Method for controlling the pitch attitude of a satellite by means of solar radiation pressure

A method of controlling the attitude of a satellite relative to a predetermined axis thereof, said satellite comprising:

• a satellite body;
• at least one planar surface member exposed to solar radiation pressure, said at least one planar surface member having a central axis extending in a first direction away from said satellite body, said first direction being substantially coaxial with said predetermined axis;
• an attitude measuring device adapted to measure an attitude error angle about said predetermined axis;
• and
• a computer connected to said attitude measuring device and adapted to determine from the attitude error anile the value of an attitude correction torque to be applied about said predetermined axis, said method comprising the step of:
• tilting said central axis of said at least one planar surface member relative to said predetermined axis such that said central axis of said at least one planar surface member is tilted away from said predetermined axis substantially transversely to said solar radiation pressure so as to generate a torque about said predetermined axis substantially equal to said value of said attitude correction torque.