摘要
针对某型喷管试车过程中出现的扩张段非正常烧蚀现象,忽略复杂的烧蚀过程,综合考虑接触热阻、摩擦热耗散过程中的能量分配以及接触对分离后的辐射传热,建立了一种满足工程要求快速分析的固体火箭发动机喷管热结构直接耦合分析方法。分析过程中,重点考察结构间隙这一鲜有讨论的问题,据此定义了2种可能导致该现象的模式,分别分析应力状态及接触对接触行为,最终排除了应力破坏模式,确定间隙烧蚀模式为主要原因。仿真结果与试车结果吻合较好,为喷管后续的改进设计提供了依据。
To research the cause of an abnormal, ablation of a nozzle during testing experiment, a fast fully-coupled thermo-struetural simulation method was established. This method ignored the complex ablation process and took contact heat resistance, friction heat dissipation and heat radiation between each contact pair into consideration. During analysis analysis, the scarcely mentioned factor, structure gap was focused on. Two possible modes were defined to this phenomenon. By analyzing stress status and contact status of the was excluded. It was confirmed that the main reason was gap ablation mode. method indicated that it agreed contact pairs, stress destruction mode Simulation results from the proposed well with testing experiment. This offered design basis for future improvement.
作者
孙林
鲍福廷
惠卫华
王绍增
张楠
邓恒
时伟
隋九龄
Sun Lin Bao Futing Hui Weihua Wang Shaozeng Zhang Nan(School of Astronautics, Northwestern Polytechnical University, Xi＇an 710072, China Xi＇an Modern Control Technology Research Institute, Xi＇an 710065, China Xi＇an Electronics Engineering Research Institute, Xi＇an 710100, China Seventh Thirteen Institute of China Shipbuilding Industry Corporation, Zhengzhou 450015, China)
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2017年第4期561-567,共7页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(51005179)资助
关键词
火箭喷管
非正常烧蚀
结构间隙
直接耦合
破坏模式
接触行为
rocket nozzles
abnormal ablation
structure gap
fully-coupled
failure modes
contact behavior
