2747102-A1 cites 5 patents.

A spiral trajectory is described to the space vehicle comprising a number of intermediate orbits (104 A-P) through a single continuous firing of the jets mounted on the space vehicle. During the first phase, the perigee is increased and the apogee is changed in a given direction while the inclination of the intermediate orbit becomes closer to the aimed orbit. In a second phase, the perigee and apogee are independently changed in predetermined constant directions while the inclination is converged until all approximate to the required orbit (107). If perigee and apogee increase in the first phase, there is a third phase in which the eccentricity of the orbit is changed to a final value.

Title
System and method of bringing into orbit a spacecraft with high specific impulse thrusters
Application Number
FR19960004330 19960405
Publication Number
2747102 (A1)
Application Date
April 5, 1996
Publication Date
October 10, 1997
Inventor
Koppel Christophe
FR
Assignee
Europ Propulsion
FR
IPC
B64G1/40
B64G 01/40
G05D1/08
G05D 01/08
B64G1/24
B64G 01/24
B64G1/00
B64G 01/00
G05D1/08
G05D 01/08
B64G1/24
B64G 01/24
B64G1/00
B64G 01/00
B64G1/26
B64G 01/26
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