倾转旋翼机旋翼/机翼气动干扰理论与试验

Theory and test of rotor/wing aero-interaction in tilt-rotor aircraft

采用参数化建模方法,建立了适用于飞行力学分析的倾转旋翼机旋翼/机翼气动干扰模型,提出一套简单而准确的干扰区计算方法,得出了干扰区边界的解析表达式,并根据解析式数值积分得到了干扰区的面积,据此给出了过渡过程中旋翼/机翼气动干扰的速度边界。针对上述模型和方法,进行了倾转旋翼不同旋翼总距、前飞速度以及短舱倾角下的旋翼/机翼气动干扰风洞试验,并通过理论计算结果与风洞试验结果的对比验证建模方法的正确性。

A new model for rotor/wing aero-interaction in tilt-rotor aircraft is established by parametirc modeling method, which suits to flight dynamic analysis. The expression for calculating the boundary of rotor/wing aero-interaction area is de- rived using a simple and accurate method. The area of interaction is then calculated with analytical expression of numerical integration, as well as the velocity boundary of rotor/wing interaction. A wing tunnel test for tilt-rotor is conducted in different rotor collective pitch, wind velocity and nacelle angle. The comparison between test and calculation shows the effectiveness of this new model.