WO2019004807A1

WO2019004807A1 - Dual-rotation rotor for a cycloidal propeller

Info

Publication number: WO2019004807A1
Application number: PCT/KZ2017/000021
Authority: WO
Inventors: Ергалий ТАСБУЛАТОВ; Ермек АШКЕНОВ
Original assignee: Ергалий ТАСБУЛАТОВ; Ермек АШКЕНОВ
Priority date: 2017-06-27
Filing date: 2017-10-11
Publication date: 2019-01-03

Abstract

The invention relates to designs of rotating-blade cycloidal propulsive elements. A dual-rotation rotor for a cycloidal propeller comprises a primary rotor which rotates about its own axis and is kinematically connected to a drive shaft. Secondary rotors are mounted along the circumference of the primary rotor and are kinematically connected to the drive shaft. On the circumference of each secondary rotor there is one rotating-blade fastening seat, and the secondary rotors are kinematically connected to the drive shaft such that the transmission ratio between the primary rotor and the secondary rotors is equal to minus 1/2. Rotating intermediate shafts are arranged on the axes of the secondary rotors, and the radius of the arrangement of the rotating-blade fastening seats relative to the axis of a secondary rotor is less than the radius of the arrangement of the secondary rotors relative to the axis of the primary rotor. This allows a propeller blade to move along an elliptical path.

Description

DOUBLE ROTATION ROTOR FOR CYCLOID PROPELLER

Technical field

The invention relates to air, water transport and energy (wind and hydropower plants), in particular, to winged propellers - cycloid propellers operating in both air and water environments.

A cycloid propeller consists of blades located along the diameter, rotating around the axis of the rotor, creating directional motion. In order to create a motion, it is necessary to change the angles of inclination of the individual blades using the blade pitch control mechanism. There are three types of cycloid movement, of which two are of the greatest practical interest: movement along a shortened cycloid (curtate) and movement along an elongated cycloid (prolate). When moving along a shortened cycloid (curtate), the blades perform periodic oscillatory movements around their axis, providing high thrust with a low speed of steady movement, which confirms the operating experience of well-known Vojt-Schneider cycloid propellers. When moving along an elongated cycloid (prolate), the blades perform a circular rotation around their own axis, ensuring a high speed of movement. At the same time, the mode of motion along an elongated cycloid (prolate) has a low thrust at the initial velocity of movement, due to the reverse circular motion of the blades on the half of the rotor orbit, relative to the direction of motion.

Taking into account also the fact that the trajectory of the wing ends of birds in flight describes an ellipse in the extended cycloid mode, then the development and implementation of a cycloid propeller, which can operate in the extended cycloid mode and the blades of which move along the ellips trajectory, will provide high traction, increase speed and expand the range of vehicle capabilities of vehicles and devices with a cycloid propeller.

Prior art

From the prior art, a number of winged engines are known - cycloid propellers, in particular, a cycloid propeller (Propeller for Aircraft), patented by Kirsten and Hoover (Kurt FJ KIRSTEN & Herbert M. HEUVER) (US Patent J S2045233, B64C 1 1/00 06/23/1936). The mechanism for changing the pitch of the blades includes an interconnected mechanism for changing the pitch of the cycloid propeller, which creates a movement along a shortened (curtate) curve and represents a crank-to-axle mechanism and a set of planetary and differential mechanisms, the number of which corresponds to the number of blades. This mechanism contains a central gear located in the hub of the rotor, rigidly fixed on the rotor axis, which engages with the satellite gear, which is freely attached to the axis of the angular gearbox containing two bevel gears. The second tier on the axis of the angular gearbox is a differential consisting of bevel gears. On the central shaft, the device for changing the eccentricity and direction of the thrust vector are freely attached to the rocker, on which is located the rocker stone, freely fixed by the third tier on the axis of the angular gearbox. The axis of the angular reducer is connected kinematically through the intermediate shaft to the angular reducer of the shaft of the blade of the cycloid propeller. Rotation of the hub of the rotor leads to rotation of the satellite gears and oscillating movements of the rocker stone, and the differential summarizes the uniform rotation of the satellite and the oscillatory movements of the rocker stone in uneven rotation transmitted through the axis of the angular gearbox to the angular gear shaft of the blade.

The disadvantage of this mechanism is insufficient thrust at low vehicle speeds. It also presents certain difficulties in the implementation of an eccentric device that changes its position relative to the axis of the rotor hub and requiring sufficient space inside the rotor hub

The cycloid propeller (Cycloidal VTOL UAV) is also known (Patent US JY "6932296, VS 64/22, 08/23/2005), patented by Glenn Martin Tierney, which is a planetary mechanism and consists of blades located along the diameter of the hub of the rotor, the shaft of each blade kinematically connected by means of two angular gears and a shaft between them, the outer satellite and parasitic satellite gears with a central gear fixed on the central shaft, which serves as an eccentric. This cycloid propeller, as stated, works in two modes of cycloid motion: due to the rotation of the central gear — in the mode of cropped cycloid (curtate) with the speed of rotation of the rotor hub and the fixed central gear — in the mode of extended cycloid (prolate) . The disadvantage of this mechanism is the impossibility of switching from one mode to another during the rotation of the rotor of the wing propulsion, since the rotor is required to switch modes. In addition, it is doubtful whether it is possible to realize an instantaneous stop or a momentary set of the rotational speed of the central gear to the speed of rotation of the rotor hub. The implementation of an eccentric mechanism, which changes its position relative to the axis of the rotor hub and requires sufficient space inside the rotor hub, presents certain difficulties.

