Fault detection, diagnosis and control in a tactical aerospace vehicle
In this paper we propose a fault-tolerant control ( FTC ) scheme using multiple controller switching. The performance of this scheme is studied on a tactical aerospace vehicle. A parity space (PS) based residual generation approach is used to detect the fault. Once a fault is detected the diagnosis scheme identifies the faulty actuator. Using this information on-line reconfiguration of the controller is done based on the configuration of the existing healthy actuator. To implement this scheme no modification were done in hardware (H/W) configuration and only existing redundancies were utilised. Simulation with nonlinear 6-degree of freedom (6-DoF) model shows that the above fault tolerant control approach is able to reduce the probability of failure due to actuators.