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所属单位：航空学院

发表刊物：Xibei Gongye Daxue Xuebao

摘要：In order to research on the effect of lateral cyclic pitch differential and rotor control phase angle on the flight dynamic characteristics of coaxial rigid rotor high-speed helicopter. By using the validated flight dynamic model of XH-59 helicopter, analyze the influence of lateral cyclic pitch differential and rotor control phase on the trim characteristics, maximum hub bending moment of upper and lower rotors and power required under helicopter mode and compound mode. The results show: with growing up of forward speed, increasing lateral cyclic pitch differential and decreasing rotor control phase angle can augment the trim pitch attitude, reduce the trim collective pitch and power required of helicopter mode and compound mode. Decreasing lateral cyclic pitch differential and increasing rotor control phase angle can lower the maximum hub bending moment. Comparing with lateral cyclic pitch differential, increasing rotor control phase angle cause the trim longitudinal cyclic pitch rapidly increase even exceed the limitation. Meanwhile, lateral cyclic pitch differential can do better in adjusting the power required and hub bending moment. © 2017, Editorial Board of Journal of Northwestern Polytechnical University. All right reserved.

ISSN号：1000-2758

是否译文：否

发表时间：2017-10-01

合写作者：Yuan, Ye,李攀,Lu, Ke

通讯作者：陈仁良