| 斜置尾桨对直升机飞行特性的影响 |
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| 引用本文： | 彭勇,陈平剑,孙强. 斜置尾桨对直升机飞行特性的影响[J]. 南京航空航天大学学报, 2011, 43(4) |
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| 作者姓名： | 彭勇 陈平剑 孙强 |
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| 作者单位： | 中航工业直升机设计研究所,景德镇,333001 |
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| 摘 要： | 基于叶素理论建立了斜置尾桨的数学模型,以UH-60A直升机为对象,计算了平飞配平特性,并与试飞结果进行对比,完成了对模型的验证。验证结果表明,所建的斜置尾桨模型合理准确,能满足工程精度。本文从直升机悬停需用功率研究了尾桨斜置角的设计,计算了不同尾桨斜置角对直升机悬停需用功率的影响,得出UH-60A直升机的尾桨斜置角优化值为20~25°。通过计算和对比斜置尾桨与常规尾桨直升机的平飞配平特性,得出尾桨斜置主要影响直升机的纵向配平特性。最后,对斜置尾桨的利与弊进行了一些讨论。
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| 关 键 词： | 斜置尾桨 数学模型 斜置角设计 UH-60A直升机 |
Effect of Canted Tail Rotor on Helicopter Flight Characteristics |
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| Peng Yong,Chen Pingjian,Sun Qiang. Effect of Canted Tail Rotor on Helicopter Flight Characteristics[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2011, 43(4) |
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| Authors: | Peng Yong Chen Pingjian Sun Qiang |
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| Affiliation: | Peng Yong,Chen Pingjian,Sun Qiang(AVIC China Helicopter Research and Development Institute,Jingdezhen,333001,China) |
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| Abstract: | A mathematical model of the canted tail rotor is developed based on the blade element theory.UH-60A helicopter is taken as an example to carry out the trim calculation.The validation of the model is made by comparison between calculation results and flight test data,which indicates that the model of canted tail rotor is reasonable,accurate,and proper for the application in engineering.The effect of different canted angle on the required power of helicopter in hover is calculated,which concludes that the opt... |
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| Keywords: | canted tail rotor mathematical model canted angle design UH-60A helicopter |
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