FIELD: aircraft engineering.
SUBSTANCE: proposed device comprises platform with nano- or microsatellite. Besides, it incorporates rod, capacitors, orientation system with inner and outer cases, motors and bearings. Its magnetic inductance ejector incorporates two solenoid-type inductors tightly compressed by pressure spring. Said inductors are fitted in pairs into barrels fitted in armour armature from ferromagnetic. Its electronic control system incorporates microcontroller, communicator, charge control unit, drivers of motors, switches and winding leads selectors.
EFFECT: higher efficiency.
4 cl, 2 dwg
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