COMBINED CONTROL ACTUATOR SYSTEM (OPTIONS) Russian patent published in 2017 - IPC F42B15/01 B64C13/36 B64C15/00 

FIELD: aviation.

SUBSTANCE: according to the first embodiment, servo unit and gas-dynamic control device are respectively provided with first and second gas ejector comprising low-pressure nozzle communicated with additionally installed the first and second airscoops of oncoming flow, high pressure nozzles communicated with the first and second airborne sources of pressurized gas that are run on the initial part of flight path at low speed pressure of the incident flow, and mixing chambers connected to gas feed channels respectively to the servo unit and gas-dynamic control device. According to the second embodiment, servo unit and gas-dynamic control device are respectively provided with first and second control valves containing working spaces connected respectively to the gas inlet channels to servo unit and gas-dynamic control device, and valve regulators, each of which has two rigidly connected inlet shutters, disposed between two respective inlet seats, wherein two inlet seats are communicated with additionally introduced airscoops of oncoming flow, and two oppositely located inlet seats are communicated respectively with the first and second airborne sources of pressurized gas, that are run on a high-rise part of the flight path at low speed pressure of the incident flow.

EFFECT: increasing the economy of control actuator system.

2 cl, 2 dwg