results were compared with test results. The results show that test results argee with numerical results to a certain extent, and the numerical simulation method is effective.

关 键 词：固体火箭发动机 长尾喷管 烧蚀实验 过载 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]