An aircraft has a static margin of 0.2 and a pitching moment coefficient of -0.05. Determine the aircraft's longitudinal stability.
Altitude Sensor → Controller → Actuator → Aircraft → Altitude Sensor Flight Stability And Automatic Control Nelson Solutions
SM = (xcg - xnp) / c
The directional stability derivative (Cnβ) is given by: An aircraft has a static margin of 0
Substituting the given values, we get:
where Kp, Ki, and Kd are the controller gains. we get: where Kp
The static margin (SM) is given by: