高温效应对全动舵飞行器气动热力特性影响  

High Temperature Effects on Aerothermodynamics of Hypersonic Flight Vehicles with All-movable Rudder

作　　者：张翔[1] 陈方[1] 张胜涛[1] 王福新[1] 

机构地区：[1]上海交通大学航空航天学院,上海200240

出　　处：《科学技术与工程》2015年第11期131-136,共6页Science Technology and Engineering

基　　金：国家自然科学基金(11102111)资助

摘　　要：针对高超声速飞行器气动热力特性受高温效应影响问题,基于5组元5反应动力学模型,采用AUSMPW+格式耦合隐式LU-SGS方法求解三维化学反应Navier-Stokes方程,以十字型全动舵导弹为模型,在不同壁面催化条件下,研究导弹气动热力特性受高温效应影响的变化,以更准确地预测导弹在高超声速状态下的气动力及气动热,提高其控制精度及效率。研究表明:高温效应使激波层变薄,明显降低物面温度及热流;壁面催化条件主要影响热流,而对气动力影响微弱;高温效应降低导弹升、阻力系数及舵面效率,使压心位置前移而产生抬头力矩。For the research of high temperature effects on aerothermodynamics of hypersonic flight vehicles, flow characteristics for hypersonic vehicles are investigated numerically through using an AUSMPW ＋ scheme coupling with implicit LU-SGS method to solve three dimensional Navier-Stokes equations with chemical source terms of muhi-species. Variation of aerothermodynamics is discussed emphatically in different conditions of surface catalysis model, so as to predict the aerodynamic forces and heat flux accurately, which contributes to the improvement of vehicles＇ flight efficiency and control precision in the end. Results show that high temperature effects make the thickness of shock layer thinner, lower surface temperature and decrease heat flux significantly. Surface catalysis affects heat flux of the wall much, but aerodynamic of missile little. High temperature effects also make the lift or drag coefficients lower, decrease rudder efficiency and move pressure center location forward, which results in a small upward moment.

关 键 词：高温效应 气动特性 全动舵 舵效 壁面催化 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]