5. Figure 05 shows the block diagram of a satellite attitude control system. The reference attitude is 6R 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, b) Derive the transfer function relating actual attitude to disturbance "(3) 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(1) due to these inputs. J = 25 kg m2 K = 500 Nm/rad K, = 100 Nms/rad D(s) OR(s) Oc(s) K Js K, Figure Q5.
5. Figure 05 shows the block diagram of a satellite attitude control system. The reference attitude is 6R 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, b) Derive the transfer function relating actual attitude to disturbance "(3) 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(1) due to these inputs. J = 25 kg m2 K = 500 Nm/rad K, = 100 Nms/rad D(s) OR(s) Oc(s) K Js K, Figure Q5.
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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 6R
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, )
b) Derive the transfer function relating actual attitude to disturbance,
DS)
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(1) due to these inputs.
J = 25 kg m?
K = 500 Nm/rad
K, = 100 Nms/rad
D(s)
OR(S)
Oc(s)
K
Js
Ky
Figure Q5.
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