KR100620487B1 - Method and Rotor For Creating Lift - Google Patents

Abstract

The present invention relates to a rotor for generating a lift (lift), the rotor according to the invention is rotated by receiving power from the power source of the aircraft; A hub coupled to the idle shaft and at least partially rotated; At least two rotating shafts radially coupled to the rotating portion of the hub; Comprising a cylindrical blade coupled to each of the rotating shaft, the circular cross section of the cylindrical blade is configured to be perpendicular to the longitudinal direction of the rotating shaft and the cylindrical blade rotates the rotating shaft as the axis of rotation, but the The rotation direction of the cylindrical blade when viewed from the top and the rotational direction of the cylindrical blade when viewed from the center of rotation of the hub is characterized in that the counterclockwise direction if one is clockwise.

Rotor, cylindrical wing, hub, lift

Description

How to generate lift and rotor {Method and Rotor For Creating Lift}

1 is a perspective view showing a rotor according to the present invention.

Figure 2 is a cross-sectional view of the cylindrical blade of the rotor according to the present invention for explaining the principle of generating lift.

Figures 3a, 3b is an operation of one embodiment of the cylindrical blade of the rotor according to the present invention.

Figures 4a, 4b is an operation of another embodiment of the cylindrical blade of the rotor according to the present invention.

5 is a cross-sectional view showing an embodiment of a rotor according to the present invention.

※ Explanation of code for main part of drawing

11: cylindrical wing 12: air pocket

13: accommodating part 14: compressed air supply pipe

15, 16: cylinder 21: hub

22: bearing collection 23: bearing

24: inner cylinder 25: fixed bevel gear

26: idle shaft bearing portion 27: cover

31: revolution axis 41: rotation axis

42: moving bevel gear

The present invention relates to a rotor for generating lift, and more particularly, a method for generating lift by installing a cylindrical wing instead of a rotor blade of a conventional helicopter and allowing the cylindrical wing to rotate and revolve. It's about the rotor.

An object of the present invention is to provide a rotor for generating lift by rotating and revolving a cylindrical wing mounted in place of the rotor wing of a conventional helicopter and reducing the radius of the rotor when not in use to generate a lift for various applications.

In order to achieve the above object, the present invention provides a method of changing the blades of the rotor rotor of the helicopter into a cylindrical shape and giving a rotational movement thereto to generate a lift along with the orbiting movement.

In order to achieve the above object, the rotor for generating a lift according to the present invention includes an idle shaft which is rotated by receiving power from a power source of a vehicle; A hub coupled to the idle shaft and at least partially rotated; At least two rotating shafts radially coupled to the rotating portion of the hub; Comprising a cylindrical blade coupled to each of the rotating shaft, the circular cross section of the cylindrical blade is configured to be perpendicular to the longitudinal direction of the rotating shaft and the cylindrical blade to rotate the rotation axis as the axis of rotation, the hub The rotational direction of the cylindrical vane when viewed from above and the rotational direction of the cylindrical vane when viewed from the center of rotation of the hub is such that one is clockwise and the other is counterclockwise.

In addition, the cylindrical wing is preferably composed of an accommodating portion for storing the air bag and the air bag is enclosed when the compressed air is supplied to the inside of the cylinder expands tightly and the compressed air is discharged.

In addition, the air bag is preferably made of carbon fiber and an elastomer.

In addition, the cylindrical wing is preferably composed of a multi-stage telescope type so that it can be extended and contracted.

In addition, the hub is coupled to the rotating shaft and integrally coupled to the bearing housing having a bearing portion to be inserted into the rotating shaft and comprises a hollow outer cylinder of the upper surface is a fixed bevel gear is coupled to the aircraft, the rotating shaft It is preferable that the movable bevel gear is integrally coupled and the movable bevel gear and the fixed bevel gear formed on the outer cylinder are engaged so that the rotating shaft is engaged with the bearing housing and rotated by itself as the axis of rotation.

In addition, the top of the bearing house is preferably coupled to the cover covering the inside of the rotating shaft and the hub.

In addition, it is preferable that the inside of the hub is provided with an idle shaft bearing unit coupled to the hub and the idle shaft passes.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

As shown in FIG. 1, the present invention replaces all of the rotor blades of a conventional helicopter with cylindrical blades 11 having a similar length, and the cylindrical wings are radially rotated with the portion of the hub 21. It has a structure that rotates with its own axis as a rotating axis through a device such as a bevel gear combined with the orbital movement. In FIG. 1, (1) shows the axis | shaft which is the center of revolution, and its rotation direction, and (2), (3), (4), (5) has shown the axis | shaft which is the center of rotation, and its rotation direction.

