Flight Stability And Automatic | Control Nelson Solutions

where m is the pitching moment and α is the angle of attack.

Therefore, the aircraft is longitudinally stable. Flight Stability And Automatic Control Nelson Solutions

The lateral stability derivative (Clβ) is given by: where m is the pitching moment and α is the angle of attack

Gc(s) = Kp + Ki / s + Kd s

Altitude Sensor → Controller → Actuator → Aircraft → Altitude Sensor Flight Stability And Automatic Control Nelson Solutions

Therefore, the aircraft is laterally stable.

SM = (xcg - xnp) / c