WO2018190670A1

WO2018190670A1 - Blade tip rotary vane

Info

Publication number: WO2018190670A1
Application number: PCT/KR2018/004335
Authority: WO
Inventors: 오성
Original assignee: 오성
Priority date: 2017-04-13
Filing date: 2018-04-13
Publication date: 2018-10-18

Abstract

The present invention relates to a blade tip rotary vane which, unlike an existing propeller, is formed by attaching a vane to a blade tip portion at which the rotational speed of the vane is fast, wherein the blade tip rotary vane is characterized in that: the rotational friction of the vanes (102) formed at blade rods (104) around a blade rod hub part (106) is reduced, and the outer surface of the vane (102) is fitted to an outer rotational surface arc in order to prevent the fluttering or vibration of the vanes; the inner surface of the vane (102) is fitted to an inner rotational surface arc; and the outer arc angle and the inner arc angle are the same with respect to the center of a rotary shaft.

Description

Feather Rotating Wings

The present invention is a rotor blade attached to the blade tip portion (blade tip) fast rotation speed of the blade, unlike the existing propeller, reducing the rotational loss of drag or rotation wind damage of the entire propeller, the rapid rotation speed of the propeller blade To get more powerful thrust.

In addition, the present invention prevents flutter or vibration caused by excessive feather tip speed caused by the existing propeller, etc. through the device for fixing the respective wings, and to increase the rotational inertia of the rotary blade to smoothly rotate, in the wing It prevents the airflow from scattering and creates a more stable and powerful thrust.

The present invention is attached to the rotor blade of the outer rotor to the outer rotor rotor of the outer rotor to increase the radius of rotation and increase the rotational inertia to create a more powerful thrust.

In another aspect, the present invention is to form a multi-stage propeller propulsion body, which is a more powerful propellant of the electric motor age by forming the feather blades in two or more stages and different rotation speed and direction of rotation.

In the present invention, since some electric vehicles currently being used are driven by directly rotating the rotary shaft of the wheels (with the weight of the main body of each vehicle) driven by the motor, the rotation radius of the turning force is extremely small, and the driving force of the motor is greatly increased. For example, various transportation engines, such as an electric vehicle running with the propeller of the present invention, are driven by propellers to propel various vehicles, trains, ships, and the like, so that a torque that rotates wheels is increased, thereby driving fewer motors. It is related to the blade rotor blade that can make a stronger thrust even by the power of the propulsion engines of various vehicles, trains, ships and the like to drive.

The background technology of the present invention is the same as the basic principle that the existing propellers make thrust through rotation, and supplements the problems of the existing propellers by using the law of the rigid body (wing) and the rotational inertia, and more It is designed to get strong thrust with smooth rotation.

The speed of the rotor blades is given by v = rω. Where r is the radius of rotation of the blade and ω is the angular velocity. In other words, the speed of the rotor blades is proportional to the radius of rotation and the angular velocity (ω = 2πn: n per second) of each wing. Therefore, the present invention is to attach the blade to the propeller tip (Blade tip) with a large radius of rotation, as shown in Figure 1 in order to quickly produce the necessary lift and thrust. Therefore, the present invention can reduce the rotation loss and obtain a more powerful thrust than the existing propeller gains thrust through the entire wing.

In addition, the present invention is to prevent the flutter and vibration caused by the excessive propeller speed of the existing propeller, and to increase the rotational inertia of the rotor blades to install the device to fix the blades to make the rotation smoothly well, This device prevents the airflow that is generated during the rotation of the blades, creating a more stable and stronger thrust.

As for the rotational inertia of the body (wing), the rotational kinetic energy of the body

Given by Here, the quantity defined by I = Mr ² is the rotational inertia. In other words, the rotational inertia of a body is proportional to the square of the weight of the body (M) and the radius of rotation of the body (r). The rotational inertia is a physical quantity that acts as a mass of a rotating body. The larger the rotational inertia is, the better it works according to Newton's law of inertia.

In this way, the rotational inertia of the rigid body, the larger the weight of the rigid body and the larger the radius of rotation, the greater the rotational inertia, so that the good rotation of the present invention attaches the blade to the blade tip portion of the large radius of rotation to increase the rotational inertia, By installing a device to fix the wing to prevent flutter (fluttering) or vibration generated in the existing propellers, such as to ensure that the rotation of the rotary blade is made smoothly.

