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Affiliation of Author(s):航空学院

Journal:Trans. Nanjing Univ. Aero. Astro.

Abstract:An investigation is conducted on optimizing the control allocation for trimmed flight on the compound helicopter. The compound helicopter features a single main rotor, a vectored thrust ducted propeller (VTDP) and lifting wings. Due to the redundant controls for thrust, elevator deflection, and differential and symmetric flap deflection, there is a wide range of trim solutions in forward flight for compound helicopter. A method is developed to calculate optimal trim solutions. Firstly, aerodynamics models for deferent subsystems of the compound helicopter are conducted, which consider the mutual interaction of each part. Secondly, a flight dynamics model is developed based on which the method of trim optimization is performed. Finally, the method is demonstrated using a compound helicopter UH 60L/VTDP. The trim optimization of flight conditions from hover to 370 km/h is conducted using the optimization method. The controls, fuselage attitudes as well as the allocation of lift and thrust along with the flight speed are obtained. © 2019, Editorial Department of Transactions of NUAA. All right reserved.

ISSN No.:1005-1120

Translation or Not:no

Date of Publication:2019-06-01

Co-author:Yu, Zhiming,crl

Correspondence Author:kwh