新型车载同心筒复燃机理与热环境研究

Research on Secondary Combustion Mechanism and Thermal Environment of A New Vehicle-carried Concentric Canister Launcher

针对新型车载同心筒自力发射系统热环境评估的问题,基于二阶AUSM格式,依托弹性变形和域动分层结合的动网格技术,采用H2-CO-HCL反应体系17步基元反应的化学反应动力学模型,求解了动态的轴对称复燃流场。数值结果表明,导弹启动之前,内筒出现了燃气向上运动的"引射效应",燃气和内筒空气发生复燃现象;导弹启动后期,内筒出现了富氧气体倒吸进入内筒的"倒吸效应",加剧了内外筒的化学反应;化学反应流的温度比单组份流高800K左右。

Based on the 2nd-order AUSM scheme and dynamic mesh technology with spring based smoothing method,and laying based zone moving method,the combustion mechanism of H2-CO-HCL reaction system and seventeen reaction steps is adopted to simulate the secondary combustion field of a new vehicle-carried concentric canister launcher（ CCL）. The numerical results show that before missile starts to move,the jet gas in the inner cylinder moves upward which leads to the ejection effect,and secondary combustion occurs clearly with the mixing of jet gas and air. In the later period,the reverse absorption effect is obviously,chemical reaction is exacerbated by the inverted absorption enriched gas flowing into the internal canister. The temperature of chemical reaction flow is higher than that of single-component flow by about 800 K.