Control of turbo shaft engine in hover flight using linear quadratic regulator (LQR)‎

Abstract EN

In this study, the Linear Quadratic Regulator (LQR) model has been obtained and the performance parameters have been estimated to minimize control effort.

in general, controlling a gas turbine engine is difficult because its system is very coupled, nonlinear, and sensitive to the control inputs and external disturbances that might destabilize the system.

due to these instabilities, it is crucial to use a control process that helps improve the system's performance, confirming stability and robustness.

The main aim of this paper is to develop a control system design using Linear Quadratic Regulator (LQR) to stabilize the gas turbine engine near hover flight.

To fulfill this objective, first of all, the nonlinear model of the turboshaft engine is linearized using the Taylor series theory.

The engine model has been demonstrated by a series of first-order differential and algebraic equations, the model is linearized and extracted in the state space formula to facilitate the analysis and design of a controller by LQR.

To explain the robustness of the controller, the impacts of disturbance are considered.

The calculations were performed using the MATLAB program.

The results show that using an LQR is a good solution for the SIMO gas turbine engine system, obtaining good stability, minimizing control effort, and refining the final behavior of the turboshaft engine.