Modelling and Simulation of Fault Detection and Diagnosis for DC Actuator in Missile

Abstract

This thesis explores the application and validation of fault detection and diagnosis (FDD) methodologies for missile DC actuator systems. Traditional fault management strategies, such as hardware redundancy, are often impractical due to increased costs and reduced payload capacities. This research employs FDD techniques, which are central to active Fault Tolerant Control Systems (FTCS), to ensure timely detection and diagnosis of faults in missile systems. The primary objectives are to investigate common actuator faults and validate robust FDD algorithms through simulations. Undetected actuator faults can lead to catastrophic failures, emphasizing the need for effective FDD systems. The study examines faults in DC actuators, including issues with resistance, inductance, friction, and moment of inertia, and assesses their impacts on missile performance under both single and multi-parameter fault conditions. MATLAB and Simulink are used for modelling and simulating fault scenarios in DC actuator systems, which are key components of missile control. The methodologies include mathematical modelling, residual generation, parameter estimation, and fault injection to simulate various conditions. Simulations demonstrate the proposed FDD techniques' effectiveness in accurately identifying and diagnosing faults, showcasing improvements over traditional methods. The findings highlight that the effectiveness of the proposed FDD system depends on the timing of input signals relative to fault occurrence. While the system diagnoses single faults effectively, diagnosing combinations of three parameters requires additional time. This research contributes to enhancing fault detection capabilities in missile actuator systems through advanced FDD methodologies. Keywords: Aerospace, Aerospace Systems, Actuator Faults, Parmeter Estimation, State Space, Fault Detection and Isolation, Active Fault Tolerant Control Systems.