Satellite Stabilization

The satellite once placed in its orbit, experiences various perturbing torques. These include gravitational forces from other bodies like solar and lunar attraction, magnetic field interaction, solar radiation pressure, etc. Due to these factors, the satellite orbit tends to drift and its orientation also changes. The satellite's position thus needs to be controlled both in the east-west as well as the north-south directions. The east-west location needs to be maintained to prevent radio frequency (RF) interference from neighboring satellites. It may be mentioned here that in the case of a geostationary satellite, a 10 drift in the east or west direction is equivalent to a drift of about 735 km along the orbit. The north-south orientation has to be maintained to have proper satellite inclination. The attitude and orbit control system maintains the satellite position and its orientation and keeps the antenna correctly pointed in the desired direction. The orbit control is performed by firing thrusters in the desired direction or by releasing a jet of gas. It is also referred to as station keeping.
In a spin-stabilized satellite, the satellite body is spun at a rate between 30 and 100 rpm about an axis perpendicular to the orbital plane. Like a spinning top, the rotating body offers inertial stiffness, which prevents the satellite from drifting from its desired orientation. Spin-stabilized satellites are generally cylindrical in shape. For stability, the satellite should be spun about its major axis, having a maximum moment of inertia. To maintain stability, the moment of inertia about the desired spin axis should at least be 10 % greater than the moment of inertia about the transverse axis.
There are two types of spinning configurations employed in spin-stabilized satellites. These include the simple spinner configuration and the dual spinner configuration. In the simple spinner configuration, the satellite payload...

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