CAJ | 학술논문

鸭式旋翼/机翼飞机是一种新概念可垂直起降高速飞行器,为了解该飞机在悬停及小速度前飞时的全机气动干扰特性,在南京航空航天大学开口风洞中进行了飞机全机气动力实验,实验采用多台测力天平分别测量主机翼和机身的气动力.结果表明,悬停时受主机翼高速旋转产生的下洗尾流影响,机身产生了较大的法向力和低头力矩;前飞时下洗尾流对机身的法向力和俯仰力矩有比较严重的干扰,对滚转力矩和偏航力矩干扰较小,对侧向力有一定影响.实验结果为飞机的飞行动力学特性研究以及控制律设计提供了参考.＃
압식선익/궤익비궤시일충신개념가수직기강고속비행기,위료해해비궤재현정급소속도전비시적전궤기동간우특성,재남경항공항천대학개구풍동중진행료비궤전궤기동력실험,실험채용다태측력천평분별측량주궤익화궤신적기동력.결과표명,현정시수주궤익고속선전산생적하세미류영향,궤신산생료교대적법향력화저두력구;전비시하세미류대궤신적법향력화부앙력구유비교엄중적간우,대곤전력구화편항력구간우교소,대측향력유일정영향.실험결과위비궤적비행동역학특성연구이급공제률설계제공료삼고.＃
Canard Rotor/Wing Aircraft(CRW)is a revolutionary high-speed rotorcraft that combines the speed and range of a fixed-wing aircraft with the flexibility of rotary-wing flight. In order to have an insight into aerodynamic interactions between the rotor/wing and fuselage of CRW in hover and low speed forward flight,a shaft-driven rotor/wing and scaled fuselage model were tested in an open circuit wind tunnel of Nanjing University of Aeronautics and Astronautics (NUAA), multiple six-component force and moment balance was used to measure the forces and moments of rotor/wing and fuselage respectively. Results show that in hover the fuselage normal force and pitching moment are relatively high due to the influence of rotor/wing downwash;and in low speed forward flight, the downwash have strong interaction on the normal force and pitching moment of fuselage due to the big dimension horizontal tail;the effects of downwash on the fuselage rolling and yawing moments are little and the influence on fuselage side force is considerable. These results can provide reference for flight dynamics research and control law development of CRW.