The principle of lifting force with the above structure and motion is based on the Magnus effect in fluid mechanics. In Fig. 2, X denotes a translational movement in air in a direction perpendicular to the axis of the cylindrical blade 11, Y denotes its rotational movement and direction, and Z denotes the lift force and the direction generated at this time. The translational motion is the relative motion between the cylindrical wing and the air, so it can be seen as the wind blowing on the stationary cylindrical wing.

As can be seen in FIG. 2, when the cylindrical blade 11 rotates, the upper portion of the cylindrical blade 11 rotates in the same direction as the direction of the wind blowing into the cylindrical blade 11. While the velocity of the air vortex passing upward increases, the lower portion of the cylindrical wing 11 rotates in the direction opposite to the direction of the wind blowing into the cylindrical wing 11, so the air vortex passing below the cylindrical wing 11 The speed of is reduced. Since the pressure of the air decreases as the speed increases, the air pressure below the cylindrical wing 11 becomes greater than the air pressure above, and the cylindrical wing 11 receives upward force. Such a force is called lift.

A typical formula for lift generated by the above principle is as follows.

Lifting force (f) = π × Air density (ρ) × rotation angle speed (ω) × cylinder blade radius (r) ² × wind speed (u) × cylinder length (l)

At this time, since the wind speed u is the speed by the revolution of each cylinder point with respect to the stationary atmosphere in the present invention, the idle angular velocity is Ω and the lifting force f per cylindrical blade 11 is passed through the cylindrical static component. Is given by

f = ∫ (π × ρ × ω × r ² × Ω × Γ) dΓ

However, Γ represents the distance from the center of revolution to the point of cylindrical randomness, that is, the radius of revolution of the point of cylindrical randomness.

The table below summarizes the lift and the power required to obtain the cylinder blade 11 by varying the radius and length. However, the revolution speed was 120rpm, and the rotation speed was 480rpm, which is four times the revolution speed.

 Diameter of cylindrical wing (m)   Cylindrical wing length (m) Lift (kgf) KW 0.28 1.68 45.6182 2.01296 0.32 1.92 64.6089 3.11012 0.36 2.16 88.9889 4.64074 0.4 2.4 119.696 6.72219 0.44 2.64 157.737 9.49133 0.48 2.88 204.196 13.106 0.52 3.12 260.233 17.7466 0.56 3.36 327.083 23.6175 0.6 3.6 406.052 30.9484 0.64 3.84 498.526 39.9964 0.68 4.08 605.961 51.0467 0.72 4.32 729.891 64.4146

In the above table, the first row indicates the diameter of the cylindrical blade 11, the second row shows the length of the cylindrical blade 11, the third row shows the lift force, and the fourth row indicates the power required for this lift.

When the rotor having the above structure is applied to a general vehicle, both the ground driving and the aerial flight are possible with the output of a conventional vehicle in terms of power. As can be seen in the above table, it can be lifted up to 730kgf with one cylindrical wing 11, so it can be concluded that using four cylindrical wings 11 can lift more than 2 tons of objects. However, in order to be able to fly by applying the rotor according to the present invention to a conventional vehicle, a tail rotor for canceling torque generated from the rotor, such as a conventional helicopter, or an apparatus having such a role should be added. The rotor having the same structure as the present invention can also be applied to the rotor.

When the cylindrical blade 11 according to the present invention is not rotated, it is necessary to greatly reduce its length to be suitable for storage or ground driving of a vehicle.

In the first method, as shown in FIG. 3, the cylindrical wing 11 is hardened by injecting compressed air into an airtight and elastic bag (bag) made by adding an elastomer (elastomer) to a strong fiber cloth such as carbon fiber. It is configured to inflate to a state. Such air bag 12 can be deformed to a small volume by discharging the compressed air therein when not in use.

When the cylindrical blade 11 is not required to be used, the entire air bag 12 is housed in a cylindrical air bag accommodating portion 13 having a hollow and one side open made of a material that is not deformed. And when it is necessary to use the cylindrical blade 11 as shown in Figure 4 when the compressed air supply from the compressed air supply pipe 14 connected to the hub 21 to the air bag 12 until the air bag 12 is hard The inflated air bag 12 is expanded to be a cylindrical shape extending to the open portion of the receiving portion 13 and can serve as a cylindrical wing 11.

