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Simulation of automatic helicopter deck landings using nature inspired flight control

Published online by Cambridge University Press:  03 February 2016

M. Voskuijl ,
G. D. Padfield ,
D. J. Walker ,
B. J Manimala  and
A. W. Gubbels
M. Voskuijl
Affiliation:
M.Voskuijl@tudelft.nl, Faculty of Aerospace Engineering, Delft University of Technology, Delft, The Netherlands
G. D. Padfield
Affiliation:
Department of Engineering, The University of Liverpool, Liverpool, UK
D. J. Walker
Affiliation:
Department of Engineering, The University of Liverpool, Liverpool, UK
B. J Manimala
Affiliation:
AgustaWestland (UK), Yeovil, UK
A. W. Gubbels
Affiliation:
Institute for Aerospace Research (IAR), National Research Council (NRC), Ottawa, Canada
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Abstract

Research studies have indicated that the optical flow parameter, time to close tau, is the basis of purposeful control in the animal world, and used by both fixed wing and helicopter pilots during manoeuvring. This parameter is defined as the instantaneous time to close a gap (spatial or force) at the current closing rate. A novel automatic flight control strategy has been developed that makes use of optical flow theory and in particular, the parameter tau. This strategy has been applied to two distinct problems; (1) the landing of a helicopter on a ship and (2) the lateral repositioning of a helicopter. The first is a challenging case because the landing of a helicopter on a ship is one of the most dangerous of all helicopter flight operations. Furthermore, helicopters are often subject to torque oscillations during rapid collective control, which increases pilot workload significantly when operating with low power margins and/or whilst performing tasks that require accurate heave control. The second case demonstrates the generality of the technique. Both automatic manoeuvres were simulated successfully within desired limits, with the novel control strategy creating a ‘natural’, smooth, tau motion.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1151 , January 2010 , pp. 25 - 34
Copyright
Copyright © Royal Aeronautical Society 2010 

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