Dynamics & Control 3 Degree Exam September 19995. Figure Q5 shows the block diagram of a satellite attitude control system. The reference attitude is Orwhilst the actual attitude is denoted by Oc. The satellite has a moment of inertia of J about its axis ofrotation whilst K and K, are control system gains. The control system also acts to eliminate unwantedrotations 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, cD(s)Control 3Section 2 Tutorial: Basics of Control System Analysisc) A reference input consisting of a step change of 5° attitude is applied at the same instant that thesatellite experiences a disturbance equivalent to a step change of 50 Nm. Given the data below derivean expression for the satellite's attitude 0(t) due to these inputs.J = 25 kg m?K = 500 Nm/radK, = 100 Nms/radD(s)OR(s)Oc(s)KJs?K,Figure Q5.

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Engineering

Electrical Engineering

Dynamics & Control 3 Degree Exam September 1999

Introductory Circuit Analysis (13th Edition)

13th Edition

ISBN:9780133923605

Author:Robert L. Boylestad

Publisher:Robert L. Boylestad

Chapter1: Introduction

Section: Chapter Questions

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Question

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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