Modeling and Control of an Aircraft System (for Aerospace Applications)

Abstract

This thesis presents design of a basic mathematical model of an aircraft system. The proposed model is implemented on a nonlinear aircraft system with six degree of freedom, which is linearized into lateral and longitudinal ight dynamics mode of an aircraft system. To achieve the specific transient performances of the both longitudinal and lateral ight dynamics mode, a model predictive control strategy is designed. The proposed model predictive control scheme is implemented on the developed aircraft model with six degree of freedom. Simulation were pursuit using Matlab / Simulink. The result obtained envisages that the aircraft system using the proposed model predictive controller achieves the good transient performances. This thesis also presents a design of Kalman Filter based diagnostic technique for deficiency identification and segregation of sensors and actuators in an air ship gas turbofan engine. A mathematical model of a two shaft turbofan engine is develop in Matlab / Simulink. The proposed Kalman Filter based diagnostic technique consist of a bank of Kalman Filters used to recognize and separate sensor aw. Each of the Kalman Filter is composed in view of a particular speculation for identifying a particular sensor issues. At the point when an issue happen, all channel aside from the one utilizing the right speculation will deliver huge estimation slip, from which a particular deficiency is secluded. The failure in the sensor in uence the attributes of the residual signal of the Kalman Filter. The proposed diagnostic technique is implemented on the developed two shaft turbofan engine. Simulation were pursuit utilizing Matlab / Simulink.