Acceleration based manoeuvre flight control system for unmanned aerial vehicles

SUNScholar Research Repository

Show simple item record

dc.contributor.advisor Jones, T. en_ZA
dc.contributor.author Peddle, Iain K. en_ZA
dc.contributor.other Stellenbosch University. Faculty of Engineering. Dept. of Electrical and Electronic Engineering.
dc.date.accessioned 2008-09-03T10:13:22Z en_ZA
dc.date.accessioned 2010-06-01T08:14:11Z
dc.date.available 2008-09-03T10:13:22Z en_ZA
dc.date.available 2010-06-01T08:14:11Z
dc.date.issued 2008-12
dc.identifier.uri http://hdl.handle.net/10019.1/1172
dc.description Thesis (PhD (Electrical and Electronic Engineering))--Stellenbosch University, 2008.
dc.description.abstract A 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.iso en en_ZA
dc.publisher Stellenbosch : Stellenbosch University
dc.subject Unmanned aerial vehicles en_ZA
dc.subject Acceleration control en_ZA
dc.subject Manoeuvre tracking en_ZA
dc.subject Theses -- Electrical and electronic engineering en_ZA
dc.subject Dissertations -- Electrical and electronic engineering en_ZA
dc.subject.lcsh Drone aircraft -- Control systems en_ZA
dc.subject.lcsh Flight control en_ZA
dc.subject.other Electrical and Electronic Engineering en_ZA
dc.title Acceleration based manoeuvre flight control system for unmanned aerial vehicles en_ZA
dc.type Thesis en_ZA
dc.rights.holder Stellenbosch University


Files in this item

This item appears in the following Collection(s)

Show simple item record