摘要
柔性翼有望提高微型飞行器(MAV)的抗风能力。为进一步了解柔性翼的气动性能,建立MAV数学模型,并为飞行仿真和飞行控制设计做准备,在低雷诺数风洞中对柔性翼微型飞行器进行了风洞试验,同时采用翼型、机翼平面形状和尺寸大小均相同的刚性翼进行了风洞对比试验。对比结果表明:柔性翼相比于对应的刚性翼,失速迎角较大;柔性翼的最大升力系数较大,但是柔性翼的变形在提高升力的同时也增大了阻力,升阻比的情况较为复杂;在较低雷诺数情况下,柔性翼的纵向静稳定性略优于刚性翼;柔性翼的长周期和短周期模态的衰减特性和阻尼特性略优于刚性翼。
The design of a flexible wing can enhance the capability of gust resistances for a micro air vehicle （MAV）. To understand the aerodynamics of the flexible wing and establish a mathematic model for it,experiments on the flexible wing were performed using a low Reynolds number wind tunnel. The established model can be used for flight simulation and control design of the MAV. Comparable experiments with a fixed wing of the same size and shape were also conducted which illustrated distinct aerodynamic advantages of the flexible wing. Experiment results indicate that the flexible wing has a larger angle of stall and a greater maximum lift coefficient than the fixed wing. However,the lift-drag ratio of the flexible wing varies in a complex way because the flexible wing also increases the drag with its lift growth. At low Reynolds number,the longitudinal stability of the flexible wing is a little better than that of the fixed wing. The longitudinal response frequency and damping features of the flexible wing at both modes of long and short periods are also better than those of the fixed wing.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第6期1440-1446,共7页
Acta Aeronautica et Astronautica Sinica
基金
国家"863"计划
关键词
柔性翼
气动特性
风洞试验
低雷诺数
升阻特性
flexible wing
aerodynamics
tunnel test
low Reynolds number
lift and drag
