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Dynamics & Control 3 Degree Exam September 1999

Dynamics & Control 3 Degree Exam September 1999

Introductory Circuit Analysis (13th Edition)
Introductory Circuit Analysis (13th Edition)
13th Edition
ISBN:9780133923605
Author:Robert L. Boylestad
Publisher:Robert L. Boylestad
Chapter1: Introduction
Section: Chapter Questions
Problem 1P: Visit your local library (at school or home) and describe the extent to which it provides literature...
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Dynamics & Control 3 Degree Exam September 1999 5. Figure Q5 shows the block diagram of a satellite attitude control system. The reference attitude is Or whilst the actual attitude is denoted by Oc. The satellite has a moment of inertia of J about its axis of rotation whilst K and K, are control system gains. The control system also acts to eliminate unwanted rotations due to a disturbance torque D. a) Derive the transfer function relating actual attitude to reference attitude, Og(s)* b) Derive the transfer function relating actual attitude to disturbance, c D(s) Control 3 Section 2 Tutorial: Basics of Control System Analysis c) A reference input consisting of a step change of 5° attitude is applied at the same instant that the satellite experiences a disturbance equivalent to a step change of 50 Nm. Given the data below derive an expression for the satellite's attitude 0(t) due to these inputs. J = 25 kg m? K = 500 Nm/rad K, = 100 Nms/rad D(s) OR(s) Oc(s) K Js? K, Figure Q5.
Transcribed Image Text:Dynamics & Control 3 Degree Exam September 1999 5. Figure Q5 shows the block diagram of a satellite attitude control system. The reference attitude is Or whilst the actual attitude is denoted by Oc. The satellite has a moment of inertia of J about its axis of rotation whilst K and K, are control system gains. The control system also acts to eliminate unwanted rotations due to a disturbance torque D. a) Derive the transfer function relating actual attitude to reference attitude, Og(s)* b) Derive the transfer function relating actual attitude to disturbance, c D(s) Control 3 Section 2 Tutorial: Basics of Control System Analysis c) A reference input consisting of a step change of 5° attitude is applied at the same instant that the satellite experiences a disturbance equivalent to a step change of 50 Nm. Given the data below derive an expression for the satellite's attitude 0(t) due to these inputs. J = 25 kg m? K = 500 Nm/rad K, = 100 Nms/rad D(s) OR(s) Oc(s) K Js? K, Figure Q5.
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