Such a method can be easily applied to a vehicle provided with an air tank. The compressed air supply pipe 14 connected from the air tank is connected to the inlet of the air bag 12, and by installing a directional valve in the middle of the supply pipe 14, the air bag 12 is filled or removed by the pilot's operation. can do.

The second method is to divide the cylindrical blade 11 into two or three to configure a multi-stage telescope type. This is a method commonly used in a configuration that allows the length of the antenna or the like in such a way that the multiple cylinders (15, 16) is slidably configured to each other to adjust the length. When it is not necessary to use the cylindrical blade 11, as shown in Figure 5 several cylinders (15, 16) are all overlapped, and when it is necessary to use the cylindrical blade 11, as shown in Figure 6 Only the end of 15) is then extended so that the cylindrical blade 11 is long enough to generate lift by sliding it so that it is locked by the end of the cylinder 16. The cylinder 15 can be attached to something like a string to move the cylinder 15 by pulling it and may be equipped with a device that automatically stretches and contracts.

Figure 7 shows a specific embodiment of the present invention. The hub 21 according to the present embodiment is a bearing cylinder 22 integrally coupled to the upper end of the idle shaft 31 and an inner cylinder surrounding the idle shaft and is fixed to the vehicle as a hollow cylinder, and a fixed bevel which is an inclined gear on the upper surface thereof. It consists of the inner cylinder 24 in which the gear 25 is formed.

The four rotating shafts 41 are fitted to the four bearing portions 23 provided in the bearing housing 22 so as to be rotatably supported. A moving bevel gear 42 is coupled to the end of the rotating shaft 41 and the moving bevel gear 42 remains engaged with the fixed bevel gear 25 of the inner cylinder.

On the other hand, the cover 27 is coupled to the upper end of the bearing house 22, which prevents people from accessing the place where the bevel gear is operated, thereby increasing safety and preventing rain from accumulating inside the hub 21 during rain. In addition, the inner shaft bearing portion 26 is provided inside the inner cylinder to support the idle shaft 31 is not bent. In addition, the outer cylinder 28 is fixed to the upper surface of the vehicle around the inner cylinder 24.

The action of the rotor according to the present invention by the above structure is as follows. When flight is required, the compressed air is filled in the air bag 12 or the multi-stage cylinders 15 and 16 are extended, and when the engine is driven, the idle shaft 31 rotates and the bearing integral with the idle shaft 31. As the house 22 is rotated, the rotating shaft 41 also rotates. When the movable bevel gear 42 coupled to the rotating shaft 41 rotates along the upper surface of the inner cylinder 24, the movable bevel gear 42 is connected to the fixed bevel gear 25 formed on the upper surface of the inner cylinder 24. Since the mesh is engaged, the rotating shaft 41 rotates while the rotating shaft 41 rotates. Therefore, the cylindrical blade 11 integrally coupled with the rotating shaft 41 also rotates and rotates at the same time, so that lifting force is generated by the above-described principle, which causes the aircraft to float. The strength of lift can be adjusted by manipulating the transmission, which can change the rotational speed of the idle shaft. If the flight is unnecessary, the cylindrical blades 11 are reduced to eliminate inconvenience due to the length of the cylindrical blades 11.

As described above, according to the rotor for generating a lift according to the present invention, by using the Magnus effect through the rotation and orbital movement of the rotor blade can generate a sufficient lift to lift the vehicle even with the power of the existing general vehicle. When not flying, the cylindrical wings can be reduced in length to be stored in a narrow space and have the advantage of easy application to a general vehicle.

Claims (8)

delete delete A revolving shaft which is rotated by power from a power source of a vehicle, a hub coupled to the revolving shaft and at least partially rotated, at least two revolving shafts radially coupled to the rotating part of the hub, and coupled to each of the rotating shafts In a rotor for generating a lift with a cylindrical blade, When the cylindrical wing is supplied with compressed air therein, the cylinder is expanded in a rigid shape. When the compressed air is discharged, an air bag and a compressed air bag are accommodated as the air bag is retracted and compressed air is supplied to supply the compressed air to the air bag. A rotor for generating a lift, characterized in that the supply pipe is composed of a receiving portion connected The method of claim 3, The air generating rotor is characterized in that the air bag is made of carbon fiber and elastomer. delete delete The method of claim 3, A rotor for generating lift, characterized in that the hub for coupling with the rotating shaft is coupled to the top of the revolution shaft, the cover for covering the inside of the hub and the rotating shaft is coupled to the top of the hub delete

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