The static margin (SM) is given by:
where l is the rolling moment and β is the sideslip angle. Flight Stability And Automatic Control Nelson Solutions
An aircraft has a static margin of 0.2 and a pitching moment coefficient of -0.05. Determine the aircraft's longitudinal stability. The static margin (SM) is given by: where
Cm = ∂m / ∂α
The controller can be designed using the following transfer function: Flight Stability And Automatic Control Nelson Solutions
The pitching moment coefficient (Cm) is given by: