| 摘要 |
1. A method for launching satellites into geostationary orbit, characterized in that satellites are launched by a launch vehicle having launching means the satellites are located in one capsule with the launching means, the capsule is launched into circular orbit, changing apogee of the orbit, then its perigee and transfer the launching vehicle into a geostationary orbit, where the satellites are separated, characterized in that two satellites are located in the capsule, the mass of the first of them is selected being essentially greater the mass of the second satellite which is adapted to local covering of territory and located in the capsule between the launching means and the first satellite which is adapted to global and local covering of the territory and which is separated first on the geostationary orbit, wherein the second satellite is separated and turned on the geostationary orbit turn with time delay sufficient to turn the first satellite, the mass of the second satellite is substantially equal to the difference between the mass of the first satellite and the payload mass of the launch vehicle. 2. The method according to claim 1, characterized in that the mass M2 of the second satellite is determined from the ratio M1 ( (5.4-6.9) M2, where M1 is the mass of the first satellite. 3. The method according to claim 1, characterized in that the mass M2 of the second satellite is determined being equal to 380-420 kg and the mass M1 of the first satellite is determined to be 2300-2600 kg.
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