| 摘要 |
The method involves calculating an elliptical orbit (201) obtained by rotation of another elliptical orbit around an axle that connects a periapsis and an apoapsis. An operation allowing the satellite to join the former elliptical orbit is determined (202). Battery mass allowing maintenance of the satellite is calculated (203) under operation for the former maximum eclipse duration to calculate fuel mass necessary to carry out the operation, where sum of mass of fuel and the battery mass is not greater than a value of another mass of the battery. An independent claim is also included for a device for optimizing fuel mass of a satellite. |
