Given a spacecraft attitude control system shown in Fig. 2: R(s) ● Control Law ● K(s) ● Actuator 2 s+10 Figure 2 (a) Show that a proportional control cannot stabilize the closed-loop system (b) Given the following requirements: Peak time tp ≤, seconds Settling time at 2% error t ≤4, seconds Natural frequency , <2, radians/second • Damping ratio > 0.4 20 0.08s +1 Sensor Spacecraft 1 10,² Y(s) (1) Design a PD control law K(s) of the form K(s+1) such that the closed-loop step response satisfies the above requirements (show the possible locations of the closed-loop poles on the complex plane; use Matlab to plot the system root locus and choose the smallest value of Kc that satisfies the given response requirements) (2) Compute the steady-state error to a unit step input (3) Compute the steady-state error to a unit ramp input

Given a spacecraft attitude control system shown in Fig. 2: R(s) ● Control Law ● K(s) ● Actuator 2 s+10 Figure 2 (a) Show that a proportional control cannot stabilize the closed-loop system (b) Given the following requirements: Peak time tp ≤, seconds Settling time at 2% error t ≤4, seconds Natural frequency , <2, radians/second • Damping ratio > 0.4 20 0.08s +1 Sensor Spacecraft 1 10,² Y(s) (1) Design a PD control law K(s) of the form K(s+1) such that the closed-loop step response satisfies the above requirements (show the possible locations of the closed-loop poles on the complex plane; use Matlab to plot the system root locus and choose the smallest value of Kc that satisfies the given response requirements) (2) Compute the steady-state error to a unit step input (3) Compute the steady-state error to a unit ramp input

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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