KR20130052168A

KR20130052168A - Long-endurance aircraft with vertical takeoff and landing

Info

Publication number: KR20130052168A
Application number: KR1020110117460A
Authority: KR
Inventors: 구자용
Original assignee: 한국표준과학연구원
Priority date: 2011-11-11
Filing date: 2011-11-11
Publication date: 2013-05-22

Abstract

PURPOSE: A long-endurance vertical takeoff and landing aircraft is provided to enable the aircraft to take off and land in a narrow space by generating lift force with rotary blades. CONSTITUTION: A long-endurance vertical takeoff and landing aircraft comprises a main body, a rotary shaft(30), a blade hub(12), blades(10), and engines(20). The bottom of the rotary shaft is rotationally connected to the top of the main body. The blade hub is fixed at the top of the rotary shaft. The blades are in parallel to the ground and are radially arranged on the rotary shaft. One end of the blades is coupled to the blade hub. The engines are respectively arranged in the blades to rotate the blade by thrust.

Description

Long-Endurance Aircraft with Vertical Takeoff and Landing}

The present invention relates to a rotorcraft vertical takeoff and landing vehicle, and more particularly, to a vertical takeoff and landing aircraft having a thrust generating engine on a rotating blade to rotate the blade through the engine.

In order to be able to patrol long distances over long periods of time at high altitudes in the air, aircraft with high flight efficiency and long-term flight are required.

To fly in the air, you need to lift the aircraft in the air. As a method for generating lift of a vehicle, it may be divided into a fixed wing method used in a conventional aircraft and a rotary wing method used in a helicopter.

Fixed wing aircraft can use long wings to generate efficient lift for long flight. Fixed wing vehicles require horizontal speed to generate lift. Therefore, a long runway is required to achieve sufficient speed during initial takeoff, and a large space is also required for landing. In particular, it is necessary to continue horizontal flight to gain lift during flight, and it is not possible to have a standing flight or a vertical takeoff and landing in place.

On the other hand, helicopters are capable of vertical takeoffs and landings in narrow locations, but also capable of stationary airspace, but shorter rotor blades than fixed-winged aircraft and generate more lift due to the rotational force of the wings. This is difficult. In addition, the torque generated by the rotor blades and additional devices to offset them make the aircraft less stable and difficult to maneuver.

Therefore, vertical takeoff and landing and stationary flight are possible, but the energy efficiency is high.

The present invention has been made to solve the above problems, an object of the present invention, by using a rotary blade system, by rotating the blade through the thrust generating engine provided in the blade long-term that does not generate torque in the body It is to provide a vertical takeoff and landing aircraft.

In addition, it is to provide a vertical take-off and landing aircraft of long-term flight that can be controlled rapidly and fine lift by varying the inclination angle of the blade continuously.

Vertical takeoff and landing aircraft of the present invention, the main body; A rotating shaft having a lower end rotatably connected to an upper side of the main body; A blade hub fixed to an upper end of the rotating shaft; A blade that is horizontal to the ground and has one end coupled to the blade hub, the blade being provided in a plurality of radially about the rotation axis; And an engine provided in each of the blades to rotate the blades by thrust. And a control unit.

In another embodiment, the main body; A rotating shaft having a lower end rotatably connected to an upper side of the main body; A blade hub fixed to an upper end of the rotating shaft; A blade that is horizontal to the ground and has one end coupled to the blade hub, the blade being provided in a plurality of radially about the rotation axis; And a plurality of engine frames horizontal to the ground and having one end coupled to the blade hub and spaced apart from each other by a predetermined distance below or above the blade. Engines provided at each of the other ends of the engine frame to rotate the engine frame by thrust; And a control unit.

In this case, the blade is coupled to the blade hub so that the inclination angle with the ground is variable, or the blade is further provided with an aileron in the rear direction of rotation, the aileron is coupled to the blade so that the inclination angle with the ground is variable do.

In addition, the vertical takeoff and landing aircraft includes a plurality of horizontal flight engines provided on the main body to horizontally move the main body by thrust, and the horizontal flight engine is capable of controlling each of the two to change the direction of the main body. It is characterized by.

The vertical takeoff and landing aircraft of the long-term flight of the present invention by the above configuration has the following effects.

First, it is possible to take off and landing in a narrow place because the vertical takeoff and landing is possible by generating lift through the rotary blades.

Second, the present invention, because the blade is self-rotating through the rotating engine does not induce a torque to the body unlike conventional helicopters do not interfere with the stability of the aircraft, high stability of the aircraft during takeoff and landing or long-term flight and low-speed horizontal flight Easy to control and low risk of accident

Third, it is possible to apply the blade longer than the conventional rotor blade type aircraft can increase the lift force is efficient long-term flight is possible.

