Gyroplane with vertical take-off and vertical landing

FIELD: transport.

SUBSTANCE: invention relates to aircraft, in particular to vertical take-off and landing aircraft. Gyroplane includes fuselage (1) with flight deck with folding pillar (2) installed on it, rotor head (3) with adjustable torsion bushing (16) and pusher screw (5) with adjustable pitch. In the rotor head (3) for even load distribution on torsion bushing (16) during preliminary spinup of rotor (4), torsion is made of flat composite plates without curve. Surface of tilting hinge (15) mounting of torsion bushing (16) is turned for angle not exceeding 40 degrees to longitudinal axis of bushing (16) torsion of rotor (4). Rotor (3) head is attached to pillar via frame hinge (9) with shifted forward trunnion (10). Pushing screw (5) has adjustable torsion bushing gathered of composite plates. All connections of rotor head tilt control rods and hinge joint of rotor spin-up shafts are positioned on axis of stand rotation.

EFFECT: lower vibration and load on control lever.

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The invention relates to an aircraft, in particular for the construction and operation of autogyros.

There are many autogyros, built for the last time. Famous gyro described in applications WO 1997/008050 (IPC⁸B64C 27/02, publ. 06.03.1997), WO 1998/030446 (IPC⁸B64C 11/06, as of 16.07.1998 entitled). The principle of pitch change of the rotor and pusher propeller data structures of the autogyro is the manufacture of special hollow blades, inside of which are long torsions. The autogyro described in these applications, allows for a vertical takeoff and vertical landing due to the pitch change of the rotor. Blade pusher propeller with variable pitch made on the same principle as the rotor blades.

The downside of it is the special labor-intensive manufacturing technology blades and torsions, which does not allow you to use the classic technique of manufacture of the blades in aviation.

The closest technical solution to the claimed is the autogyro in patent RU 2313473 C1 (IPC B64C 27/02, publ. 27.12.2007), which uses a rotor head with controllable pitch with torsion bushing. The disadvantage of this design is that the swinging hinge has preservance faces at an angle of 2-3° to the plane, resulting in steklotekstolity torsion bar fixed to the tilting hinge is the angle of 4-6°. When has preliminarily the th promotion of the rotor due to centrifugal forces, there is a reduction of the angle to 0, thus the top steklotekstolite plate torsion experience additional load on the gap, and the bottom is compressed, which is a disadvantage of this design and can lead to the destruction of the torsion in the promotion of the rotor.

To reduce the load on the handle controlling the gyro in flight, the framework hinge is made symmetrical, and the head fixed fairing role discharging air compensator. This design does not effectively solve the problem of unloading efforts on the handle when the control gyro in flight.

Thus, there is a need for the development of the autogyro with more advanced nodes, reliable in flight, manageable and convenient storage.

The basis of the claimed invention is the task of creating a gyroplane with a variable pitch rotor for the implementation of vertical take-off and vertical landing, reliable and secure, easily managed in flight.

The problem is solved using an autogyro with vertical takeoff and vertical landing, including the fuselage, mounted on a pylon with a cylinder, a rotor fixed to the pylon through the frame hinge and having a torsion sleeve, consisting of a swinging hinge and torsion recruited from composite plates, power unit with a pusher propeller controllable pitch placed behind the cockpit, tail vertical tail with rudder, tricycle landing gear.

Torsion rotor hub recruited from a flat composite plates without bending at the ends of the torsion installed rotor blades, the plane of the mounting of the tilting hinge torsion rotor hub is deployed at an angle of not more than 40° relative to the longitudinal axis of the torsion or the plane of the mounting of the tilting hinge torsion sleeve of the rotor coincides with the longitudinal axis of the torsion bar, a cylinder, a rotor fixed to the pylon through the frame hinge with offset forward of the axis of rolling.

Preferably the plane of the mounting of the tilting hinge torsion rotor hub is deployed relative to the longitudinal axis of the torsion angle of 30°.

