小型多桨倾转机翼飞行器倾转过渡特性风洞试验研究  

Wind-tunnel Testing on Tilting Flight Mode Characteristics of a Small Distributed Propulsion VTOL Tilt-Wing Aircraft

作　　者：刘纪福[1] 马东林 罗骏[1] LIU Jifu;MA Donglin;LUO Jun(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2023年第1期29-33,40,共6页Helicopter Technique

摘　　要：多桨倾转机翼飞行器飞行模式多且操控复杂,尤其是倾转过渡模式,气动干扰复杂,操纵冗余,从理论上确定气动与操纵特性难度大。为了研究多桨倾转机翼飞行器倾转过渡模式的气动与操纵特性,对某小型多桨倾转机翼无人机单独机翼及整机开展了倾转过渡模式不同机翼倾角、不同舵面角度、不同油门等状态下的吹风测力试验。根据试验数据分析了整机倾转过渡模式的操纵特性及控制原则,为多桨倾转机翼构型飞行器总体设计及倾转过渡模式操纵策略研究提供了参考。It is very difficult to determine the aerodynamics and control characteristics theoretically for distributed propulsion VTOL tilt-wing aircraft,because of multi-flight modes,complexity of control,especially complexity of aerodynamics interactions and redundancy of control surfaces for the tilting flight mode.In order to investigate the aerodynamics and control characteristics of tilting flight mode,a small unmanned distributed propulsion VTOL tilt-wing aircraft and it’s wing alone were tested in wind tunnel with different wing tilt angles,control surface angles and throttles.According to the experimental data,control characteristics and control principle of the aircraft for the tilting flight mode were analyzed,which provided some references for overall design and research on manipulation strategy for the tilting flight mode of distributed propulsion VTOL tilt-wing aircraft.

关 键 词：倾转机翼 倾转过渡 操纵特性 风洞试验 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] V211.74V212.4