The transfer function for an AFTI/F-16 aircraft relating angle of attack, a(t), to elevator de- flection,...

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The transfer function for an AFTI/F-16 aircraft relating angle of attack, a(t), to elevator de- flection, &e(t), is given by G(s) = 0.072 (s+3) (s +0.05s +0.04) (s+0.7) (s+1.7) (s +0.08s +0.04) Assume the block diagram shown in Figure 2 for controlling the angle of attack, a, and do the following: a) For Gc= 1, find the following: 1) What is the system type and the appropriate error constant associated with the system type? 2) What are the Gain-Margin and Phase Margin? 3) Plot the s-plane and define if the system is stable or not. b) Use MATABL to design a PD controller to have a percent overshoot 3%, rise time 0.2 second. Commanded angle of attack c) Use MATLAB to simulate your controlled system. Compare the results of the simula- tion with the requirements in Part (b). (s) + Controller & Aircraft G(s) (2) G(s) Actual angle of attack a(s) Figure 2: Simplified block diagram for angle of attack control. The transfer function for an AFTI/F-16 aircraft relating angle of attack, a(t), to elevator de- flection, &e(t), is given by G(s) = 0.072 (s+3) (s +0.05s +0.04) (s+0.7) (s+1.7) (s +0.08s +0.04) Assume the block diagram shown in Figure 2 for controlling the angle of attack, a, and do the following: a) For Gc= 1, find the following: 1) What is the system type and the appropriate error constant associated with the system type? 2) What are the Gain-Margin and Phase Margin? 3) Plot the s-plane and define if the system is stable or not. b) Use MATABL to design a PD controller to have a percent overshoot 3%, rise time 0.2 second. Commanded angle of attack c) Use MATLAB to simulate your controlled system. Compare the results of the simula- tion with the requirements in Part (b). (s) + Controller & Aircraft G(s) (2) G(s) Actual angle of attack a(s) Figure 2: Simplified block diagram for angle of attack control.

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