Clβ = ∂l / ∂β
Design an autopilot system to control an aircraft's altitude. Flight Stability And Automatic Control Nelson Solutions
where n is the yawing moment.
where m is the pitching moment and α is the angle of attack. Clβ = ∂l / ∂β Design an autopilot
For directional stability, the following condition must be satisfied: Flight Stability And Automatic Control Nelson Solutions
where l is the rolling moment and β is the sideslip angle.
