Method and a system for launching satellites simultaneously on non-coplanar orbits by using highly eccentric orbits and atmospheric braking

A method of launching satellites simultaneously on non-coplanar orbits, in which a first satellite is put on a launcher suitable for placing said first satellite practically directly on a first final orbit having first orbital parameters with a first eccentricity value, a first inclination value, and a first apogee value, and in which at least one second satellite is put on the launcher to be placed on a second final orbit having second orbital parameters with a second eccentricity value, a second inclination value, and a second apogee value which are substantially different from the corresponding values of the first orbital parameters provided by the launcher and applied to the first satellite launched simultaneously with the second satellite,

• wherein, to place the second satellite on its orbit, a first maneuver is performed to transfer it onto a highly elliptical waiting orbit having an apogee that is situated typically in the range 50,000 km to 400,000 km, and having a semi-major axis situated in the initial orbit plane, during a second maneuver situated in the vicinity of the apogee of the waiting orbit, the inclination and the perigee of the waiting orbit are changed to place the second satellite on an intermediate orbit, a third maneuver is performed for mid-course correction of the intermediate orbit, a fourth maneuver is performed, including at least one step that makes use of atmospheric breaking in the vicinity of the perigee of the intermediate orbit, to lower the altitude of the apogee of the intermediate orbit, and a fifth maneuver is performed during which an impulse is supplied to the second satellite at apogee of the intermediate orbit so as to raise its perigee and transform the intermediate orbit into said second final orbit constituted by an inclined low orbit.