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Unformatted text preview: Flight Control Systems Test #3 : Take-Home Dr. Bishop - Fall 2007 Due Tuesday, December 4, 2007 Satellite Attitude Controller Consider a small satellite with active attitude control to perform photo re- connaissance of Earth as illustrated in Figure 1. We are interested in controlling the pitch attitude of the satellite so that a camera can be accurately pointed towards the Earth in the presence of environmental disturbance torques. Figure 1: Earth pointing small satellite for photo reconnaissance. The transfer function of the spacecraft relating the input torque to the output pitch attitude is G ( s ) = 1 Js 2 , where the pitch axis moment of inertia J = 0 . 01 kg-m 2 . The satellite employs a reaction wheel as the actuator. The spin rate of the reaction wheel can be controlled. If we want to rotate the satellite, we start the reaction wheel spinning, and in order to conserve angular momentum, the satellite will begin rotating in the opposite direction. A torque is thus applied to the satellite. The transfer function of the reaction wheel is G a ( s ) = 2 s + 10 ....
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