导弹发动机推进剂恶劣工况下温度分析  

Temperature Analysis for Propellant of Missile Engine under Severe Environmental Conditions

作　　者：姜毅[1] 王艳彬[2] 刘群[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081 [2]中国航天科工集团第二研究院二部,北京100854

出　　处：《中北大学学报（自然科学版）》2008年第1期18-24,共7页Journal of North University of China(Natural Science Edition)

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,并利用该方法对导弹弹射动力装置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进行传热问题的计算,可为导弹发动机推进剂温度场的分析提供参考和依据.For analyzing the influence of initial room＇s temperature on the rocket motor at high temperature or low temperature, the computational fluid dynamics （CFD） method is used to build the model of the first stage motor. Through considering heat transfer modes （heat exchange, heat convection and radicalization）, using the fluid-solid coupled heat transfer method to calculate the stationary model, the paper gets the temperature distribution under different temperature conditions to provide the theoretical proofs for adjusting the temperature criterion of the initial room. The simulating result based on the model of missile ejection launcher is consistent with that of experiment, which indicates that using the CFD method and the fluid-solid coupled method can provide the reference and basis for adjusting the propellant temperature of missile motors.

关 键 词：推进剂 计算流体力学 流固耦合 自然对流 

分 类 号：TJ760.33[兵器科学与技术—武器系统与运用工程]