Preferably the pusher propeller with adjustable pitch has an adjustable torsion bar bushing, recruited from the composite plates mounted on the hub, at the ends of the torsion sleeve fixed blades.

Preferably the blades are cut along the contour Coca.

It is preferable to fold the pole in a horizontal position all the connection rod control tilt head rotor swivel gook shafts spin rotor drive is located on the axis of rotation of the front pylon.

The problem is solved also by using head rotor for gyro attached to the pylon through the framework of the joint, including Orsino sleeve, consisting of a swinging hinge and torsion recruited from composite plates.

Torsion rotor hub recruited from a flat composite plates without bending plane of the mounting of the tilting hinge torsion rotor hub is deployed at an angle of not more than 40° relative to the longitudinal axis of the torsion or the plane of the mounting of the tilting hinge torsion sleeve of the rotor coincides with the longitudinal axis of the torsion bar, a cylinder, a rotor fixed to the pylon through the frame hinge with offset forward of the axis of rolling.

Preferably the plane of the mounting of the tilting hinge torsion rotor hub is deployed relative to the longitudinal axis of the torsion angle of 30°.

Head rotor for uniform distribution of the load on the torsion sleeve of the rotor, when the pre-promotion of the rotor, the torsion bar is made from a flat composite plates without bending.

To reduce vibration on the control stick in flight, the plane of the mounting of the tilting hinge torsion rotor hub is deployed at an angle of not more than 40° to the longitudinal axis of the torsion bar.

In another variant implementation of the autogyro, the plane of the mounting of the tilting hinge torsion sleeve of the rotor coincides with the longitudinal axis of the torsion bar.

To reduce the load on the handle when the control gyro in flight pitch, rotor head is attached to the pylon through the frame hinge someseni forward axis of rolling.

For convenience of storage and transportation of the autogyro removed the blades of the rotor, the pole is folded into a horizontal position by means of electrohydroblock without further disassembly. All swivel rod of the control cylinder, rotor, and swivel gook shafts spin rotor drive is located on the axis of rotation of the front pylon.

The proposed rotor head can be used in autogyros other structures.

It is preferable to install in-flight favorable mode of the engine, pusher propeller is made with adjustable pitch. For this purpose, the hollow flange of the gearbox, which passes through a control push-rod, installed hollow hub on which is mounted a torsion bushing, recruited from the composite plates. The whole mechanism with a variable pitch closed COCOM large diameter. At the ends of the sleeve fixed trapezoidal blade, cut along the contour Coca. This design of a propeller with adjustable pitch can be applied both in pushing and tandem version and can be used on any aircraft.

The technical result of the proposed solutions is the creation of the autogyro, which is safe, reliable and compact aircraft with vertical takeoff and vertical landing.

The following is about the Institute of the possible variants of the autogyro with vertical takeoff and vertical landing.

Figure 1 presents a General view of the declared autogyro.

Figure 2 shows the layout of the control mechanisms autogyro.

Figure 3 shows the detail of the head of the rotor with a variable pitch.

Figure 4 shows the detail pusher propeller with adjustable pitch.

The gyro consists of a fuselage 1 (1), hours of pylon 2, head rotor 3, the rotor 4, the clamping screw 5, tail unit 6, a three-wheeled chassis 7.

Rotor head 3 (figure 2) includes a housing bearing 8, which is attached to the front of the pylon 2, in the framework of the hinge 9, having shifted forward axis of the roller 10 (Fig 3).

In the bearing housing 8 is inserted hollow shaft hub 11 on the hub 11, mounted rigidly or through overrunning clutch gear 12 depending on the design of the drive.

The actuator 13 promotion of the rotor 4 is mounted on the plate 14.

The bearing housing 8 hub mounted on the plate 14.

On the shaft of the hub 11 has a swinging hinge 15, which is fixed to the torsion bar, recruited from direct composite plates.

