基于UMARC的大展弦比机翼空气动力建模方法  

Aerodynamic Modeling of High-aspect-ratio Wing Based on UMARC

作　　者：赵常[1] 杨茂[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《科学技术与工程》2010年第12期2913-2919,共7页Science Technology and Engineering

摘　　要：将旋翼气动建模思想引入大展弦比固定翼,对旋翼飞行器UMARC理论中直升机旋翼空气动力建模方法进行适当改进,建立适应机翼较大变形情况下的空气动力学模型。将大展弦比机翼描述为Bernoulii-Euler梁形式,利用机翼大变形前后坐标系转换关系,推导得到变形后坐标系下机翼任意截面瞬时空气速度并最终建立空气动力载荷模型。利用模型计算机翼气动弹性静平衡位置,经与已有文献结果对比,表明此模型建立方法准确、有效;将UMARC理论移植到大展弦比机翼思想可行;并具较高工程应用前景。The aeroelastic characteristic of high-aspect-ratio fixed wing and that of rotor blade on a helicopter were analogical. Enlightened by this idea, an effort was made to mend the UMARC theory, which could be used to establish the aeroelastic models of rotor blade, so as to gain a method adaptive to aerodynamic modeling of high-as- pect-ratio fixed wing with large deflection. The high-aspect-ratio fixed wing was treated as an Bernoulii-Euler beam. By dealing with the transformation of the coordinates correlated to the deformed and undeformed wing, ex- pressions of the velocity in the deformed wing section and aerodynamic loads at a given moment were deduced. Employing the modeling method mentioned here, the steady state equilibrium solutions were gained. By comparing with the result in the reference, the effectiveness and accurateness of the method is validated.

关 键 词：大展弦比机翼 Bernoulii-Euler梁 空气动力载荷 气动弹性 

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]