Design and Analysis of Robust Fault Diagnosis Schemes for a Simulated Aircraft Model

Table 2

PM FDI technique: minimal step faults with 𝑐_𝑖(𝑡).

𝛿𝑒	Variable	Fault size	Delay time
Elevator	2^∘	18	𝛿𝑎 s
Aileron	3^∘	6	𝛿𝑟 s
Rudder	4^∘	8	𝛿th s
Throttle aperture %	2	15%	𝜈=4 s