What we can easily pull out of carts, strollers, wheelchairs, etc. is by using the torque of the rotation of the wheels. The physical theory of this is as follows.

"Torque is a physical quantity that corresponds to a force in a rotational motion. For example, even if you give the same force when you open the door, the door may be easier or more difficult to open depending on how far it is from the axis of rotation of the door. Therefore, the rotation radius is somehow involved in the turning force.

Actually turning

(Tau in Greek) is defined as

to be. here

Is power

Is the position vector of the point where the force acts. These two vectors are multiplied by the vector product

Define. The magnitude of the vector product is proportional to the sine of the angle between the two vectors. soon,

to be. Is the angle between the two vectors.

Therefore, if the two vectors are parallel (i.e. the angle is 0 degrees or 180 degrees), the torque is zero. This is consistent with our intuition. If the door is pulled outward or pushed inward, the door will not turn. Also, for maximum torque, the position vector to the point of action and the force must be perpendicular to each other. This is also a very consistent phenomenon with our intuition.

Torsional force is a physical quantity that acts as a force in rotational motion.

The equation of rotational motion corresponding to τ = Iα. Where I is the rotational inertia, which corresponds to the mass of the rotational motion, and α is the angular acceleration.

Next, let's look at the rotation of the wheel,

As shown above, if the wheel does not slip and keeps touching the ground and rolls to the right, the wheel is rotated around the point O where it touches the ground. Therefore, if the radius of the wheel is r and the mass of the wheel is M, then I = I _com + Mr ² by parallel axis theorem.

The result is a formula for the rotational kinetic energy of a rigid body.

Put it in

… (1) is obtained. Here, the relationship of ν _com = rω was used. This relationship holds true even when the wheel rolls as a basic relation of rotational motion.

Looking at the equation (1), it can be seen that the kinetic energy of the rolling wheel is composed of two. The first term in equation (1) is the rotational kinetic energy when the wheel rotates about its axis through the center of mass. And the second term is the kinetic energy when the center of mass moves at the speed υ _com . Therefore, the rolling wheel is the sum of the rotational kinetic energy rotating in the axis passing through the center of mass and the energy of the center of mass moving in a straight line.

Based on the above theory, we want to compare the difference between pulling a wheelbarrow, a stroller, a wheelchair, etc., and rotating a wheel by rotating a wheel of a motor.

Since dragging a wheelbarrow or a stroller is a rotation of the wheel around the point O, the pulling force of the cart acts at the center of the wheel (rotation axis), so that the radius of rotation of the wheel's turning force is equal to the radius of the wheel. It acts as a large torque in proportion to the size of the wheel. On the contrary, since the motor rotates the wheels by rotating the wheels, the motor rotates the wheels in a state in which there is almost no radius of rotation. do. Therefore, in order to rotate the wheels with a motor, the driving force of a larger motor is required.

Similarly, running a car with a propeller allows the wheel to run with less propeller driving force because the radius of the wheel acts as a turning radius of the turning force, such as pulling a wheelbarrow or a wheelchair. To run a car with a propeller is to run the wheels with much less force than the force that directly drives the wheels of the wheels with a motor.

The present invention, unlike the propeller of the existing aircraft such as drones, helicopters, aircraft to reduce the rotational loss, such as drag or rotation wind loss of the entire propeller, to obtain a more powerful thrust by obtaining a fast rotational speed of the propeller.

In addition, the present invention prevents flutter or vibration caused by excessive blade tip speed caused by the existing propeller, and to increase the rotational inertia of the rotary blades to facilitate the rotation smoothly, the dispersion of air flow generated from the blade during rotation It is to prevent it and to make more stable and strong thrust

The central assembly of the rotating shaft of the present invention is to install a magnetic bearing or the like to reduce the mechanical rotational friction generated when the rotary blade is rotated to take off or propel the vehicle vertically.

