倾转旋翼/机翼耦合系统过渡状态气弹动力学试验研究  

Experiment on aeroelastic characteristics of tiltrotor aircraft in transition flight

作　　者：董凌华[1] 杨卫东[1] 张呈林[1] 

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：《振动工程学报》2008年第5期465-470,共6页Journal of Vibration Engineering

摘　　要：研制了半展长的倾转旋翼/机翼耦合系统动力学模型,进行了模型的机翼基阶挥舞弯曲/扭转耦合振动随倾转角变化的气弹动力学特性分析及风洞试验,研究倾转角及前吹风速度对倾转旋翼/机翼耦合系统的机翼基阶挥舞弯曲/扭转耦合振动气弹动力学特性的影响。理论分析与试验结果表明:随试验模型从直升机模式倾转过渡到飞机模式,倾转旋翼/机翼耦合系统的机翼基阶挥舞弯曲/扭转耦合振动频率将会提高;在小前进比的前吹风倾转过程中,倾转旋翼/机翼耦合系统的机翼基阶挥舞弯曲/扭转耦合振动的阻尼随倾转角位置的不同而显著变化,随试验模型从直升机模式过渡到飞机模式,倾转旋翼/机翼耦合系统的机翼基阶挥舞弯曲/扭转耦合振动的阻尼明显降低。A experimental investigation on aeroelastic characteristics of tiltrotor aircraft in transition flight mode is carried out on a new designed dynamic model of semi-span tiltrotor with elastic wing in the wind tunnel of National Key Laboratory of Rotorcraft Aeromechanics of NUAA. The dynamic behaviors of the basic beamwise bending mode of elastic wing are analyzed at the various position of the pylon during transition. Good correlation between numerical and experimental results is achieved. During transition of tiltrotor aircraft from helicopter mode to airplane mode under low advance ratio, numerical and experimental results indicate that the frequency of the basic beamwise bending mode of elastic wing is increased, but the damping of the basic beamwise bending mode of elastic wing is decreased obviously.

关 键 词：旋翼 气动弹性 多体动力学 倾转旋翼 倾转过渡 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]