From the main problem, the open-loop transfer function for the aircraft pitch dynamics is 8(s) 1.151s +0.1774 G(S) = A(S

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From The Main Problem The Open Loop Transfer Function For The Aircraft Pitch Dynamics Is 8 S 1 151s 0 1774 G S A S 1 (45.49 KiB) Viewed 32 times

From the main problem, the open-loop transfer function for the aircraft pitch dynamics is 8(s) 1.151s +0.1774 G(S) = A(S) s3 +0.739s2 +0.921s where the input is elevator deflection angle and the output is the aircraft pitch angle. For the original problem setup and the derivation of the above transfer function please refer to the Aircraft Pitch: System Modeling page. For a step reference of 0.2 radians, the design criteria are the following. Unit-step input Overshoot less than 10% ● . Rise time less than 2 seconds Setting time less than 10 seconds. • Steady-state error less than 2% Recall from the Introduction: PID Controller Design page that the transfer function for a PID controller is the following. Ge(s) = Kp + K + K₁ Kas² + K₂s + Ki S Calculation Poles and Zeros and Root-locus and PI, PID Controller + Kas =