旋转机翼飞机旋翼飞行验证平台设计  

Design of the Rotor Wing Flight Testing Platform for Rotor Aircraft

作　　者：李亮明[1] 高正红[1] 何澳[1] 邓阳平[1] 田力[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2013年第4期488-492,共5页Advances in Aeronautical Science and Engineering

摘　　要：为了更好地研究旋转机翼飞机旋翼模式下的飞行性能,针对旋转机翼飞机的特点,开展旋转机翼飞机旋翼飞行验证平台的设计,主要包括旋转机翼的结构设计、动力系统设计。通过数值计算的方法,对不同相对厚度椭圆翼型气动特性进行分析研究。建立旋转机翼悬停气动特性的估算方法,地面试验结果和计算结果的对比表明所建立的估算方法是有效的,该方法对今后开展旋转机翼飞机研究具有一定的参考价值和意义。In order to study the flight performance of the rotor aircraft, according to the characteristics of rotor wing aircraft, the rotor wing flitht testing platform is developed, including the structural design of rotor wing and power system. The calculating method of aerodynamic performance of elliptic airfoils with different thickness-chord ratio is given. And in the end of this paper, estimation method of the hovering mode is developed, the comparison between experimental results and computation shows the estimation method is effective. The re sults provide some reference value for the research of rotor wing aircraft.

关 键 词：椭圆翼型 旋转机翼 气动特性 飞行验证平台 

分 类 号：V221.8[航空宇航科学与技术—飞行器设计]