Abstract: The invention described here concerns the use of GPS (Global Positioning System) interferometry, or any similar satellite constellation, to estimate the attitude of a vehicle, and is particularly suited for LEO (Low Earth Orbit) satellites. The invention is based on a system of gyroscopic and interferometric sensors and a piece of software to process the data received by such sensors. The invention can be applied to any type of vehicle (terrestrial, naval, aircraft or spacecraft) to determine the attitude of the vehicle with respect to an inertial reference system.

Abstract: A triaxially stabilized satellite having a Cartesian axis system with mutually perpendicular X, Y and Z axes, two electric propulsors for orbital maneuvers and attitude control of the satellite and having respective versors including a right angle between them and lying in an X-Y plane, the versors being orientable in the plane about the Z axis to include a variable angle a with the X axis to impart two degrees of freedom of movement to the electric propulsors, the electric propulsors generating thrust vectors in line with the versors away from a center of gravity of the satellite at an intersection of the versors, the electric propulsors being firable independently and for respective angles of arc in their displacement with the degrees of freedom to maneuver the satellite orbitally, control attitude of the satellite and dissipate angular momentum of the satellite. The electric, preferably ionic, pulsars can be used with triaxially stabilized satellites with an LEO or GEO.