Patent ID: 8583297

Claim:
A method for optimization of mass of a satellite intended for a mission including a phase of orbit around a massive body in an elliptical first orbit, a shape and orientation of which are constrained by another phase of the mission, the first orbit including a first point also called the periapsis and a second point also called the apoapsis and being associated with a first maximum eclipse duration necessitating a first battery mass making it possible to maintain the satellite in operation during said first maximum eclipse duration, said method comprising: a step of calculation of an elliptical second orbit obtained by rotation of the first orbit about an axis connecting the periapsis and the apoapsis, the elliptical second orbit being associated with a second maximum eclipse duration less than the first maximum eclipse duration, a step of determination of a manoeuvre enabling the satellite to move to the second orbit, a step of calculation of a second battery mass making it possible to maintain the satellite in operation during the second maximum eclipse duration and of calculation of a mass of fuel necessary to effect the manoeuvre, and a step of calculation of a change of mass of the satellite by addition of the mass of fuel to the satellite and removal of a battery mass equivalent to a difference between the first battery mass and the second battery mass, a sum of the mass of fuel and the second battery mass being less than the first battery mass, wherein said steps are carried out by a calculation and determination device.