In the present invention, since some electric vehicles currently being used are driven by directly rotating the rotary shaft of the wheels (with the weight of the main body of each vehicle) driven by the motor, the rotation radius of the turning force is extremely small, and the driving force of the motor is greatly increased. For example, various transportation engines, such as an electric vehicle running with the propeller of the present invention, are driven by propellers to propel various vehicles, trains, ships, and the like, so that a torque that rotates wheels is increased, thereby driving fewer motors. It will also make the thrust more powerful with the power of, to increase the energy efficiency and performance of various transportation agencies.

In addition, the propeller used in the present invention should be used in various vehicles, trains, ships, etc., and should be a suitable size to fit the size of each product. To provide a rotor blade.

In addition, the present invention is to provide a device for securing safety from the danger of the rotation of the blade rotating blade and to increase the efficacy of the blade rotating blade in the commercialization of the blade rotating blade to various transport engines.

The present invention forms a streamlined (103.105) of the cross-section of the blade 102 and the flagpole 104 in order to increase the lifting force and reduce the rotational friction, the outer surface of the blade 102 in the arc of the outer rotation surface The inner surface of the blade 102 is aligned with the arc of the inner rotational surface, and the blade rotation blade characterized in that the angle of the outer arc and the angle of the inner arc are the same with respect to the center of the rotation axis.

And, in the present invention, the blade 102 is a blade end rotary blade 101a is divided into the flagpole 104 or a blade tip portion without the distinction between the wing 102 and the flagpole 104 is wide and thin toward the center (Hud) The blade is a blade rotating blade characterized in that the blade rotating blade (101b).

In addition, in the present invention, the flagpole 104 of the blade 102 has a cross-section of the streamlined wing 105, or if the length of the flagpole 104 is long to fix the flagpoles 104 to each other A feather tip ring 107 is formed to prevent fluttering or vibration, or a feather tip ring 108 and a feather ring 109 are formed at the tip or inner part of a wing. to be.

And, in the present invention, the protection net 2402 is installed to protect from the danger caused by the rotation of the feather blades and prevent foreign objects from entering, and hit through the cover 2401 and the outer border 2403 It is a feather-blade wing, characterized in that to increase the thrust of the rotor blades by collecting the air toward the wing 2102 to increase the density of the air hitting the wing 2102.

In addition, the present invention lengthens the width (2108) of the feather tip fixing ring 2105 and the pinion fixing ring (2106) for fixing each wing 102, the front between the two fixing rings to install the wing 2101 The rear side is fixed by connecting the streamlined flagpole (2102), and connects the pinned anchor ring (2106) and the central portion (2104) with a connecting plate (2103), to prevent the airflow scattered through the rotation of the blade (102) It is a feather blade which is characterized by gathering together to create a more stable and strong thrust.

The present invention is less rotational loss than the existing propeller, to obtain a faster rotational speed to make a more powerful thrust.

Compared with the existing propeller, the present invention has less noise, and because the speed of the blade can be made faster in a short time, fast thrust is obtained.

The present invention can be used as a rotary blade for propulsion or landing vertical landing and giving a predetermined blade angle (Blade angle).

The present invention is easy to use for small and medium aircraft, such as various drones, helicopters, light aircraft.

Therefore, the present invention does not need the wing of the existing airplane body, it becomes an invention that allows to open the medium and small electric airplane age without the runway for takeoff and landing.

The present invention uses a propeller to increase the turning force of wheels, etc., rather than driving the rotating shaft of the wheels directly by an electric motor, thereby enabling the operation of various transportation engines with less driving force. It is very economical because it increases efficiency.

Feather rotary blades for the transport engine of the present invention can be mounted on a variety of vehicles, such as trains, ships, and other transport engines to obtain a more powerful thrust at low cost and high efficiency.

1 (a), (b) and (c) are sectional views showing the front view of the small blade end rotary blades and the first and second forms of the blade end rotary blades.

2 is a front view of the medium and large feather tip rotor blades.

Fig.3 (a) (b) is a front view of a feather tip blade | wing with a feather tip and an anchor ring.

Figure 4 is a cross-sectional view of the central assembly of the rotating shaft of the present invention, a cross-sectional view of the central assembly of the rotary shaft of the blade landing blade for vertical landing and landing.

5 is a cross-sectional view of the central assembly of the rotary shaft of the present invention, a cross-sectional view of the central assembly of the rotary shaft of the blade front rotor for propulsion in front of the body.

