초록 ▼

The method serves to place a space vehicle, such as a satellite, on a target orbit such as the orbit adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that is significantly different from, and in particular more eccentric than the target orbit. The space

The method serves to place a space vehicle, such as a satellite, on a target orbit such as the orbit adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that is significantly different from, and in particular more eccentric than the target orbit. The space vehicle is caused to describe a spiral trajectory made up of a plurality of intermediate orbits while a set of high specific impulse thrusters mounted on the space vehicle are fired continuously and without interruption, thereby causing the spiral trajectory to vary so that on each successive revolution, at least during a first stage of the maneuver, perigee altitude increases, apogee altitude varies in a desired direction, and any difference in inclination between the intermediate orbit and the target orbit is decreased, after which, at least during a second stage of the maneuver, changes in perigee altitude and in apogee altitude are controlled individually in predetermined constant directions, while any difference in inclination between the intermediate orbit and the target orbit continues to be reduced until the apogee altitude, the perigee altitude, and the orbital inclination of an intermediate orbit of the space vehicle have substantially the values of the target orbit.

대표청구항 ▼

[ What is claimed is:] [1.] 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 t

[ What is claimed is:] [1.] 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.