FIELD: aviation.
SUBSTANCE: invention relates to aircraft engineering, particularly, to control structures of multi-screw aircrafts of quadcopter type. Aircraft flight control system consists of take-off and landing control system, left-right movement, forward-backward, stop and parking system control systems, aircraft safety system. Electrohydraulic system includes hydraulic pumps, flight control unit, hydraulic motors, hydraulic system operation control units, bypass valves of hydraulics system, electromechanical hydraulic distributor controlling gear shifting of lifting hydromechanical gearboxes, unit of adjustable bypass valves that control operation of hydraulic motors and unit of pressure stabilization.
EFFECT: higher reliability of aircraft in operation and safety of flights.
1 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIRCRAFT | 2018 |
|
RU2699452C1 |
| AIRCRAFT | 2018 |
|
RU2699591C1 |
| ADJUSTABLE BY-PASS VALVE BLOCK | 2021 |
|
RU2753012C1 |
| POWER TAKEOFF BOX | 2018 |
|
RU2708117C1 |
| HYDROMECHANICAL GEARBOX | 2018 |
|
RU2696901C1 |
| FLYING MOTOR CAR | 2007 |
|
RU2344946C2 |
| RECONNAISSANCE UNMANNED AERIAL VEHICLE | 2023 |
|
RU2806574C1 |
| MULTI-COPTER WITH AIR SCREWS OF VARIOUS PURPOSE | 2016 |
|
RU2718460C1 |
| PERSONAL AIRCRAFT | 2010 |
|
RU2422328C1 |
| SELF-CONTAINED HYDRAULIC SERVO UNIT | 1986 |
|
SU1839994A1 |