Figure 6 is a cross-sectional view of the central assembly of the rotating shaft of the present invention, a cross-sectional view of the central assembly of the rotary shaft blade blade for propulsion behind the body.

7 is a front view and a cross-sectional view of the blade end rotary blade for a transport engine of the present invention.

8 is a side view and a cross-sectional view of the shaft of the rotor blade rotation of the present invention.

9 is a front view and a sectional view of the fixing device of the present invention.

10 is a front view and a sectional view of the protective net cover of the present invention.

11 is an overall configuration diagram of a power system of the present invention.

101: feather turn blade

101a: Feather rotation blade to distinguish wings and flagpoles

101b: Feather rotation blade with no distinction between wings and flagpoles

102: wings

103: streamlined cross section

104: flagpole

105: streamlined wing

106: Hub

107: flagpole fixing ring

108: feather tip fixing ring

109: feather ring

401: feather turn blade

402: rotation axis

405: Bearing

406: Upper magnet bearing

407: Lower magnetic bearing

408: magnetic bearing connecting plate

410 gas body

411: motor

412: Front magnet bearing

413: Rear magnet bearing

414: Front Magnet Bearing

415: Rear magnet bearing

The embodiments of the present invention may be modified in various forms, and the scope of the present invention should not be interpreted as being limited by the embodiments described below. This embodiment is provided to more completely explain the present invention to those skilled in the art. Therefore, the shape of the components in the drawings, etc. have been exaggerated to emphasize a more clear description.

In addition, when a component is described as being "connected", "coupled" or "connected" to another component, the component may be directly connected to or connected to the other component, It is to be understood that other components may be "connected", "coupled" or "connected".

1 (a), (b) and (c) are cross-sectional views showing the front view of the small blade end rotary blades and the first and second forms of the blade end rotary blades, and FIG. 2 is a front view of the medium and large blade end rotary blades, and FIG. Is a front view of a feather tip blade with a feather tip and an anchor ring.

Feather blade rotor blade 101 of the present invention, as shown in Figure 1, the blade 102 and the flagpole 104 is installed on the propeller blade (Blade tip) fast rotation speed to obtain a large lift and fast thrust, as shown in FIG. Refers to a rotary blade composed of).

As shown in FIG. 1, the blade 102 of the blade rotating blade 101 uses a wing such as a wing shape of an aircraft or a streamlined end face 103 of a propeller blade.

The blade 102 of the blade rotating blade 101 is a blade rotating blade 101a, a blade 102 and a flagpole, in which the blade 102 and the flagpole 104 are divided as shown in FIG. 1 (b) (c). 104 shows the first, second, and forms of the blade end blade 101b which have a wide end portion and become thinner toward the central portion 106 without division.

The wing 102 is manufactured to match the outer surface of the wing 102 to the arc of the outer rotation surface, the inner surface of the wing 102 to the arc to the inner rotation surface in order to reduce the rotational friction. At this time, the angle of the outer arc and the angle of the inner arc are the same with respect to the center of the rotation axis.

The wing 102 is installed at the propeller blade (Blade tip) of high rotational speed in order to reduce the rotation loss of the entire rotor blade 101, to obtain a large lift and fast thrust.

The speed of the blade rotation blade 101 is given by v = rω, where r is the radius of rotation of each portion of the blade rotation blade 101, ω is ω = 2πn (n is the number of revolutions per second) at an angular velocity.

When the rotor blade 101 rotates, the blade back of the blade (102) is the air flow is faster, the lower (blade face) is slower, the lift force is generated to obtain the thrust of the blade 102 shape, feather angle (Blade angle) gives a strong thrust.

In the present invention, the size and number of the end rotor blade 101 is determined and installed so as to obtain sufficient thrust according to the size, weight and use of the aircraft.

In addition, since the present invention is mostly used as a fixed pitch propeller, the rotor blade is installed by giving a blade angle to obtain sufficient thrust according to a predetermined rotation speed.

Calculate the lift and thrust according to the size and number of revolutions of the rotor blade 101, and maintain the aircraft at a constant height (cruising altitude) according to the size, weight, and purpose of the aircraft. To determine the size and number and the feather angle of the rotor blade (101) so that the flight at a speed) is installed.

