ISSN 0021-3454 (print version)
ISSN 2500-0381 (online version)

vol 67 / April, 2024

DOI 10.17586/0021-3454-2016-59-6-489-498

UDC 629.78


O. V. Filonin
SSAU, Department of Space Exploration; Professor

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Abstract. A compact microprocessor launching system for nanosatellites with defined separation parameters (initial velocity, zenithal and azimuthal angles) on a given trajectory is presented. The system includes magnetic induction ejector, the mechanisms for orientation of the discharge apparatus in the zenithal and azimuthal directions, and a microprocessor control module. The separation system may be mounted on any delivery vehicle or on the Russian segment of the ISS.
Keywords: nanosatellite, system of separated apparatus insertion, launching system, microprocessor control module

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