Effect of free play in rotor blades hinges on the non‐linear ground resonance of a helicopter
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 1 December 2002
Abstract
In this paper results of numerical analysis of the ground resonance are shown. This analysis is performed making use of the complete model of the one‐main rotor helicopter. This model is adopted from flight mechanics. For the basic analysis it is assumed that the helicopter fuselage is a rigid body and the main rotor consists of four rigid blades. Each blade performs motions about its horizontal flapping hinge and vertical lagging hinge. The tail rotor is treated as a hingeless and weightless source of thrust, which equilibrates the drag moment and ensures directional control of the helicopter. For analysis of the ground resonance phenomenon, forces and moments produced by the landing gear are taken into account – their rigidity and damping are included into consideration.
Keywords
Citation
Kowaleczko, G. and Dzygadlo, Z. (2002), "Effect of free play in rotor blades hinges on the non‐linear ground resonance of a helicopter", Aircraft Engineering and Aerospace Technology, Vol. 74 No. 6, pp. 508-516. https://doi.org/10.1108/00022660210448438
Publisher
:MCB UP Ltd
Copyright © 2002, MCB UP Limited