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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 parametric modeling method is used to establish a rotor / wing aerodynamic interference model suitable for flight mechanics analysis. A simple and accurate calculation method of the interference zone is proposed, and the analytical expression of the boundary of the disturbance zone is derived. The area of disturbing area is obtained by numerical integration of analytic method, and the velocity boundary of aerodynamic disturbance of rotor / wing during transition is given. According to the above models and methods, the rotor-wing / wing aerodynamic disturbance wind tunnel tests under different rotor total rotor pitch, forward flight speed and nacelle inclination angle are carried out. The theoretical calculation results are compared with the wind tunnel test results to validate the modeling The correctness of the method.