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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。
The mathematic model of tilting tail rotor was established based on the elemental theory. The UHMW-60A helicopter was used as a target to calculate the leveling performance of the flat flight, and compared with the flight test results. The model verification was completed. The verification results show that the inclined tail rotor model built is reasonable and accurate and can meet the engineering accuracy. In this paper, the design of skew angle of tail rotor is studied from the power required for helicopter hovering. The influence of different skew angle of tail rotor on horsepower required for helicopter hovering is calculated. The optimal value of skew angle of tail rotor of UH-60A helicopter is obtained For 20 ~ 25 °. By calculating and comparing the leveling performance of the inclined tail rotor and the conventional tail rotor helicopter, it is concluded that the tail rotor inclination mainly affects the longitudinal trim characteristics of the helicopter. Finally, some discussions are made on the advantages and disadvantages of skewed tail rotor.