The material of the wing 102 and the flagpole 104 uses a heavy material such as a metal material in order to increase the rotational inertia of the present rotary blade to smoothly rotate. However, when the weight of the gas is small or when using the feather tip ring 108 as shown in Figure 4 may be used a light metal or wood.

Rotational inertia of the rigid body (wing) is I = Mr ² , so it is proportional to the square of the rigid body's weight (M) and the radius of rotation of the rigid body (r), so that the blade 102 is attached to the blade tip. The rotational inertia is much larger than the existing propellers, so that the rotation is smoothly performed well.

As shown in FIG. 2, the medium and large feather tip rotating blade 101 having a long flagpole 104 connects the flagpole 104 to an intermediate portion of the flagpole 104 in order to prevent fluttering or vibration caused by excessive blade speed. Fixed by connecting with a fixing ring (107).

In the type of the feather tip blade 101, as shown in FIG. 1, the blade tip blade 101a and the blade tip 102 and the flag pole 104 which are distinguished from the blade 102 and the flag pole 104 are distinguished, There is a blade end blade 101b and the like that becomes thinner toward the central portion 106.

3 (a) is a feather tip blade with a feather tip ring 108 and a pinned ring ring 109, the pin tip ring 108 is to adjust the wing 102 in accordance with the arc of the outer surface of the blade 102 Fixing and feathering ring 109 is fixed in accordance with the arc of the inner surface of the wing 102, the blade end ring 108 and feather ring 109 is to increase the rotational inertia of the rotor blades As a result, the rotation of the rotary blade is smoothed, and the airflow of the blade 102 generated through the rotation is prevented, thereby creating a more stable and strong thrust.

3 (b) is a feather tip rotating blade having only the feather tip ring 108 using a wing 101b having a wider end portion and thinning toward the central portion 106 without the distinction between the wing 102 and the flagpole 104. , The feather tip fixing ring 108 to secure the blade 102 in accordance with the arc of the outer rotary surface of the blade 102 and to increase the rotational inertia of the rotary blade to smooth the rotation of the rotary blade, through the rotation By preventing the scattering of the air flow of the wing 102 is generated to create a more stable and strong thrust.

The use of the present invention is used for the takeoff and landing of a vehicle vertically or for propulsion to speed the aircraft.

When the present invention is used for vertical takeoff and landing, it is manufactured by setting the blade angle to maintain the cruising altitude according to the constant rotational speed, and when using it for propulsion, to maintain the required cruising speed according to the constant rotational speed. Set up the quill angle and install it.

The rotation of the present invention is a motor, by adjusting the rotational speed of the motor to generate a thrust so that the aircraft can float at a certain height (cruising altitude), or to generate a thrust to operate at a constant speed (cruising speed) do.

Since the present invention is mostly used as a fixed pitch propeller, the required thrust is obtained by adjusting the rotation speed.

In the present invention, when used as a fixed pitch propeller, the whole body is manufactured in one body, or the flagpole 104 and the flagpole center portion 106 are manufactured in one body, and the wings 102 and the flagpole 104 are uniform depending on the purpose of manufacture. Produce by giving a pitch.

Figure 4 is a cross-sectional view of the central assembly of the rotary shaft of the present invention, a cross-sectional view of the central assembly of the rotary shaft of the blade tip rotor blade for vertical landing and landing, Figure 5 is a cross-sectional view of the central assembly of the rotary shaft of the present invention, for propulsion in front of the body Fig. 6 is a sectional view of the central assembly of the rotary shaft center assembly of the present invention, and Fig. 6 is a sectional view of the central assembly of the rotary shaft center assembly of the present invention.

4 is a magnet assembly as shown in FIG. 4 in order to reduce mechanical rotational friction generated when the rotary blade 401 is rotated and the gas body 410 is pulled up, pulled or pushed forward while the rotary blade 401 is rotated. Bearings are installed.

