Patent ID: 6116543
Filing Date: 2000-09-12
Classification: B64G

Abstract:
A method of placing a space vehicle, such as a satellite, on a target orbit such as that adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that is substantially different from the target orbit and in particular more eccentric than the target orbit,wherein the space vehicle is subjected to a maneuver comprising a single continuous firing of a set of high specific impulse thrusters mounted on the space vehicle, during a first stage of the maneuver, the space vehicle is caused to describe a spiral trajectory made up of a plurality of intermediate orbits, progress of the spiral trajectory being controlled in such a manner that on each successive revolution, at least during the first stage of the maneuver, apogee altitude increases, perigee altitude increases to a lesser extent, and any difference in inclination between an intermediate orbit and the target orbit decreases, then, at least during a second stage of the maneuver, changes in perigee and apogee altitude are controlled individually in constant predetermined directions while any difference in inclination of an intermediate orbit relative to the target orbit continues to be reduced until the apogee altitude, the perigee altitude, and the orbital inclinations of an intermediate orbit of the space vehicle have reached substantially the values of the target orbit, andwherein during the second stage of the maneuver, until the end of continuous firing, on each successive revolution, apogee altitude of intermediate orbits is decreased while perigee altitude is increased.