The tabular display shows:
- The times when the control loop is linearized.
- The computed gain and phase margins.
Margins that violate the specified bounds are shown in red. The phase margin bound is
violated towards the end of the simulation when the fuel mass and airplane velocity have
dropped. The Nichols plot indicates the small loop response variations as the fuel load
and aircraft velocity change.
Verifying Frequency-Domain Characteristics of an Aircraft