Detection filters for aircraft sensor and actuator faults

The fault detection and isolation problem is developed for both actuator faults and sensor faults of an aircraft. Pertinent theorems and definitions are presented. The fault detection filter design is treated as an eigensystem assignment problem. A computer algorithm which calculates the detection filters is discussed. Detection filter gains are developed for a linear aircraft model which augments actuator dynamics and a simplified wind gust model. A simulation of various faults and the performance of the detection filters are developed. Results indicate potential for improving fault-tolerant control system designs.