Method of changing orbit of a satellite, in particular for injection in a geostationary orbit and satellite implementing said method

摘要

Method of changing orbit of a space permitting the passage of a substantially elliptical orbit has a circular orbit and satellite implementing said method. / p & & p & the process is not specific of the propulsion units, but those which are indispensable to the control of the orbit and attitude during the life of the satellite operational. When the satellite has been used for a launcher on a transfer orbit apogee which is close to the final value desired, its axis oz is a point on the ground, by means of detectors 7, 8. The axis oy is in the plane of the orbit and its solar panels 10 are extended in the direction ox north and south -. In the vicinity of the climaxes successive increments of the speed are supplied by the activation of the tuyeres of the control of the orbit and attitude 12 located on the face 11 of the satellite. After a few revolutions whose perigees are increasingly students, the final orbit is reached. / p & & p & the invention can be used for the circular orbit of a geostationary satellite is provided with propulsion units capable of maintaining a longitude.