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A spacecraft in orbit always needs to stabilize the attitude against the external disturbance torques acting on it. Attitude control usually needs to be autonomous or semi-autonomous. On Alsat-1, the available actuators are reaction/momentum wheels and magnetic torquing. An analytic solution of Nadir attitude pointing equation of gravity gradient satellite stabilized is presented. The attitude equation is Euler linearised equation for near Nadir pointing axially symmetric satellite including only gravity gradient torque and assuming other torques such as magnetic torque, aerodynamic torque, solar radiation pressure torque and controller are constants. The obtained analytical solution was compared to numerical solution of satellite attitude equation.
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