Solar torque compensation for a satellite

Claim 1

An attitude control system for a spin stabilized spacecraft to compensate for torques due to solar pressure, said spacecraft having a panel with a set of solar cells adapted to receive solar radiant energy for conversion to electrical power, said panel being arranged for deployment from the spacecraft including means for orienting the panel toward the sun, the improvement comprising: a. electromagnetic means included in said panel for generating a magnetic flux having a magnetic field extending normal to the plane of said panel for reacting with the magnetic field of the earth, said electromagnetic means comprising a single electromagnetic air core coil having at least one turn of wire disposed in the peripheral portion Of said solar cell panel, and in a plane parallel with the plane of said solar panel, and b. means for energizing said electromagnetic means in response to solar energy received on said solar panel such that a magnetic flux therefrom reacts with the magnetic field of the earth to produce a magnetic torque substantially of equal magnitude and opposite direction to the torque developed on said spacecraft by the solar pressure of the solar radiant energy on said panel.