Research Article
Fault Diagnosis for Linear Discrete Systems Based on an Adaptive Observer
Table 1
Signals in the F-16 simulation study.
| Signal | Not. | Meaning | Size |
| Inputs | | Spoiler angle (0.1 deg) | 1 | | Forward accelerations (m/s2) | 1 | | Elevator angle (deg) | 1 |
| Outputs | | Relative altitude (m) | | | Forward speed (m/s) | | | Pitch angle (deg) | |
| States | | Altitude (m) | | | Forward speed (m/s) | | | Pitch angle (deg) | | | Pitch rate (deg/s) | | | Vertical speed (deg/s) | |
| Faults
| | Spoiler angle actuator | 0.5 | | Forward acceleration actuator | 0.1 | | Elevator angle actuator | 1 |
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