Robust Control of High Altitude Long Endurance Unmanned Aerial Vehicles using Novel Lift Effectors

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Title: Robust Control of High Altitude Long Endurance Unmanned Aerial Vehicles using Novel Lift Effectors
Authors: Cook, Robert Graham
Item Type: Thesis or dissertation
Abstract: High-Altitude Long-Endurance Unmanned Aerial Vehicles (HALE UAVs) have been the focus for many researchers in the past decades, and are becoming more and more attainable as technology is improving. Recent interest into solar-powered HALE UAVs is leading the way to achieving flight-times which are not limited by a requirement for refuelling, and could continue for months at a time. Such aircraft have huge potential in providing reconnaissance or communications services, and could potentially take on the usual roles of satellites as a much cheaper alternative. One area of HALE UAV design which requires further technological developments is automated control of trajectory, and active alleviation of gusts. The latter concern is of particular interest to this thesis. In this work, a coupled flight dynamics and aeroelastic methodology will be introduced. This approach features a geometrically-exact beam model, which is required to capture the large deformations expected in such flexible aircraft, along with unsteady aerodynamics. The intrinsically nonlinear system is then linearised to provide an approximation to the system dynamics which is more approachable for control synthesis. With a linearisation of the system, robust linear control methods are applied to derive a controller which can reduce the loading onto the system, while simultaneously stabilising it and providing some degree of robustness which can still perform given the unmodelled dynamics that appear in the nonlinear system. This linear control approach will be investigated on two types of HALE UAV with very different dynamic responses to determine how well such control methods deal with nonlinearities, and what the limitations of such an approach may be to apply in real-life. In addition, various novel control effectors will be then considered for gust alleviation of a very flexible aircraft, using the closed-loop control as a method to fairly assess their effectiveness.
Issue Date: 2012
Date Awarded: Aug-2012
URI: http://hdl.handle.net/10044/1/9998
DOI: https://doi.org/10.25560/9998
Supervisor: Palacios Nieto, Rafael
Sponsor/Funder: Engineering and Physical Sciences Research Council ; QinetiQ (Firm)
Department: Aeronautics
Publisher: Imperial College London
Qualification Level: Doctoral
Qualification Name: Doctor of Philosophy (PhD)
Appears in Collections:Aeronautics PhD theses



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