导弹/火箭燃烧尾焰冲击特性计算研究综述

Overview of Calculations on Exhaust Plume Impinging Characteristics of Missile/Rocket

在导弹/火箭从点火到起飞过程中,其后的尾焰冲击发射装置迎气面可能导致发射装置的严重烧蚀,向尾焰喷射大量冷却水可以有效起到保护发射装置作用。针对导弹/火箭发射时燃烧尾焰冲击发射平台和喷水降温降噪问题,介绍了燃烧尾焰冲击特性计算步骤方法,通过对燃烧尾焰流场计算、燃烧尾焰对迎气面冲击流场计算和喷水情况下燃烧尾焰对迎气面冲击流场计算工作进行归纳整理、综合分析,总结论述了各种计算方法及其适用性。基于充分考虑发动机内部燃烧的影响,提出了适用于多喷管导弹/火箭的燃烧尾焰及其冲击流场和喷水对燃烧尾焰冲击流场影响的计算方法,便于流场计算区域网格构建,避免了大量重复计算和资源浪费。

In the course from ignition to lift off of missile/rocket launching,airblast against the airflow-resisting side of the exhaust plume may cause severe ablation of launch installation,while injecting large volume of water to cool down the plume may effectively protect the launch installation.To solve out the problems including the impinging of exhaust plume to the launch pad during the launch course and the water injection to lower the temperature and noise,the paper introduces steps and methods for computing characteristics of exhaust plume impinging.Through summarization and comprehensive analysis on the computations of exhaust plume flow field,airblast flow field on airflow-resisting side in the conditions with or without water injection,the paper concludes and discusses various computation methods and their applicability.Based on the full consideration of influence of engine combustion,the paper proposes a computation method applicable to exhaust plume of multinozzle missile/rocket and its impinging flow field in the conditions with or without water injection so as to facilitate the building of the computing grid and avoid a lot of redundant computations and waste of computing resource.