When the present invention is used for vertical take-off and landing as shown in FIG. 4, the upper magnetic bearing 406 as a sectional view of the central assembly portion of the rotating shaft 402 is provided with a magnetic bearing capable of withstanding the weight of the base body 410, and The magnetic bearing 407 is mechanically rotated during the rotation operation of the rotary blade 401 by installing a magnetic bearing that can withstand the rotor blade 401, the magnet connecting plate 408 and the weight of the rotor of the motor 411, etc. Reduce friction

As shown in Figure 5, when using the present invention for the front propulsion of the rotating shaft 402, the front sectional view of the front magnetic bearing 412 is the force that the rotary blade 401 pulls the body main body 410 The magnetic bearing that can withstand the installation, and the rear magnet bearing 413 is the front magnet bearing 412 is installed so that the magnetic bearing connecting plate 408 does not stick with the body main body 410 rotation of the rotary blade 401 Reduce mechanical rotational friction during operation.

As shown in Figure 6, when the present invention is used for propulsion in the back of the body constituting the cross-sectional view of the central assembly portion of the rotating shaft 402 is the force that the rotary blade 401 pushes the body body 410 The magnetic bearing that can withstand the installation, and the rear magnet bearing 415 is the front magnet bearing 414 is installed so that the magnetic bearing connecting plate 408 does not stick with the body main body 410 to rotate the rotary blade 401 Reduce mechanical rotational friction during operation.

The connection portion between the rotary shaft 402 and the base body 410 rotates horizontally as shown in FIGS. 4 and 6 and when the rotary shaft 402 rotates vertically as shown in FIG. 4 to reduce mechanical friction when the rotary shaft 402 rotates. In order to reduce the mechanical friction when the bearing 405 is installed accordingly.

Next, a description will be given of a transportation engine using a feather rotor blade.

7 is a front view and a cross-sectional view of the blade end rotary blade for a transport engine of the present invention, Figure 8 is a side view and a cross-sectional view of the blade end rotary shaft of the present invention, Figure 9 is a front view and a cross-sectional view of the fixing device of the present invention, Figure 10 is Front view and sectional drawing of the guard net cover of this invention, FIG. 11 is an overall block diagram of the power system of this invention.

Feather rotating blade used in the present invention, as shown in Figure 7 to prevent flutter (fluttering) or vibration generated in the existing propeller, etc., and to increase the rotational inertia of the rotary blade to the feather tip ring (2105) and the inner blade A feather-rotating blade with a fixing ring 2106 is used, and the width 2108 of the feather tip fixing ring 2105 and the pinned ring fixing ring 2106 is lengthened, and the front side between the two fixing rings is the wing 2101. And the rear side is fixed by connecting to the wing-shaped flagpole (2102), by connecting the anchor ring (2106) and the central portion (2104) with a connecting plate (2103), of the air flow generated through the rotation of the blade (102) The blade rotor blade for a transportation engine of the present invention is used to prevent scattering and to gather together to create a more stable and strong thrust.

The center portion 2104 of the connecting plate 2103 makes a square groove in the center for connecting with the rotation shaft 2107.

8 is a side view and a cross-sectional view of the rotary shaft of the end of the rotor blade, the center portion 2202 is a square so as to be connected to the center of the rotor blades 2104, the front of the center portion 2202 to fix the rotary blades and the rotating shaft The fixing stand 2201 is fixed and manufactured, and the rear side is made of a bolt screw 2203 to be fixed by the fixing nut 2205. In addition, the connecting projection portion 2204 having a rectangular cross section formed at the rear of the rotating shaft is manufactured in one or both portions in a straight line as a cross section in order to connect the motor and the coupling.

9 is a fixing device for easily rotating the end rotor blade 2301, the fixed frame 2303 is connected to the rotating shaft 2302 to reduce the rotational load, such as mechanical friction due to the weight of the end rotor blade 2301. The bearing 304 is installed on the site so that the feather tip rotor blade 2301 can rotate smoothly. The air flowing portion of the wing between the outer fixing device and the center of the fixing device is connected to the wing-shaped flag pole (2305).

FIG. 10 is a protection net cover of the rotary blade, and this rotor blade is commercially used in various vehicles, trains, ships, and other transportation engines. And prevents foreign objects from entering, and the cover 2401 and the outer border 2403 collect the air collided toward the wing 2102 to increase the density of the air colliding with the wing 2102, thereby increasing the thrust of the rotor blades. To increase.

