A Design Study for Multivariable Feedback Control System Regulation for Aircraft Turbo-Jet Engines
The British University in Dubai (BUiD)
This research work deals with the design of a multivariable control system for aircraft jet engines. It is motivated by the desire to exploit recent advances in design strategy emphasizing the dissipation of minimum control effort, and the need to investigate suitability and applicability compared with previous applied methodologies. Attention is paid to the energy consumed by the control system itself; in order to minimize wear, cost refits changes and noise generation improving thereby the reliability of aircraft engines. The first part of the research deals with introduction of gas turbine engines. The research theme problem states the design of a multivariable control system for a twin spool turbo-jet engine model with two inputs. These are the fuel flow rate and nozzle area controlling the high and low pressure spool speeds. Objectives are defined as evaluating the proposed controller in comparison to previous designs. This study is presented based upon evaluating the performance and power consumption of the proposed controller compared with other controllers designed in accordance with classical and modern control theory. Previous work conducted to design a controller for the theme problem is reviewed. This includes a controller designed by the Inverse Nyquist Array method and the one synthesized by optimal control method. The research concludes that the new least effort control technique gives superior performance and disturbance recovery. It also generates the simplest controller. This should promote the rapid implementation of this design theory for aircraft engines and for general multivariable applications in near future.
DISSERTATION WITH DISTINCTION
multivariable feedback control, system regulation, aircraft turbo-jet engines, gas turbine engines, power consumption