METHOD AND DEVICE FOR OPTIMIZATION OF THE MASS OF A SATELLITE

摘要

The invention concerns a method and a device for the optimization of the mass of a satellite. The method includes: a step (201) of calculation of elliptical second orbit (107) obtained by rotation of the first orbit (103) about an axis (106) connecting the periapsis (104) and the apoapsis (105), the elliptical second orbit (107) being associated with a second maximum eclipse duration (D2) less than the first maximum eclipse duration (D1), a step (202) of determination of a manoeuvre enabling the satellite to move to the second orbit (107), and a step (203) of calculation of a second battery mass (Mb2) making it possible to maintain the satellite in operation during the second maximum eclipse duration (D2) and of calculation of a mass of fuel (Mc) necessary to effect the manoeuvre).