In addition, to reduce the rotational load, such as mechanical friction due to the weight of the rotor blades, to install a rotary bearing bearing (2405) on the guard net cover side to prevent the rotation of the rotor blades to rotate smoothly and connect the connecting portion (2404) to the fixing device To fix

The power of the feather blade is made up of the sum of the wind energy that strikes each blade 2102 and the lift generated by the rotational speed of the blade 2102. The wind energy that strikes one wing 2102 is simply calculated by the following formula.

Wind energy

Where ρ is the air density, A is the perpendicular area where the wing is formed by the feather angle of the wing 102, wind is n, the number of revolutions per second of the wing, r ₀ is the average radius of rotation of the wing 2102, The unit of wind energy is kgm ² / sec ³ [W].

The size of this rotor blade can be produced in a suitable size according to the power (power) and the size of the product required by each product. In general, the diameter of rotor blades is 0.6m ~ 1.2m for automobiles, and 1.4m ~ 2.4m for buses, trucks, and trains.

Various ships can be operated by installing two to three main rotor blades on the top of the ship, depending on the size of the ship.

The rotor blades using the outer rotor are used for transport engines that require greater thrust such as high speed trains and large ships.

When the terminal rotor blade 2501 for a transportation engine suitable for each transportation engine is manufactured, it is installed to rotate the rotary blade 501 by the fixing device 2503, and the guard net cover 2504 is fixed to the fixing device 503. Connect The rotary shaft 2502 of the rotary blade 2501 and the rotary shaft of the motor 2505 are connected with a fixing pin or a coupling. Then, the power supply 2507 is connected to the inverter (speed controller) 2506 to adjust the rotational speed of the motor to operate the power system of the present invention.

In the above description of the present invention with reference to the accompanying drawings, a description has been made mainly on the "power unit and infinite self-generator using the same" having a specific shape and structure, the present invention can be variously modified and changed by those skilled in the art, such a modification And modifications should be construed as falling within the protection scope of the present invention.

Claims

In order to increase the lift formed in each wing 102 and flagpole 104 and to reduce rotational friction, its cross section is streamlined (103.105), the outer surface of the wing 102 is aligned with the arc of the outer rotation surface, the wing An inner surface of (102) is aligned with the arc of the inner rotating surface, and the feather blades, characterized in that the angle of the outer arc and the inner arc equal to the center of the rotation axis.
The method of claim 1,

The blade 102 is a blade end blade 101a in which the flagpole 104 is divided, or a blade end blade 101b having a wide end without a distinction between the blade 102 and the flag pole 104 and thinning toward the center (Hud). Feather rotary wing, characterized in that.
The method according to claim 1 or 2,

The flagpole 104 of the blade 102 is a streamlined wing 105 of the cross section, or if the length of the flagpole 104 is long to fix the flagpole 104 to each other to flutter (fluttering) or vibration of the blade Flagpole fixed ring (107) to prevent, or feather tip ring (108) and feather pinned ring (109) formed on the tip or inner portion of the wing blades.
The method according to claim 1 or 2,

In order to protect from the danger of the rotation of the feather blades and to prevent foreign objects from entering the guard net 2402 is installed, the air hitting through the cover 2401 and the outer border 2403 toward the wing 2102 Feather rotating blades, characterized in that to increase the thrust of the rotary blades by increasing the density of the air hitting the wings (2102).
To extend the width (2108) of the feather tip fixing ring (2105) and the pinion fixing ring (2106) fixing each of the wings (102), the front between the two fixing rings to install the wing (2101) and the rear streamlined flagpole ( 2102) to be fixed and connected to the pinned anchor ring 2106 and the central portion 2104 by the connecting plate 2103, to prevent the scattering of the air flow generated through the rotation of the wing 102, gather together Feather rotary wing, characterized by producing a stable and strong thrust.
The method of claim 5, wherein

In order to protect from the danger of the rotation of the feather blades and to prevent foreign objects from entering the guard net 2402 is installed, the air hitting through the cover 2401 and the outer border 2403 toward the wing 2102 Feather rotating blades, characterized in that to increase the thrust of the rotary blades by increasing the density of the air hitting the wings (2102).