Patent ID: 6264145
Filing Date: 2001-07-24
Classification: B64G,F02K

Abstract:
A satellite adapted to be spin-stabelized in geostationary orbit comprising:a satellite body having a spin rotation axis;a cylindrical solar generator disposed circumferentially around said satellite body;at least two equipments axially and oppositely disposed on said satellite body; andan apogee maneuvering system disposed along said spin rotation axis, said apogee maneuvering system being secured to said satellite body opposite one of said at least two equipments, said apogee maneuvering system comprising at least two thrusters oriented parallel to said spin rotation axis, each one of said at least two thrusters being offset from said spin rotation axis by an equal desitance, said at least two thrusters being equi-angularly spaced with respect to an other of said at least two equipments, said at least two thrusters further being connected to a common liquid propellant feed system.