Affiliation of Author(s):航空学院

Journal:Beijing Hangkong Hangtian Daxue Xuebao

Abstract:Adopting the flight dynamic model of coaxial rigid rotor helicopter, this paper sets the XH-59A coaxial rigid rotor helicopter as research object and analyzes the influence of rotor control phase angle on longitudinal trim characteristics, helicopter power required and hub bending moment of upper and lower rotor. Based on the analysis results, this paper proposes the allocation method of coaxial rigid rotor helicopter's rotor control phase angle. It aims to decrease the helicopter power required and make upper and lower rotor's hub bending moment and trim characteristics meet the requirement. The method can make the XH-59A helicopter satisfy the requirements of hub bending moment of upper and lower rotor and longitudinal cyclic pitch limitation within the flight speed scope of 0-80 m/s, and can minimize up to 8% power required. This method provides reference for design of coaxial rigid rotor helicopter. © 2017, Editorial Board of JBUAA. All right reserved.

ISSN No.:1001-5965

Translation or Not:no

Date of Publication:2017-10-01

Co-author:Yuan, Ye,LIPAN,Lu, Ke

Correspondence Author:crl