EG - helicopter pilot production Yakovlev. Experimental option that had coaxial blades. In designing participated workers OKB Kamov. Flight tests were conducted with a helicopter on the 1947 1948, the
Chief designer of the helicopter became SA Bemowo, his deputy - IA Ehrlich. Through the development of the helicopter, OKB Yakovlev and TsAGI specialists visited the company "Brig", where they got acquainted with the pre-war machine Dorand, which had a coaxial screws.
Program for the construction of EG stopped due to some technical problems and the emergence of a more successful version of a light helicopter Mi-1.
Helicopter EG has a coaxial screw placement and is equipped with an engine M-11FR-1, 140 whose power hp The fuselage is divided into three parts. The front of the cockpit takes, petrol and oil tank, reducer. In the middle part of the engine is placed. The tail portion acts as a stabilizer. Frameworks for the middle and front parts are presented hromansilevymi welded pipes. The front of the fuselage with wooden decking, linen lining and a removable bow cook duralumin, which was fixed with locks zushi.
In the middle of the cage closed easily removable panels. They play the role of the engine compartment hoods. The mobile docking of the front and middle parts of the fuselage on the four bolts made specifically to compensate for the different vibration frequencies. The tail section of the helicopter EH made of duralumin profiles angled and fitted a canvas.
In the first instance of the EG applied four wooden tail washers are composed of a set of ribs and spar. Sock washers trimmed with plywood, the other part - cloth. Lock washers performed by the rear bulkhead of the fuselage, which was connected with a fairing. The material, which was glazed cockpit - plexiglass. The cabin had two doors. Paul is equipped with a window for the inspection area during the landing.
Rotors helicopter pilot engines Yakovlev rotate in opposite directions. The composition of each rotor were two wooden blades, which are attached to the structure with metal sleeves. This allowed the blades to rotate in perpendicular planes.
In addition, the blades can be folded on a "tulip", change the angle of attack and make turns around the vertical axis. Each sleeve has a friction braking device which absorb the inertial forces change blades during rotation of the rotor speed. The lower and upper rotors are composed of a special safety device which makes it impossible to strike the blades together.
The structure consists of a skeleton blade spar, a rim and a set of ribs. The spar, which forms the sock is made of oak slats. For the toe of the blade is placed plywood sheathing. Wood blades paste cloth. The butt is duralumin butt-coupling, which can be divided into two halves. The torque transmitted from the engine to the gearbox horizontal shaft through two cardan joints.
The gearbox includes two coaxial vertical shaft, a set of cylindrical and bevel gears, hydraulic clutch and spin the rotors driven roller freewheel. The latter transmits the torque from the engine to the rotor in autorotation and perform decoupling the engine and the gearbox.
For inclusion freewheel responsible hydraulic system. Gearbox oil system is independent of the engine lubricating system.
The control mechanism is cyclical and general rotors step includes upper and lower wheels. The composition of each of the two yoke rings with double ball bearing, and the center ring slide. The slides discs are splined connection. Lower the slider was connected to the gear unit, the top - from the top of the rotor shaft. This allows the control mechanism wrapped around the perpendicular and longitudinal planes, lowered and raised.
In order to eliminate the backlog of the lower disc from the top, they are interconnected by a slot-joints. During the movement of the helicopter left, right, forward, backward posted aircraft type lever. The rotation around the vertical axis is controlled by the pedals, the redistribution of torque. Motion control up and down is done at the expense of the collective handle, which was placed on the left of the pilot.
The control system of collective pitch is operated hydraulic cylinder, which automatically shift paddles on a small step in autorotation. The inner part of the cylinder takes a spring, which is compressed by the pressure oil supplied from the additional pump. If you stop the engine, oil will cease to flow and the overall pitch of the rotors is reduced.
The structure of the control wiring includes a set of rigid braces and rods. Hydraulic dampers are also used. There was a helicopter tricycle fixed landing gear, which had an oil-pneumatic cushioning. The main wheels have a size 400h150 mm front wheel - 250h80 mm. Fixing landing gear is made by tubular trusses. The front landing gear lever is mounted to the suspension and the first fuselage frame.
In the middle part of the fuselage housed the engine M-11FR-1, which has a nominal capacity of 140 hp is mounted to the engine frame and the air cooling of 8-bladed fan, which was mounted on the motor shaft.
The gas tank was fixed gear under the fuselage on the farm. Filler neck was placed at the left side. Oil tank located behind the rear cab wall.
Yakovlev EG characteristics:
|The diameter of the rotor, m||10.00|
|engine's type||1 PD M-11FR-1|
|takeoff||X 1 160|
|Rated||X 1 140|
|Maximum speed km / h||150|
|Practical range, km||235|
|Rate of climb, m / min||66|
|Dynamic ceiling, m||2700|
|Static ceiling, m||250|
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