Fourth, the lifting blades can be generated without the horizontal speed in the rotary vane method, so that the stopping air can be.

1 is a front schematic view of a vertical takeoff and landing body of a first embodiment of the present invention;
2 is a front schematic view of a vertical takeoff and landing body of a second embodiment of the present invention;
3 is a plan view of the vertical takeoff and landing aircraft of the present invention.
4A is a cross-sectional view taken along line AA ′ of FIG. 3.
4B and 4C are cross-sectional views of the blade having a variable inclination angle of FIG. 4A.
5 is a plan view of a vertical takeoff and landing vehicle according to a third embodiment of the present invention.
FIG. 6A is a cross-sectional view taken along line BB ′ of FIG. 5.
6B and 6C are cross-sectional views of the blade having an aileron having a variable inclination angle of FIG. 6A.

Hereinafter, an embodiment of the present invention will be described in detail with reference to the drawings.

- Example 1

1 to 3, the vertical takeoff and landing vehicle of the present invention includes a blade unit 10, an engine 20, a rotation shaft 30, a body 40, and a horizontal flight engine 50.

The main body 40 may be applied to the configuration of the main body of the conventional helicopter on the housing, so a detailed description thereof will be omitted. However, in the main body 40 of the present invention, a configuration for rotating the blade unit 10 or a configuration for offsetting the rotational torque of the main body 40 may be deleted. The landing frame 41 is provided below the main body. Landing frame 41 may be applied to the conventional skid (Skid) method.

The rotary shaft 30 is coupled to the upper side of the main body 40. The rotating shaft 30 is installed in the vertical direction vertical to the ground, the lower end is coupled to the upper side of the main body 40. At this time, the rotating shaft 30 is coupled to the main body 40 to be rotatable about the axial direction. Coupling method of the rotating shaft 30 and the main body 40 may be applied to the coupling method using a conventional bearing.

The blade unit 10 is coupled to the upper end of the rotating shaft 30. The blade unit 10 is composed of a blade 11 and a blade hub 12. The blade hub 12 consists of a circular plate. Although the blade hub 12 is shown in a circular shape, any shape may be applied as long as the blade hub 12 is connected to the rotary shaft 30 to support the blade 11. The upper end of the rotating shaft 30 is fixed to the center of the lower surface of the blade hub (12). The blade 11 is positioned horizontally on the ground. Blade 11 is provided with a plurality, one end is coupled to the peripheral surface of the blade hub (12). The shape of the blade 11 may be applied to a conventional helicopter blade. The blade 11 may be configured radially about the rotation axis 30. In this case, the blade 11 may be coupled to the blade hub 12 so that the inclination angle with the ground is variable. Therefore, when a line connecting the center of the cross section of the blade 11 is referred to as a variable axis, it is coupled to the circumferential surface of the blade hub 12 so as to be rotatable about the variable axis. Through the configuration as described above makes it possible to quickly and finely adjust the lift during rotation of the blade (11).

The engine 20 is provided on the lower surface of the blade 11. The engine 20 may be a conventional engine for generating thrust. Engine 20 may be provided with a plurality of to be installed on each blade (11). At this time, each engine 20 is installed so that the distance to the rotation shaft 30 is the same. That is, each engine 20 may be arranged in a symmetrical with respect to the rotation axis (30). This is to prevent the vibration during the rotational movement.

In addition, the present invention has the following configuration to maximize the flight efficiency.

The distance between the engine 20 and the rotation shaft 30 is preferably 20 to 70% of the length of the blade 11. When the engine 20 with high output can be applied to rotate the blade 11 at a sufficiently strong force at a high speed, the distance between the engine 20 and the rotation shaft 30 is preferably shortened to about 20% of the length of the blade 11. In order to increase the energy efficiency by applying the engine 20 having a low output, it is preferable to lengthen the distance between the engine 20 and the rotation shaft 30 to about 70%. Therefore, the distance between the engine 20 and the rotation shaft 30 can be varied within the above range according to the output of the engine.

Through the above configuration, the blade unit 10 rotates by the engine 20 to generate lift force by itself, and thus does not generate torque in the main body 40, and it is possible to apply a longer blade than a conventional helicopter blade and fly efficiency. Is higher.

