过载对固体火箭发动机性能影响试验研究(英文)  

Experiment study of effects induced by overload on SRM performance

作　　者：武渊[1] 何国强[1] 孙展鹏[2] 贾有军[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2010年第5期511-514,共4页Journal of Solid Rocket Technology

摘　　要：建立了立式旋转试车台,研究了高过载对固体火箭发动机性能的影响。通过地面静止及不同过载(15gn,15gn;35gn,15gn)条件下点火对比试验,获得固体火箭发动机在不同过载条件下内弹道性能以及绝热层和喉衬的烧蚀规律。试验表明,随着过载增加,发动机压强增大、工作时间缩短;横向与轴向的组合过载恶化了烧蚀环境,使喉衬出现偏心烧蚀。Experiments for effect on solid rocket motor（SRM） performance induced by overload were carried out on a vertical rotation test stand.The comparison of static tests and overload（15gn,15gn;35gn,15gn）firing tests was performed.The change of internal ballistics performance,insulator and throat insert abnormal erosion induced by overload were obtained from test.The results show that the increasing overload tends to raise the solid rocket pressure and shorten the work time.The lateral overload combined with the axial overload tends to deteriorate the insulation erosion environment and make the eccentric erosion of throat insert.

关 键 词：固体火箭发动机 飞行过载模拟试验 内弹道 喉衬偏心烧蚀 绝热层烧蚀 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]