ABSTRACT
Failure of sensors used to provide a feedback signal in a control system can cause serious deterioration in performance of the system, and even instability may be observed. Based on knowledge of aircraft engine systems, fault in such Air-breathing Combustion Systems (ACS) with no rotating parts is primarily due to the pressure sensors. This chapter discusses novel fault detection and accommodation (FDA) algorithm based on the analytical redundancy-based technique for ACS. For the purpose of simulation, the combustion system is modelled as three sub-systems: intake, combustor and nozzle. The non-linear plant dynamics is complex and it consumes significant resources during simulations. Since, the FDA algorithm is to be implemented in real time it should be based on a simpler linear model that can be processed much faster. A controller for an ACS was designed initially. The controller’s main objective is to regulate the thrust so that the desired acceleration is obtained at all flight conditions while maintaining supercritical intake operation.
