5. Figure Q5 shows the block diagram of a satellite attitude control system. The reference attitude is 0rwhilst the actual attitude is denoted by 0c. 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,Oc(s)OR(s)'Oc(s)b) Derive the transfer function relating actual attitude to disturbance,D(s) *c) 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)KJs2Kv

Answered: Image /qna-images/answer/6818c43b-de96-4107-bab6-8461257a0267.jpg

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 0c. 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, OR(S)' b) Derive the transfer function relating actual attitude to disturbance, . Oc(s) D(s)' 2 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 Js² K,

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 0c. 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, OR(S)' b) Derive the transfer function relating actual attitude to disturbance, . Oc(s) D(s)' 2 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 Js² K,

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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