双发飞翼布局保形尾喷管燃气舵概念设计  

Conceptual design of jet vane on the conformal nozzle for twin-engine flying wing layout

作　　者：张乐[1] 周洲[2] 许晓平[2] ZHANG Le;ZHOU Zhou;XU Xiao-ping(Institute of System Engineering, CAEP, Mianyang 621900, China;School of Aeronautics, NWPU, Xi＇ an 710072, China)

机构地区：[1]中国工程物理研究院总体工程研究所,四川绵阳621900 [2]西北工业大学航空学院,陕西西安710072

出　　处：《飞行力学》2018年第2期16-20,共5页Flight Dynamics

基　　金：国家自然科学基金资助(11302178)

摘　　要：针对飞翼布局操纵效能低、稳定性差等不足,基于大展弦比双发动机布局飞翼无人机,开展了保形尾喷管燃气舵概念设计,分别设计了一种燃气方向舵与燃气升降舵。结合可靠的计算流体力学(CFD)计算方法,获取了全机纵向和横航向气动特性,并与常规气动舵设计进行了对比。研究表明:燃气方向舵比传统阻力方向舵具有更好的偏航操纵效率,且基本不影响全机升阻特性和俯仰力矩特性;燃气升降舵与内翼段开设升降舵时俯仰操纵效率接近,且在小迎角下具有显著的俯仰操纵效率,带来的附加阻力较小。Since the flying wing layout has the feature of low control efficiency and poor stability,conceptual design of jet vane was carried out on the conformal nozzle based on the high aspect ratio flying wing unmanned aerial vehicle（UAV）with twin-engine.And then a kind of jet rudder and jet elevator was designed respectively.Combining the reliable computational fluid dynamics（CFD）method,the longitudinal and lateral-directional aerodynamic performance of UAV were obtained,and they were compared with the conventional aerodynamic rudder design.Results indicated that the jet rudder has better yawing control efficiency than the conventional drag rudder,and it hardly affects the lift-drag and pitching moment characteristics;the pitching control efficiency of jet elevator is very close to the elevator established on the interior wing surface,and then not only there is a significant pitching control efficiency at small attack angle,but also it brings a little additional drag.

关 键 词：双发 保形尾喷管 燃气舵 概念设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]