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Acceleration based manoeuvre flight control system for unmanned aerial vehicles

dc.contributor.advisorJones, T.en_ZA
dc.contributor.authorPeddle, Iain K.en_ZA
dc.contributor.otherStellenbosch University. Faculty of Engineering. Dept. of Electrical and Electronic Engineering.
dc.date.accessioned2008-09-03T10:13:22Zen_ZA
dc.date.accessioned2010-06-01T08:14:11Z
dc.date.available2008-09-03T10:13:22Zen_ZA
dc.date.available2010-06-01T08:14:11Z
dc.date.issued2008-12
dc.identifier.urihttp://hdl.handle.net/10019.1/1172
dc.descriptionThesis (PhD (Electrical and Electronic Engineering))--Stellenbosch University, 2008.
dc.description.abstractA strategy for the design of an effective, practically feasible, robust, computationally efficient autopilot for three dimensional manoeuvre flight control of Unmanned Aerial Vehicles is presented. The core feature of the strategy is the design of attitude independent inner loop acceleration controllers. With these controllers implemented, the aircraft is reduced to a point mass with a steerable acceleration vector when viewed from an outer loop guidance perspective. Trajectory generation is also simplified with reference trajectories only required to be kinematically feasible. Robustness is achieved through uncertainty encapsulation and disturbance rejection at an acceleration level. The detailed design and associated analysis of the inner loop acceleration controllers is carried out for the case where the airflow incidence angles are small. For this case it is shown that under mild practically feasible conditions the inner loop dynamics decouple and become linear, thereby allowing the derivation of closed form pole placement solutions. Dimensional and normalised non-dimensional time variants of the inner loop controllers are designed and their respective advantages highlighted. Pole placement constraints that arise due to the typically weak non-minimum phase nature of aircraft dynamics are developed. A generic, aircraft independent guidance control algorithm, well suited for use with the inner loop acceleration controllers, is also presented. The guidance algorithm regulates the aircraft about a kinematically feasible reference trajectory. A number of fundamental basis trajectories are presented which are easily linkable to form complex three dimensional manoeuvres. Results from simulations with a number of different aircraft and reference trajectories illustrate the versatility and functionality of the autopilot. Key words: Aircraft control, Autonomous vehicles, UAV flight control, Acceleration control, Aircraft guidance, Trajectory tracking, Manoeuvre flight control.en_ZA
dc.language.isoenen_ZA
dc.publisherStellenbosch : Stellenbosch University
dc.subjectUnmanned aerial vehiclesen_ZA
dc.subjectAcceleration controlen_ZA
dc.subjectManoeuvre trackingen_ZA
dc.subjectTheses -- Electrical and electronic engineeringen_ZA
dc.subjectDissertations -- Electrical and electronic engineeringen_ZA
dc.subject.lcshDrone aircraft -- Control systemsen_ZA
dc.subject.lcshFlight controlen_ZA
dc.subject.otherElectrical and Electronic Engineeringen_ZA
dc.titleAcceleration based manoeuvre flight control system for unmanned aerial vehiclesen_ZA
dc.typeThesisen_ZA
dc.rights.holderStellenbosch University


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