Research Papers

Modeling Helicopter Blade Sailing: Dynamic Formulation and Validation

[+] Author and Article Information
A. S. Wall, F. F. Afagh, R. G. Langlois

Department of Mechanical and Aerospace Engineering, Carleton University, 1125 Colonel By Drive, Ottawa, ON, K1S 5B6, Canada

S. J. Zan

Aerodynamics Laboratory, Institute for Aerospace Research, National Research Council of Canada, 1200 Montreal Road, Ottawa, ON, K1A 0R6, Canada

J. Appl. Mech 75(6), 061004 (Aug 15, 2008) (10 pages) doi:10.1115/1.2957599 History: Received September 21, 2006; Revised May 02, 2008; Published August 15, 2008

Rotor blade sailing, which is characterized by excessive deflection of rotor blades, can be experienced by shipboard helicopters during rotor start-up and shut-down. In an attempt to model the complete ship-helicopter-rotor system in a way that is geometrically representative and computationally efficient, the system was represented as a discrete-property rigid-body and flexible-element system capable of simulating many important dynamic effects that contribute to the motion of rotor blades. This paper describes the model in detail and discusses validation cases. While both dynamic effects and aerodynamic effects are believed to be important components of blade sailing, this paper focuses exclusively on the dynamics. The validation cases discussed herein suggest that the modeling approach presented offers excellent potential for efficiently modeling blade sailing and other blade motion phenomena.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 1

The model coordinate systems

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Figure 2

General stiffness curve for blade root springs

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Figure 3

Blade response in flap to a pull test (hingeless blade with varying number of segments)

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Figure 4

Large bending tip deflections due to static tip force (ten segments)

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Figure 5

Beam spin-up validation (finite element results from (1): Ref. 30 and (2): Ref. 31)

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Figure 6

Variation in flapping frequencies with rotor speed

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Figure 7

Lead/lag motion restrained by Bramwell moment

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Figure 8

First three flap-coupled frequencies for swept tip beam (experimental data from Ref. 33)

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Figure 9

Droop stop test blade tip deflection (experimental data and published results from Ref. 11)

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Figure 10

Droop stop test flap hinge angle (experimental data and published results from Ref. 11)



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