固体火箭发动机尾焰温度场特性建模与分析  

Modeling and analysis of wake flame temperature fieldcharacteristics of solid rocket engine

作　　者：那佳琪 杨录[1] 李文强[1] 张明 崔梦君 NA Jiaqi;YANG Lu;LI Wenqiang;ZHANG Ming;CUI Mengjun(State Key Laboratory of Electronic Testing,School of Information and Communication Engineering,North University of China,Taiyuan 030051,China)

机构地区：[1]中北大学信息与通信工程学院,电子测试国家重点实验室,山西太原030051

出　　处：《传感器与微系统》2023年第1期10-13,18,共5页Transducer and Microsystem Technologies

基　　金：山西省自然科学基金资助项目(201901D111161);地下目标毁伤技术国防重点学科实验室开放研究基金资助项目(DXMBJJ2021-02)

摘　　要：针对固体火箭发动机尾焰温度测试问题,提出采用建立物理模型来模拟尾焰温度场的解决方法。根据燃烧理论和流体力学,建立多物理场直接耦合的物理模型,通过数值模型来验证其可靠性,并对尾焰温度场燃烧过程进行了模拟,获得不同点火药量和不同压强的温度分布数据。结果表明:点燃剂量越多,单位时刻内放出的高温燃料就更多,高温区域的面积更大,使发动机系统能够快速进入最佳工作状态;压强提高后,温度场内燃气将其压强降低至环境压强需要经过更长的距离,尾焰后部轴线附近的高温区的位置会向后移动。In order to solve the problem of measuring the temperature of solid rocket motor wake flame,a physical model is proposed to simulate the wake flame temperature field.According to the combustion theory and fluid mechanics,a physical model directly coupled with multiple physical fields is established,and its reliability is verified by numerical model.The combustion process of the temperature field of the wake flame is simulated,and the temperature distribution data of different ignition charge quantities and different intensity of pressures are obtained.The results show that the more the ignition dose is,the more high temperature fuel will be released per unit time,and the area of the high temperature area will be larger,so that the engine system can quickly enter the optimal working state.After the pressure is increased,the gas in the temperature field needs a longer distance to reduce its pressure to the ambient pressure,and the position of the high temperature zone near the rear axis of the wake flame will move backward.

关 键 词：固体火箭发动机 尾焰 建模 温度场 

分 类 号：T205[一般工业技术] V435[航空宇航科学与技术—航空宇航推进理论与工程]