分段式固体发动机绝热环对后封头绝热层烧蚀影响分析(英文)  

Effect of adiabatic inhibitor on afterward-dome insulation ablation in segmented solid rocket motors

作　　者：王建儒[1] 何国强[1] 许团委[1] 李江[1] 李强[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2013年第3期318-323,共6页Journal of Solid Rocket Technology

摘　　要：针对某典型分段式固体发动机燃烧室内部绝热环在发动机工作过程中对后封头绝热层的烧蚀影响进行了系统分析,通过数值模拟和已有试验数据证明,分段式固体发动机工作过程中,分段药柱端面绝热环的存在一定程度上加速了燃烧室内部燃气流动的速度,导致燃烧室后封头一定范围内两相流燃气浓度的增加,从而导致后封头烧蚀量的大幅增加。在此基础上,结合改进型分段式固体发动机的数值分析,提出了分段式固体发动机在有效拟制后封头绝热层烧蚀加剧方面的设计措施和建议。The ablation effect of adiabatic inhibitor on afterward-dome insulation was discussed systematically under combustion chamber operating condition for a typical SSRM （segmented solid rocket motor）. Both numerical simulation results and tested data show that the existence of adiabatic inhibitor accelerate the gas flow speed to a certain extent, which result in two phase flow gas con- centration and speed enhanced in certain scope of afterward-dome of combustion chamber, and make the ablation quantity of after- ward-dome increased significantly. Furthermore,with the numerical analysis of modified SSRM ,the result of this investigation is to provide the motor design characteristics and the system engineering approach used to effectively suppress the insulation ablation of afterward-dome for SSRMs.

关 键 词：分段式固体发动机 绝热环 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]