The closest to the claimed technical solution is the Sea propulsion unit with a vertical axis and a transverse position relative to the flow direction, with a constant controlled orientation of the blades (Patent US 6244919, В63Н1 / 10, 2001), which consists of a rotor that creates a rotation around its own the axis of the motor shaft and the device changes the pitch consisting of a pulsed electric motors. There are many blades on the rotor, while on the rotor axis they are coaxial with each other. Spindles with independent kinematic connection with the blades inside the rotor housing and independent rotational connection with the drives of the pitch changing device, outside the rotor housing, are located. The number of spindles and drives corresponds to the number of individual blades.

This mechanism has a significant advantage in regulation in the mode of movement along an extended (prolate) cycloid, but the disadvantage of this mechanism is insufficient thrust with a low speed of the vehicle.

DISCLOSURE OF INVENTION

The task to be solved by the claimed invention is the creation of a double rotation rotor for a cycloid propeller, which ensures the motion of the blade along the trajectory of the ellipse.

The technical result consists in the development and creation of a double-rotor rotor for a cycloid propeller, which ensures the motion of the blade along the trajectory of the ellipse.

This technical result in the proposed double-rotor rotor for a cycloid propeller containing a main rotor rotating around its own axis and having a kinematic connection with the drive shaft, according to the invention, rotating secondary rotors located along the circumference of the main rotor are additionally introduced located in one place for fastening the blades rotating on their axes, the secondary rotors have a kinematic connection with the drive shaft, providing General transferred datochnoe ratio secondary to the main rotor equal minus 1/2 except that on the minor axes of the rotors are arranged rotating countershafts, and the radius of locations for attachment of the blades relative to the secondary axis of the rotor smaller than the radius location of the minor axes of the rotors with respect to the axis of the main rotor.

The kinematic connection of the secondary rotors with the drive shaft is performed through gears, namely, on the The central gear fixed on the main rotor axis is rigidly fixed, which meshes with the gears mounted on the hubs of the secondary rotors through parasitic gears.

On both sides of the hub of the secondary rotors on the intermediate shafts are rigidly fixed on one gear.

The central shaft on the drive side of the main rotor hub is rigidly fixed to the worm drive with a servo drive control vector thrust.

The introduction of minor rotors into the rotor of the cycloid propeller led to the possibility of the motion of the blades along the path of the ellipse.

Consider as an example the use of a double-rotor rotor in a two-blade cycloid propeller, which creates movement of the blades along an ellipse trajectory in the extended cycloid mode (prolate), with an external arrangement of the pitch change device relative to the rotor.

Brief Description of the Drawings

For a better understanding, the essence of the proposed technical solution is explained with the involvement of graphic materials, where figure 1 shows the kinematic diagram of a two-blade cycloid propeller with a rotor of double rotation. Figure 2- shows a pattern of moving the blades of a cycloid propeller with a rotor of double rotation, creating movement of the blades along the path of the ellipse in the extended cycloid mode (prolate).

The best embodiment of the invention

A cycloid propeller with a rotor of double rotation, the blades of which move along the trajectory of the ellipse in the extended (prolate) cycloid mode (Fig. 1) consists of the main rotor 1, including secondary rotors 2, devices for changing the pitch 3 of the blades and the blades themselves 4, located on the circumference of the secondary rotors.

The secondary rotors 2 are located along the radius of the main rotor 1 and have the possibility of rotation. Each minor rotor 2 contains one blade 4. On the shaft 5 of the blade the gear wheel 6 is rigidly fixed, ^The second is connected via a toothed belt 7 to a gear wheel 8, which is rigidly fixed to the intermediate shaft 9 of the secondary rotor 2.

On the central shaft 10 of the main rotor 1, the central gear 11 is fixed, which meshes with the gears 12 fixed on the hubs of the secondary rotors 2 via parasitic gears 13.

The spindles 14 are located coaxially with each other on the axis of the main rotor 1. The spindles 14 are separated from each other, by the central shaft 10 and the hub of the rotor 1 by bearings, the gears 15 are rigidly fixed on the spindles 14, the gears are also rigidly fixed on the intermediate shafts 9 These wheels 16 are connected to the spindles 14 via gear belts 17. Outside the main rotor housing 1 on the spindles, the gear wheels 18 which are in engagement with the gear wheels 19 of the pitch change device 3, are fixed on the shafts 20 of the drives by gears. straps 21. The number of spindles 14 and shafts of 20 drives corresponds to the number of individual blades 4. The device for changing the pitch of the blades of the cycloid propeller 3, consisting of impulse electric motors, is fixed on the frame.

