航空学报 > 2017, Vol. 38 Issue (3): 120196-120196   doi: 10.7527/S1000-6893.2016.0228

倾转旋翼机旋翼/机翼气动干扰理论与试验

张铮, 陈仁良   

  1. 南京航空航天大学 直升机旋翼动力学国家级重点实验室, 南京 210016
  • 收稿日期:2016-03-07 修回日期:2016-06-20 出版日期:2017-03-15 发布日期:2016-08-22
  • 通讯作者: 陈仁良,E-mail:crlae@nuaa.edu.cn E-mail:crlae@nuaa.edu.cn
  • 基金资助:

    国家自然科学基金(11672128)

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

ZHANG Zheng, CHEN Renliang   

  1. National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2016-03-07 Revised:2016-06-20 Online:2017-03-15 Published:2016-08-22
  • Supported by:

    National Natural Science Foundation of China (11672128)

摘要:

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。

关键词: 倾转旋翼机, 气动干扰, 干扰边界, 解析表达式, 风洞试验

Abstract:

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 derived 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.

Key words: tilt-rotor aircraft, aero-interaction, interaction boundary, analytical expression, wind tunnel test

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