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	𝑢1	Spoiler angle (0.1 deg)	1
	𝑢2	Forward accelerations (m/s^2)	1
	𝑢3	Elevator angle (deg)	1
Outputs	𝑦1	Relative altitude (m)	10^−4
	𝑦2	Forward speed (m/s)	10^−6
	𝑦3	Pitch angle (deg)	10^−6
States	𝑥1	Altitude (m)	10^−4
	𝑥2	Forward speed (m/s)	10^−4
	𝑥3	Pitch angle (deg)	10^−4
	𝑥4	Pitch rate (deg/s)	10^−4
	𝑥5	Vertical speed (deg/s)	10^−4
Faults	𝑓1	Spoiler angle actuator	0.5
	𝑓2	Forward acceleration actuator	0.1
	𝑓3	Elevator angle actuator	1