某型导弹发动机推进剂恶劣工况下温度仿真研究  

Temperature Simulation Study of Missile Motor Propellant in Severe Environment

作　　者：刘群[1] 姜毅[1] 郝继光[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081

出　　处：《兵工学报》2007年第12期1463-1467,共5页Acta Armamentarii

摘　　要：为分析高温和低温工况下初容温度超标对导弹发动机的影响,采用计算流体力学方法,对一级发动机的各部分进行了三维实体的简化及建模,综合考虑热传导、自然对流和辐射等传热方式,运用流固耦合传热一体化计算方法进行定常模拟计算,获得野外高温日照和低温恶劣环境下该装置的温度分布情况,为初容温度指标调整提供理论依据,并利用该方法对文献[2]中的模型进行了非定常数值模拟,与实验数据吻合较好,表明采用计算流体力学方法和流固耦合方法可进行传热问题的计算,为导弹发动机推进剂温度场的分析提供参考和依据。In order to analyze the influence of exceeding the initial room temperature criterion on a missile motor under conditions of high and low temperatures, three-dimensional solid for every part of the first stage motor was simplified and modeled by the CFD method. After considering heat conduction, convection and radiation, the stationary simulation calculation was conducted by the fluid-solid coupled heat transfer method to obtain the temperature distribution at different temperatures in severe field environment and theoretical basis used for adjusting the initial room temperature criterion. Through simulating the model described in Reference [2], it could be determined that the results of the simulation are in accordance with that of the experimental data. Using the CFD method and the fluid-solid coupled method can provide both reference and basis for adjusting the temperature of missile motor propellant.

关 键 词：热学 推进剂 计算流体力学 流固耦合 自然对流 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]