倾转机翼无人倾转旋翼机飞行动力学稳定性分析  

Analysis of flight dynamics stability of unmanned tilt-rotor aircraft with tilting wings

作　　者：刘泽宇 招启军[1] 张夏阳 杜思亮[1] LIU Zeyu;ZHAO Qijun;ZHANG Xiayang;DU Siliang(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《飞行力学》2021年第3期1-7,共7页Flight Dynamics

基　　金：国家自然科学基金资助(11872211);重点实验室基金资助(61422200101);江苏高校优势学科建设工程资助。

摘　　要：为了研究倾转机翼无人倾转旋翼机的稳定性,发展了一种倾转机翼无人倾转旋翼机飞行力学模型,并开展了仿真研究。旋翼气动模型采用动量-叶素理论,机翼、尾翼和机身的气动模型在升力线气动理论的基础上结合了旋翼动量源方法以计入旋翼尾流的气动干扰影响。在全机飞行力学模型配平的基础上开展了动力学稳定性分析,并与常规倾转旋翼机飞行动力学特性进行了对比分析。研究结果表明:倾转机翼无人倾转旋翼机在悬停状态下,表现出俯仰角衰减迅速的稳定模态;在直升机模式小速度前飞时,改变重心位置及机翼倾转段面积可使机体纵向振荡模态发散速度减缓,系统稳定性增强。In order to research the stability of the tilt-wing unmanned tilt-rotor aircraft,a flight dynamics model of the tilt-wing unmanned tilt-rotor aircraft was developed and a simulation study was carried out.The aerodynamic model of rotor adopted the momentum-blade element theory,and the aerodynamic model of wing,tail and fuselage combined the rotor momentum source method on the basis of the lift line aerodynamic theory to take into account the influence of aerodynamic disturbance of rotor wake.The dynamic stability analysis was carried out on the basis of the flight mechanics model of the aircraft,and the flight dynamics characteristics of the tilt-rotor aircraft were compared with those of the conventional tilt-rotor aircraft.The results show that the hovering state of the tilt-wing unmanned tilt-rotor aircraft presents a stable mode with rapid attenuation of pitch angle.When flying forward at low speed in helicopter mode,changing the position of the center of gravity and the area of the wing tilting section can reduce the divergence velocity of the longitudinal vibration mode and enhance the system stability.

关 键 词：倾转机翼 倾转旋翼机 稳定性分析 飞行力学模型 

分 类 号：V279[航空宇航科学与技术—飞行器设计] V212