动量增升高升阻比飞行器横航向稳定性研究  

Study on lateral-directional stability of a practical high lift-to-drag ratio hypersonic vehicle with momentum lift augmentation

作　　者：刘深深 罗磊 韩青华 唐伟 桂业伟[1,2] 贾洪印[2] LIU Shenshen;LUO Lei;HAN Qinghua;TANG Wei;GUI Yewei;JIA Hongyin(State Key Laboratory of Aerodynamics,Mianyang 621000,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Environment-Friendly Energy Materials,Southwest Univeisity of Science and Technology,Mianyang 621000,China)

机构地区：[1]空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [3]西南科技大学环境友好能源材料国家重点实验室,绵阳621000

出　　处：《北京航空航天大学学报》2023年第11期3010-3021,共12页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家数值风洞工程。

摘　　要：考虑高超声速飞行器装填、防热及操稳等多约束条件下的实用化设计需求,提出一种新型下反式高升阻比滑翔飞行器气动布局。借鉴乘波体飞行器的高升力设计方法及动量增升原理,该新型飞行器采用下反式后掠翼构型,上表面为光滑倒圆“Λ”形设计,下表面为内凹的装填空间,为尽可能避免长时间超远距离高超声速飞行带来的防热负担,采用后缘体襟翼及体侧扩张方向舵面设计。采用数值计算方法对所提布局思路进行验证分析,计算结果表明:在飞行高度为40 km,Ma=10的条件下升阻比可以达到4.48左右,在一定迎角范围内均具备很高的气动效率,验证了所提布局的有效性。同时重点针对所提布局共性的横航向稳定性问题基于数值模拟方法探讨了3种不同优化改进方案的效果及可行性,并采用风洞试验对两侧翼梢V尾的控制方案进行横航向稳定性控制效果的试验验证,结果表明:采用两侧翼梢V尾的控制方案是实现横航向稳定性控制的较优方案。A new aerodynamic configuration concept for a hypersonic vehicle with a high lift-to-drag ratio is proposed to satisfy the constantly increasing practicability multi-constraints of high volumetric efficiency,control and stability,and acceptable thermal protection.The design principles of this practical configuration is inspired by the wave-rider design idea and momentum principle which incorporates inverted dihedral with an aft-sweeping wing,caret upper surface,and con-cavity lower surface are elaborated.A trailing edge flap and a body-fitted expansion rudder were used in place of the standard control surface's leading edge to prevent excessive heat flow during the prolonged hypersonic flight.The aerodynamic characteristics of this new configuration were obtained and discussed by applying numerical simulation with Navier-Stokes equations and wind tunnel test.The results show that the delta wing with a caret upper surface and concavity bottom surface can generate highly compressed air beneath the vehicle and reduce the loss of lifting pressure.The maximum lift-to-drag ratio achieves nearly 4.48 at Ma=10 and 40Km altitude and maintains well at a wide range of angles of attack.At the same time,the effects and feasibility of three different optimization schemes are discussed based on the numerical simulation method,aiming at the common lateral and directional stability problem of the proposed configuration,and the wind tunnel test is used to verify the lateral and directional stability control effect of the scheme with two V winglets.The results show that the control scheme with two V winglets is the better scheme to realize the lateral and directional stability.

关 键 词：高超声速飞行器 高升阻比 下反 气动布局 概念设计 横航向稳定性 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] TB553[理学—物理]