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

Table 4

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

𝛿𝑒	Variable	Fault size	Delay time
Elevator	2^∘	5	𝛿𝑎 s
Aileron	2^∘	3	𝛿𝑟 s
Rudder	2^∘	6	𝛿th s
Throttle aperture %	6	3%	𝜈=8 s