The plane of the mounting of the tilting hinge 15 torsion sleeve 16 of the rotor 4 with the shaft hub 11 is deployed at an angle of not more than 40° relative to the longitudinal axis of the torsion or the plane of the mounting of the tilting hinge 15 torsion sleeve 16 of the rotor 4 with the shaft hub 11 coincides with the longitudinal axis of torsion (Fig 3).

In a hollow hub 11 of the TSA who updates the shaft 17, installed the rocker 18. Swinging hinge 15 and the rocker shaft 17 fixed to the hub 11 by the axis.

The ends of the rocker arm 18 thrust through 19 are connected with the levers 20 torsion bushing 16.

Rotor blades are attached to the torsion sleeve 16 through the plate 21. The rocker shaft 18 is connected with a pull of the step 22 through bearing hinge 23.

Pitch control of the blades of the rotor 4

From the control knob 24 (step on the gas thrust through 22 through bearing hinge 23, the shaft 17, the force is transmitted to the rocker arm 18 and through the thrust 19 acts on the torsion sleeve 16, recruited from direct composite plates, thereby changing the pitch of the rotor blades.

Control the angle of attack of the rotor blades 4

From the handle control autogyro 25 thrust through 26, mounted on a swinging lever 27, the force is transferred to the plate 14 fixed on the housing of the bearing 8, the shaft of the hub 11, the swinging hinge 15 with torsion bushing 16. Thus, changing the angle of attack of the rotor 4 in pitch and roll.

Pre-promotion of the rotor 4

From pulley 28 attached to the shaft of the gear motor 29 through a belt drive 30 with the idler pulley, the torque is transmitted to the angular gear 31.

From the angular gear 31 through the double hinge gook 32 and slot connection 33 torque is transmitted to the actuator 13 promotion of the rotor 4.

Turn at pylon 2 in g the horizontal position

All connection rod control head 26 of the rotor 3 and swivel gook 32 drive shaft to spin the rotor 4 is located on the axis of rotation 34 of the rack of the pylon 2. This allows removing the blades of the rotor 4 with electrohydroblock 35 to rotate the pole in a horizontal position without additional disassembly.

Pusher propeller with adjustable pitch 5

Pusher propeller with adjustable pitch 5 consists of a hollow hub 36 through which passes the shaft of the rocker arm 45, a locking pin (Figure 4).

On the hub 36 is installed torsion bushing 38, recruited from direct composite plates.

At the ends of the torsion sleeve 38 through the bracket 39 fixed blade 40 and the control levers of the step 41. The whole mechanism is closed COCOM 48 large diameter.

The force from the actuator 42 through a lever 43, through bearing hinge 44 is transmitted to the shaft 45 and arm 46. From the rocker arm 46, thrust through 47, the force is transmitted to the levers 41 and torsion bushing 38 of the feeding screw 5. Thus, changes the pitch of the blades 40 of the feeding screw 5.

The autogyro is as follows.

Start the engine 29. Handle control step-GAZ 24 of the rotor blades 4 are output at zero angle of attack, and then using a belt drive 30 with the idler pulley is the promotion of the rotor 4 to speed 1.5 times the flight, the car is Il is held on the brakes. Control system the overall pitch of the rotor blades 4 provides three fixed positions on the handle step-gas at the mounting angle of the rotor blade: with zero angle of attack, the installation (flight and landing.

After reaching the rotor 4 turns 450-500 rpm, stops the spinning of the rotor 4. Handle step-GAZ 24 angle of attack of the blades of the rotor 4 is displayed on the flight and added gas. As a result, the load of the rotor 4.

The autogyro takes off vertically and begins forward motion, and the speed of the rotor 4 fall before the flight, and the rotor 4 rotates from air flow. In the future, the autogyro is controlled by the aircraft. Before planting autogyro cleaned gas and the autogyro, hover over the landing pad, starts to fall (parachutiste). 1-2 m above the ground, depending on the mass of the rotor blades 4, the control knob step-GAZ 24 angle of attack of the rotor blades is increased, i.e. converted into the seat angle. The speed of parachuting gyroplane is significantly reduced and is a soft landing.

