现代防御技术2024，Vol.52Issue(3)：9-19,11.DOI:10.3969/j.issn.1009-086x.2024.03.002
倾转机翼旋翼无人机倾转过渡状态数值模拟
Numerical Simulation of Tilting Wing and Rotor UAV During Transition Flight
摘要
Abstract
Compared with traditional configuration tiltrotor aircraft,tilting wing and rotor UAV can significantly reduce the aerodynamic interference of rotor wake on wings in hover,and increase flight efficiency.Regarding the continuous tilting transition process of the UAV with complex unsteady aerodynamic characteristics,the delayed detached eddy simulation(DDES)method,improved from the classical detached eddy simulation(DES)method,is used to simulate aerodynamic interference.During the tilting transition process,the aircraft's forward flight speed,rotor pitch angle,fuselage and fixed wing angle of attack,and nacelle inclination angle all dynamically change over time.By comparing with the traditional configuration,the aerodynamic performance changes and flow field mechanisms during the tilting transition process are analyzed.The simulation calculation results show that the UAV in the initial state of tilting is less affected by the rotor downwash.During the tilting process before the 30° nacelle inclination angle,due to the increased resistance of the tilting wing segment,the required thrust of the rotor are increased.The separation vortices generate during the tilting process of the tilting wing section collide with the downwash wake of the rotor,resulting in a larger wake interference area at the wing tip position and a downwash effect on the inner fixed wing tip,reducing the overall lift of the aircraft.关键词
倾转机翼/无人机/延迟分离涡模拟/倾转过渡/气动干扰/非定常气动特性Key words
tilting wing/unmanned aerial vehicle(UAV)/the delayed detached eddy simulation/transition flight/aerodynamic interference/unsteady aerodynamic characteristics分类
航空航天引用本文复制引用
王宗辉,杨云军,赵弘睿,赵佳祥..倾转机翼旋翼无人机倾转过渡状态数值模拟[J].现代防御技术,2024,52(3):9-19,11.基金项目
国家自然科学基金(U21B2054) （U21B2054）
