高空飞行多级运载火箭基础热环境控制研究  

Investigation the control of the basic thermal environment of multistage launch vehicle at high altitude flight

作　　者：赵晨耕 孙中一 苏逸飞 王逸尘 乐贵高[1] ZHAO Chengeng;SUN Zhongyi;SU Yifei;WANG Yichen;LE Guigao(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《航空动力学报》2024年第12期377-387,共11页Journal of Aerospace Power

摘　　要：采用数值模拟的方法,系统地研究了单喷管和四喷管多级液体运载火箭的基础热环境,并验证了箭底氮气喷射热防护方法的可行性。基于多组分Navier-Stokes方程、k-ε方程湍流模型、热辐射方程,运用AUSM格式对控制方程进行离散,建立了高空超声速飞行运载火箭的羽流模型。采用分块化网格构建法,计算了运载火箭在不同高度下的羽流流场和热流密度,并且将数值结果与飞行试验进行对比,验证了计算方法的可行性。研究表明在低海拔高度,箭底热流以对流热流为主,峰值出现在30 km处;在高海拔高度,箭底热流以辐射热流为主,峰值出现在110 km处;同时箭底氮气喷射装置能够有效地抑制燃气回流,起到降低箭底对流热流的效果,但是选择合适的喷口数量和喷射总压极为重要。The basic thermal environment of one-engine and four-engine multi-stage liquid launch vehicles has been systematically investigated and the feasibility of the nitrogen injection thermal protection method at the rocket base has been verified by numerical simulation.Based on multi-component Navier-Stokes equation,k-εequation turbulence model and thermal radiation equation,the control equations were discretized using AUSM format to establish a plume model for high altitude supersonic flight launch vehicles.The plume flow field and heating rate of the launch vehicle at different altitudes were calculated using the blocked gird construction method,and the numerical results were compared with flight experiments to verify the feasibility of the calculation method.Study showed that at low altitudes,convection heating rate is dominant,with a peak at 30 km;at high altitudes,radiation heating rate is dominant,with a peak at 110 km;at the same time,the nitrogen injection device can effectively suppress gas backflow and reduce convection heating rate at the rocket base,but the selection of the right number of spouts and total injection pressure is extremely important.

关 键 词：多级运载火箭 分块化网格 对流热流 辐射热流 氮气喷射 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]