The horizontal flight engine 50 may be installed on the main body 40. Since the object of the present invention is not for high-speed horizontal start, the horizontal flight engine is provided on the main body 40 to perform horizontal movement at low speed or to individually control each of the plurality of horizontal flight engines to change the direction of the main body. Can be used to The horizontal flight engine 50 is provided in plural on one side and the other side of the main body. Horizontal flight engine 50 is applied to a conventional engine for generating a thrust. The horizontal flight engine 50 simultaneously controls a plurality of aircraft to horizontally fly the main body 40, or controls a plurality of each to change the direction of the main body 40.

- Example 2

2, the vertical takeoff and landing vehicle of the present invention includes a blade unit 10, an engine 20, a rotation shaft 30, a main body 40, and a horizontal flight engine 50.

The second embodiment of the present invention is characterized in that the coupling structure of the blade unit 10 and the engine 20, except for the configuration is the same as the first embodiment of the present invention, the same configuration will be omitted and described do.

The blade unit 10 of the second embodiment of the present invention is composed of a blade 11, a blade hub 12a, an engine frame hub 12b, and an engine frame 13. The blade hub 12a consists of a circular plate. The engine frame hub 12b is formed below or above the blade hub 12a and is formed of a circular plate. Although the engine frame hub 12b is illustrated as being coupled to the bottom surface of the blade hub 12a in the drawing, the engine frame hub 12b is coupled to the bottom or top surface of the blade hub 12a, or the blade hub 12a. It can be formed integrally with.

The upper end of the rotating shaft 30 is fixed to the center of the lower surface of the engine frame hub 12b. The blade 11 is positioned horizontally on the ground. Blade 11 is provided with a plurality, one end is coupled to the peripheral surface of the blade hub (12a). The shape of the blade 11 may be applied to a conventional helicopter blade. The blade 11 may be configured radially about the rotation axis 30. In this case, the blade 11 may be coupled to the blade hub 12a so that the inclination angle with the ground is variable. Therefore, when the line connecting the center of the cross section of the blade 11 is called a variable axis, it is coupled to the circumferential surface of the blade hub 12a to be rotatable about the variable axis. Through the configuration as described above makes it possible to quickly and finely adjust the lift during rotation of the blade (11).

The engine frame 13 is located horizontally on the ground. Engine frame 13 is provided with a plurality, one end is coupled to the circumferential surface of the engine frame hub (12b). The engine frame 13 is configured radially about the rotation shaft 30.

The engine 20 is provided at the other end of the engine frame 13. The engine 20 may be a conventional engine for generating thrust. Engine 20 may be provided with a plurality so as to be installed on each engine frame (13). At this time, each engine 20 is installed so that the distance to the rotation shaft 30 is the same. In other words, each engine frame 13 may have the same length. This is to prevent the vibration during the rotational movement.

In the second embodiment of the present invention as described above, since the blades 11 and the engine 20 are separated, the number of blades 11 and the number of engines 20 may be different. For example, if a plurality of engines 20 with weak outputs are used, even if a few of the engines 20 are defective, there is an advantage in that they can safely land with time allowance without being connected to an accident immediately. In addition, since the engine 20 is not mounted on the blade 11, there is an advantage that the blade 20 having a different length and shape can be used depending on the purpose without replacing the engine 20.

Example 3

5 and 6, the vertical takeoff and landing vehicle according to the third embodiment of the present invention includes a blade unit 11 and 12, an engine 20, a rotation shaft 30, a body 40, and an aileron 60. Is done.

The third embodiment of the present invention is characterized in that the blade portion 10 and the aileron 60, except for the configuration is the same as the first embodiment or the second embodiment of the present invention, the same configuration is omitted and described Let's do it.

The blade unit 10 is coupled to the upper end of the rotating shaft 30. The blade unit 10 is composed of a blade 11, a blade hub 12 and the aileron 60. The blade hub 12 consists of a circular plate. The upper end of the rotating shaft 30 is fixed to the center of the lower surface of the blade hub (12). The blade 11 is positioned horizontally on the ground. Blade 11 is provided with a plurality, one end is coupled to the peripheral surface of the blade hub (12). The blade 11 may be configured radially about the rotation axis 30. At this time, the blade 11 has the following configuration so that the inclination angle with the ground is variable. The aileron 60 is formed at the rear side of the blade 11 in the rotational direction. Aileron (60) is applied to the configuration of a conventional auxiliary blade and one end may be hinged to the blade 11 through the hinge coupling portion 61 so that the inclination angle with the ground is variable. The aileron 60 may be applied to only a part of the blade 11 as shown in the figure. Through the above configuration, the blade 11 is not changed to change the inclination angle with the ground when the blade 11 rotates, and only the aileron 60 is varied so that the lift force can be adjusted more quickly and finely.

