| 摘要 |
1. A method of changing the orbit of a space vehicle allowing among others a transition from a highly elliptic orbit (2) to a circular orbit (4) possibly geosynchronous and of different inclination, according to which the vehicle is made to follow a plurality of successive intermediate orbits (4A-4N) by means of speed increments in directions approximatively tangent to the orbits, resulting from accelerations compatible with the mechanical behaviour of the vehicle in operational configuration, such accelerations being modulated so as to ensure the desired direction to the resultant, said method being characterized in that it consists of : - aiming with a launcher at a transfer orbit (2) the apogee (3A) of which is close to the desired value for the final orbit (4), - making the vehicle change from such transfer orbit (2) to the final orbit (4) through successive intermediate orbits (4A, 4B ... 4N) the apogees of which are adjoining but the perigees of which get closer to the desired final value, by means of a succession of speed increments delivered in the immediate neighbourhood of the successive apogees resulting from accelerations obtained by means of motors (12) intended for subsequent orbit and attitude control during the operational life of the vehicle, and - modulating such accelerations depending on information provided by speed or angular position sensors, also usable in the other flight phases of the vehicle. |
