Anderson, D. (1995) Simulation of Helicopter Manoeuvres Using an Individual Blade Rotor Model. Internal report no 9514. Technical Report. Department of Aerospace Engineering, University of Glasgow.
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Abstract
A control methodology is presented and applied to the simulation of helicopter manoeuvres using an individual blade rotor model. The novelty of constraining an individual blade/blade element rotorcraft model is explained with reference to some existing manoeuvre simulation techniques. A fully non-linear control algorithm is employed which estimates the controls required to maintain a constant flight path by minimising the error between the inertial frame flight path states predicted by the rotorcraft model, and those demanded by the flight path generator. A simple flight path generation model, based on Newtonian kinematics is used. Firstly, the algorithm is evaluated in a disturbance rejection role, negating the effect of obstruction-induced atmospheric turbulence. Secondly, a flare to hover manoeuvre is simulated and the results discussed. The effects of parameter changes within the control algorithm are also discussed and the results for changes in tolerance levels and the control application interval are presented. Finally an approach to an offshore oil platform, landing on the helideck, with the turbulence field included was performed. It is found that the control algorithm tracks the required flight path well in both still air and turbulence.
| Item Type: | Research Reports or Papers (Technical Report) |
|---|---|
| Status: | Published |
| Glasgow Author(s) Enlighten ID: | Anderson, Dr David |
| Authors: | Anderson, D. |
| College/School: | College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity |
| Publisher: | Department of Aerospace Engineering, University of Glasgow |
| Copyright Holders: | Copyright © 1995 Department of Aerospace Engineering, University of Glasgow |
| Publisher Policy: | Reproduced with the permission of the Department |
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