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?structural 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, the scarcely mentioned factor, structure gap was focused on. Two possible modes were defined to analysis this phenomenon. By analyzing stress status and contact status of the contact pairs, stress destruction mode was excluded. It was confirmed that the main reason was gap ablation mode. Simulation results from the proposed method indicated that it agreed well with testing experiment. This offered design basis for future improvement.
展开▼
