FIELD: transport.
SUBSTANCE: invention relates to aircraft power supply systems. Proposed system P is designed to increase aircraft power supply system output and consists of the following components: power supply 10 with channel K extending between two openings (4, 5, 85, 95) at fuselage R of aircraft F, turbine 12 with generator 14 arranged in channel K, covering device 6 to stop front opening 4, open-close device 61 and unlocking device 61 connecting with covering device 6. Said unlocking device locks covering device when current of first intensity signal is fed thereto and unlocks it when current of second intensity signal is fed thereto. Note here that signal second intensity exceeds the first one by preset magnitude. Besides it includes drive device 41, 42 functionally coupled with open-close device 61 to generate go-no-go signal, go-switch 27 functionally coupled with power generation control device 25 and with unlocking device 62. The latter controls unlocking device 62 by second signal intensity to lock covering device 8 in response to power request signal from power generation control device 25.
EFFECT: higher reliability of power supply.
14 cl, 3 dwg
