| 倾转旋翼机旋翼/机翼气动干扰理论与试验 |
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| 引用本文： | 张铮,陈仁良.倾转旋翼机旋翼/机翼气动干扰理论与试验[J].航空学报,2017,38(3). |
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| 作者姓名： | 张铮 陈仁良 |
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| 作者单位： | 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 |
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| 基金项目： | 国家自然科学基金，National Natural Science Foundation of China |
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| 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。
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| 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 |
Theory and test of rotor/wing aero-interaction in tilt-rotor aircraft |
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| ZHANG Zheng,CHEN Renliang.Theory and test of rotor/wing aero-interaction in tilt-rotor aircraft[J].Acta Aeronautica et Astronautica Sinica,2017,38(3). |
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| Authors: | ZHANG Zheng CHEN Renliang |
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| 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. |
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| Keywords: | tilt-rotor aircraft aero-interaction interaction boundary analytical expression wind tunnel test |
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