Question

Please answer all the questions with MATLAB and also upload the code. Thanks.

3 Experiment - Matlab controller complexity and steady-state 3.1 Consider the satellite-attitude control problem shown in following figure where the normalized parameters are J 10 spacecraft inertia; N-m-sec2 /rad erreference satellite attitude; rad actual satellite attitude; rad Hy 1 sensor scale; factor volts/rad Hr = 1 reference sensor scale factor ; volts/rad w= disturbance torque: N-m H, D(s) Js Figure 4: Satellite attitude control Suppose kP = 8.3, k1 = 0.32, and kD error from graph. 53.95 and plot the graph for each cases and find the steady state a. Use proportional control, P, with Dc(s)-kp , and give the range of values for kp for which the system b. Use PD control and let Dc(s) = (kp +kDs) and determine the system type and error constant with c. Use PD control, let De(s)- (kp+kps) and determine the system type and error constant with respect d. Use PI control, let De(s)-(kp ki/s), and determine the system type and error constant with will be stable. respect to reference inputs to disturbance inputs respect to reference inputs Feedback Control Systems Lab 11. PID control e. Use PI control, let De(s)- (kp + kı/s), and determine the system type and error constant with f. Use PID control, let Dc(s) = (Kp + kl/s + kps) and determine the system type and error constant g. Use PID control, let De(s)(kp +ki/s + kps) and determine the system type and error constant respect to disturbance inputs with respect to reference inputs. with respect to disturbance inputs.

Answer 1

solve 'The ven that dicgcom ot the y stem PTih the b DAI 2 JS Stable usth oats on Jus oats les 2 10 -Ys) NCS) (OS ECS)

tus es 10S S30 Ecs) 2 kr (6c oS BTS ECS)