Hereinafter, the operation of the present invention configured as described above will be described with reference to the drawings.

1. Preparation for takeoff

In order to prepare for takeoff, as shown in FIGS. 4A and 6A, the inclination angle with the ground of the blade 11 or the aileron 60 is adjusted so that lift does not occur even at a high speed rotation of the blade 11, and then the engine 20. Rotate the blade 11 until it reaches maximum rotation speed. Since the blade 11 is relatively long and heavy compared to the capacity of the engine 20, the blade 11 is initially rotated at a low speed, but accelerates gradually when the thrust is continuously applied to reach a high speed rotation after a predetermined time.

Since the blade 11 rotates but no lift is generated, the aircraft is in place.

2. Take off

When the rotation of the blade 11 reaches the maximum speed, as shown in FIGS. 4C and 6C, the inclination angle with the ground of the blade 11 or the aileron 60 is increased to generate lift. When the inclination angle is reached over a certain angle, lift force is generated to strike the aircraft in the air, and the aircraft takes off in the vertical direction. Since the inclination angle of the blade 11 or the aileron 60 is independently changed while maintaining the rotational speed of the blade 11, the vertical flying body of the present invention smoothly controls takeoff.

Since the blade 11 rotates with the force of the engine 20 attached to itself, the main body 40 does not generate torque and the vehicle is stably maneuvered. This is possible by eliminating the torque inherent in existing helicopters and the instability that occurs in the configuration to offset it.

3. Stop flight, horizontal flight and long flight

After the vehicle has risen to a sufficient altitude, the horizontal flight engine 50 is operated to allow horizontal flight at low speed. In addition, when the direction of the main body 40 is changed, the output of the plurality of horizontal flight engines 50 provided with each is controlled and adjusted.

In the case of applying the blade 11 of the long wing type like the conventional reconnaissance plane, it is possible to increase the lift in the vertical direction, which enables long-term air hole with high fuel efficiency. Since the present invention is basically implemented by an independent engine for vertical lift and horizontal flight, the stationary flight is possible when the horizontal flight engine 50 does not operate.

4. Landing

In the case of landing, when the horizontal flight is stopped and the tilt angle of the blade 11 or the aileron 60 is gradually reduced in the stationary hole state, and the lift force is gradually decreased, the aircraft lands on the ground in a stable posture.

The technical spirit should not be interpreted as being limited to the above embodiments of the present invention. Various modifications may be made at the level of those skilled in the art without departing from the spirit of the invention as claimed in the claims. Therefore, such improvements and modifications fall within the protection scope of the present invention as long as it will be apparent to those skilled in the art.

10: blade portion 11: blade
12: blade hub 13: engine frame
20: engine
30:
40: main body 41: landing frame
50: horizontal flight engine
60: Aileron 61: hinge coupling portion

Claims

Main body;
A rotating shaft having a lower end rotatably connected to an upper side of the main body;
A blade hub fixed to an upper end of the rotating shaft;
A blade that is horizontal to the ground and has one end coupled to the blade hub, the blade being provided in a plurality of radially about the rotation axis; And
An engine provided in each of the blades to rotate the blades by thrust;
Longitudinal takeoff and landing aircraft of the long-haul including.

Main body;
A rotating shaft having a lower end rotatably connected to an upper side of the main body;
A blade hub fixed to an upper end of the rotating shaft;
A blade that is horizontal to the ground and has one end coupled to the blade hub, the blade being provided in a plurality of radially about the rotation axis; And
A plurality of engine frames that are horizontal to the ground and have one end coupled to the blade hub and spaced apart at a predetermined distance downward or upward of the blade;
Engines provided at each of the other ends of the engine frame to rotate the engine frame by thrust;
Longitudinal takeoff and landing aircraft of the long-haul including.

3. The method according to claim 1 or 2,
The blade is a vertical takeoff and landing aircraft of the long-term ball, characterized in that coupled to the blade hub so that the inclination angle with the ground is variable.

3. The method according to claim 1 or 2,
The blade further comprises an aileron in the rear direction of rotation, the aileron is a vertical take-off and landing aircraft of the long-term ball, characterized in that coupled to the blade so that the inclination angle with the ground is variable.

3. The method according to claim 1 or 2,
The vertical takeoff and landing vehicle,
It includes a plurality of horizontal flight engine provided in the main body for horizontally moving the main body by the thrust,
The horizontal flight engine is a vertical takeoff and landing aircraft of the long-term flight, characterized in that each control is possible to change the direction of the body.