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The application of a theoretical blade sailing model to predict the behaviour of articulated helicopter rotors

Published online by Cambridge University Press:  04 July 2016

S. J. Newman
S. J. Newman*
Affiliation:
Department of Aeronautics and Astronautics University of Southampton
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Abstract

A theoretical model had been previously developed to predict the behaviour of a semi-rigid helicopter rotor blade during rotor engagement and disengagement under high wind conditions. This has now been extended to cater for an articulated rotor by modelling the droop and anti-flap stop mechanisms by high rate linear springs.. Much increased blade deflections are predicted, as anticipated, along with the possibility of blade tip/tail boom contact at a high enough wind speed. The importance of the higher modes in the description of the phenomenon is demonstrated. A comparison of the theoretical model with an experiment using a full size Puma aircraft is presented.

Type
Research Article
Information
The Aeronautical Journal , Volume 96 , Issue 956 , July 1992 , pp. 233 - 239
Copyright
Copyright © Royal Aeronautical Society 1992 

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References

1. Newman, S. J. A theoretical model for predicting the blade sailing behaviour of a semi-rigid rotor helicopter. Vertica, 1990, 14, (4), pp 531–544.Google Scholar