On the autogyro installed pusher propeller 5 with adjustable pitch. When performing the route of flight or flight at higher speeds, by means of the actuator 42, is the increase of the angle of attack of the blades 40 of the feeding screw 5 mounted on the ends of the torsion sleeve 38. While the us favorable mode of operation of the engine.

For easy storage of the autogyro and transportation in the trailer, you can take the rotor blades 4 and using electrohydroblock 35 to lower the pole in a horizontal position without any additional disassembly.

Above the autogyro is the best embodiment of the invention shown in figure 1, figure 2, figure 3, Figure 4.

The autogyro in accordance with this embodiment of the invention includes a fuselage, with the installed folding pylon, head rotor, having adjustable torsion bushing, and a pusher propeller with adjustable pitch.

For uniform distribution of the load on the torsion sleeve 16 of the rotor 4, in the pre-promotion of the rotor 4, the torsion bar is made from a flat composite plates without bending.

To reduce vibration on the control stick in flight, the plane of the mounting of the tilting hinge 15 torsion sleeve 16 of the rotor 4 with the shaft hub 11 is deployed at an angle of about 30° relative to the longitudinal axis of torsion (Fig 3).

To reduce the load on the control stick the gyro in flight, the axis 10 of the framework of the hinge 9 is moved forward.

For easy storage and transportation in the trailer, the pylon is made folding.

To select a favorable mode of the engine in flight, the clamping screw 5 (Figure 4) are made adjustable step.

The invention is used for the manufacture of the screw is rylah aircraft, in particular autogyros with vertical takeoff and vertical landing.

Rotor head can be used in autogyros other structures.

1. The autogyro with vertical takeoff and vertical landing, including the fuselage, mounted on a pylon with a cylinder, a rotor fixed to the pylon through the frame hinge and having a torsion sleeve, consisting of a swinging hinge and torsion recruited from composite plates, power unit with a pusher propeller controllable pitch, placed behind the cockpit, tail vertical tail with rudder, tricycle landing gear, characterized in that the torsion of the rotor hub recruited from a flat composite plates without bending at the ends of the torsion installed rotor blades, the plane of the mounting of the tilting hinge torsion rotor hub is deployed at an angle of not more than 40° relative to the longitudinal axis of the torsion or the plane of the mounting of the tilting hinge torsion sleeve of the rotor coincides with the longitudinal axis of the torsion bar, a cylinder, a rotor fixed to the pylon through the frame hinge with offset forward of the axis of rolling.

2. The gyro according to claim 1, characterized in that the plane of the mounting of the tilting hinge torsion rotor hub is deployed relative to the longitudinal axis of the torsion angle of 30°.

3. The gyro according to claim 1, characterized in that the clamping screw with Regulus in the alignment step has an adjustable torsion bar bushing, recruited from composite plates mounted on the hub, at the ends of the torsion sleeve fixed blades.

4. The autogyro according to claim 3, characterized in that the blades are cut along the contour Coca.

5. The autogyro according to any one of claims 1 to 4, characterized in that the folding pole in a horizontal position all the connection rod control tilt head rotor, swivel gook shafts spin rotor drive is located on the axis of rotation of the front pylon.

6. Head rotor for gyro attached to the pylon through the frame hinge comprising a torsion sleeve, consisting of a swinging hinge and torsion recruited from composite plates, characterized in that the torsion of the rotor hub recruited from a flat composite plates without bending plane of the mounting of the tilting hinge torsion rotor hub is deployed at an angle of not more than 40° relative to the longitudinal axis of the torsion or the plane of the mounting of the tilting hinge torsion sleeve of the rotor coincides with the longitudinal axis of the torsion bar, a cylinder, a rotor fixed to the pylon through the frame hinge with offset forward of the axis of rolling.

7. Rotor head according to claim 6, characterized in that the plane of the mounting of the tilting hinge torsion rotor hub is deployed relative to the longitudinal axis of the torsion angle of 30°.