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Given : The following control system Aircraft pitch loop model Aircraft Dynamics Controller ref ( s ) 20.9 s 2 + 5.57 s + 20.784 s( s + 8.4) Gyro 1...

New Problem needs to solve for Control System.
Given : The following control system Aircraft pitch loop model Aircraft Dynamics Controller Gyro ( ) ref s θ ( ) actual s θ 14.784 ( 8.4) s s + 2 20.9 5.57 20.9 s s + + 1 -
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1- Determine the Closed-Loop Transfer function in rational polynomial form Required : The following control system ( ) ( ) ( ) ( ) actual ref s N s s D s θ θ = 2- Determine and plot the unit step response of the system use MATHLAB to compute and plot the unit step response. 3- From the plot on step 2 (using zoom-in techniques) determine the following time-domain specifications (Be very clear in all your plot determinations) 10 points 10 points 20 points 1 1 1 ( ) ( ) ( ) ( ) actual actual N s t L s L s D s θ θ - - = = Peak Time [ sec ] PO% Settling Time [ sec ]
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