Evaluation of relative final mass of a nanosatellite delivered to the near-earth space using a pulsed launcher and a pulsed correcting thruster

Propelling a nanosatellite to orbit using a pulsed launcher is considered. According to the accepted model, the nanosatellite acquires an initial liftoff speed inside the pulsed launcher; then it passively flies a trajectory up to the highest point at an altitude of 100 km (above the Karman line). At the highest point, a pulsed correcting thruster transfers the satellite to the circular orbit. The orbital injection can be implemented from the Earth's surface, from the airplane or aerostat. The correcting impulse needed for the nanosatellite to transfer from the suborbital trajectory to the circular orbit with an altitude of 100 km is evaluated. The results enable the rational launch parameters to be estimated which minimize the costs of nanosatellite delivery to the near-Earth space. Advantages of pulsed launchers in comparison with traditional delivery aids are revealed. The availability of the marked "stability shelves" makes it possible to use technologies of manufacturing of acceleration systems with broad limits for parameters of nanosatellites and pulsed accelerators. This scheme is self-stabilizing, which permits the technology of manufacturing of both pulsed launcher and nanosatellite to be substantially simplified and cheapened.

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