All belt drives can be replaced with chain, gear or crank drives.

The central shaft 10 on the drive side of the main rotor hub 1 is rigidly fixed to the worm drive with a servo drive 22 for controlling the thrust vector. The hub of the main rotor 1 has a kinematic connection from the drive shaft of the engine 23 through gears 24 and 25.

A cycloid propeller with a rotor of double rotation, ensures the motion of the blade along the path of the ellipse in the extended cycloid mode (prolate) as follows.

Rotation of the main rotor 1 counterclockwise from the drive shaft of the engine 23 causes the rotation of the secondary rotors 2 through a gear connection with the central gear 11, parasitic gear 13, and gear 12 with a total gear ratio K = -1/2. those. During one revolution of the main rotor 1, the secondary rotor 2 makes two revolutions clockwise around its axis, in the direction opposite to the rotation of the main rotor 1, which ensures the movement of the blades 4 along the ellipse's trajectory (Fig. 2). The geometrical parameters of an ellipse are determined by the ratio of the radii of the main 1 and secondary rotors 2, while the rotation radius of the blades 4 relative to the axis of the secondary rotor 2 is smaller than the radius of rotation of the secondary rotors 2 relative to the axis of the main rotor 1.

The oscillatory movements of the shafts 20 of the device for changing step 3, consisting of software-controlled impulse electric motors, are transmitted to the shaft 5 of the blade 4 via a belt drive 21, spindles 14, a belt drive 17, an intermediate shaft 9 of the secondary rotor 3 and a belt drive 7

Changing the direction of the thrust vector performs a change in step 3 device as well as a servo 22 by turning the central shaft 10 inside the axis of the main rotor 1, while the servo 22 performs a simultaneous rotation of only 1/2 the angle of rotation of the change in thrust vector 3 .

The joint rotation of the main rotor 1 and the secondary rotors 2 from the drive shaft of the engine 23, as well as the blades 4 from the change device of step 3, ensures the movement of the blades 4 of the cycloid propeller in the extended cycloid mode (prolate) along the ellipse trajectory (Fig. 2).

The location of the pitch changing device is not limited only to its external position relative to the main rotor. It can also be mounted inside the main rotor, it is also possible to completely mechanically execute the device for changing the pitch, including creating the movement of the blades along the shortened cycloid (curtate).

Industrial Applicability

The well-known Voith Schneider movers used on ships have good traction and maneuverability, but are limited in speed. movement have a mode of movement on a shortened cycloid (curtate). The use of the double-rotor rotor for the cycloid propeller, which can operate in the extended cycloid mode, and the blades of which move along the ellipse trajectory, in water transport will provide high traction, increase the speed of movement and expand the range of vehicle capabilities and devices with a cycloid propeller.

It is also possible to use the proposed double-rotor rotor for the cycloid propeller with the horizontal axis of the rotors in the aft hull of the marine vessel.

It is also possible to use the dual rotation rotor proposed in the present invention for a cycloid propeller on an air transport, in particular, on a cyclocopter. In case of engine failure during an emergency landing, the autorotation mode is provided.

In addition, it is possible to use a cycloid propeller with a dual-rotation rotor for a cycloid propeller in modern aircraft that is lighter than air, including on airships, which allows for improved maneuverability and stabilization of airships, thanks to the possibility of cycling propeller almost instantly change the direction of thrust.

The rotor of double rotation for a cycloid propeller proposed in the present invention can be used in wind and hydropower as a generator drive. Unlike the Darier rotor, the cycloid propeller provides for the rotor to start rotating at the minimum speed of air or water flow. A cycloid propeller with a double-rotor rotor also allows for more operational orientation towards the wind than other wind generator systems, such as horizontal-axial installations.

Claims

F O R M U L A

1. A double-rotor rotor for a cycloid propeller containing a main rotor rotating around its own axis and having a kinematic connection with the drive shaft, which has been added around the circumference of the main rotor rotor rotating secondary rotors, on the circumferences of which there is one place for fastening the blades turning on their axes, while the secondary rotors have a kinematic connection with the drive shaft, providing a total gear ratio of the main rotor o- ra equal to secondary minus 1/2 except that on the minor axes of the rotors are arranged rotating countershafts, and the radius of locations for attachment of the blades relative to the secondary axis of the rotor smaller than the radius location of the minor axes of the rotors with respect to the axis of the main rotor.

2. Double rotor for a cycloid propeller, according to claim 1, that the kinematic connection of the secondary rotors with the drive shaft is performed through gears, namely, on the axis The main rotor of the central shaft is rigidly fixed to the central gear, which engages with the gears mounted on the hubs of the secondary rotors through parasitic gears.

3. The rotor of double rotation for a cycloid propeller, according to claim 1, which means that on both sides of the hubs of the secondary rotors on the intermediate shafts are rigidly fixed on one toothed wheel.

4. Double rotor for a cycloid propeller, according to claim 1, that the central shaft from the drive side of the main rotor hub is rigidly fixed on the worm drive with a servo drive control thrust vector.