机动弹头舵轴热环境分析  

Analysis of Thermal Environment of Maneuvering Rudder Shaft

作　　者：张志刚[1,2] 赵金山[2] 粟斯尧[2] 孔荣宗 陈挺[2] ZHANG Zhigang;ZHAO Jinshan;SU Siyao;KONG Rongzong;CHEN Ting(College of Aerospace Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]南京航空航天大学航空学院,南京210016 [2]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000

出　　处：《南京航空航天大学学报》2022年第4期583-591,共9页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：机动弹头舵轴热环境是高超声速飞行器热防护系统设计中需重点考虑的局部问题,舵轴缝隙中流动结构极其复杂,且舵轴局部热环境峰值相对于大面积区域要严重得多。针对高超声速机动弹头舵轴热环境问题,结合数值模拟方法和激波风洞试验,研究了舵轴热环境随迎角、舵偏角、马赫数和飞行高度等参数的变化规律。结果表明,对于十字布局的气动舵,大迎角时水平舵轴热环境最为严酷;在小迎角条件下,水平舵轴无量纲热流随舵偏角和马赫数逐渐上升,但在大迎角情况下,马赫数和舵偏对水平舵轴无量纲热流的影响较小。在此基础上,建立了适用于舵轴热流峰值预测的四参数插值拟合方法,可用于舵轴峰值热环境随飞行历程的快速预测。The thermal environment of maneuvering rudder shaft is a local problem to be considered in the design of thermal protection system of hypersonic missile.The flow structure in rudder shaft gap is complex,and under typical flight conditions,the peak of the local thermal environment of the rudder shaft is more serious than that of in large area.Aiming at the problem of thermal environment of hypersonic maneuvering warhead shaft,combined with numerical calculation and wind tunnel test,the variation of thermal environment of rudder shaft with attack angle,rudder deflection angle and Mach number is studied.Then,a four-parameter interpolation fitting method suitable for predicting the peak heat flow of rudder shaft is established.The results show that,for the rudder like letter“+”,the thermal environment of horizontal rudder shaft is the most severe;under the condition of small attack angle,the dimensionless heat flow of the rudder shaft increases gradually with the increase of the rudder deflection angle and Mach number,but under the condition of large attack angle,the influence of Mach number and rudder deflection on the dimensionless heat flow of the rudder shaft is small.The four-parameter fitting method established in this paper can be used to rapidly evaluate the peak thermal environment of the rudder shaft along the trajectory.

关 键 词：舵轴 热环境 风洞实验 数值模拟 关联分析 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]