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Unformatted text preview: Flight Control Systems Test #3 : Take-Home Dr. Bishop - Spring 2010 Due Thursday, April 29, 2010 Satellite Attitude Controller with Control Moment Gyros Consider a small satellite with active pitch attitude control. The small satel- lite is operating in a circular orbit at an altitude of 275 km. We are interested in controlling the pitch attitude of the satellite using a control moment gyro (CMG) considering the effects of gravity gradient torques and aerodynamic dis- turbances. For a detailed description of this problem, see Chapter 3 of Dorf &amp; Bishop. The model of the spacecraft is given by ( s ) U ( s ) = G ( s ) = 1 I y s 2- 3 n 2 , where ( s ) is the pitch angle, U ( s ) is the CMG input torque, I y = 0 . 2 kg-m 2 , := I z- I x , I x = 0 . 1 kg-m 2 , I z = 0 . 01 kg-m 2 , n = 0 . 0011 rad/s is the orbital angular velocity. When ( s ) = 0 the satellite is Earth pointing, as desired. In other words, the desired pitch angle is d ( s ) = 0. The gravity gradient torque) = 0....
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- Spring '10