KR20160116736A - Convertible Wing Type Hybrid UAV - Google Patents

Abstract

The present invention relates to a convertible wing-type hybrid unmanned aerial vehicle including: a streamlined shaped body unit; a pair of main wing units extended from both lateral surfaces of the body unit; booms extended forward and rearward from the main wing units; lift-force generating units formed in upper and lower sides of both ends of the booms and selectively operated when the unmanned aerial vehicle takes off and lands in a vertical direction; a tail wing unit vertically formed in a rear end of the body unit for stable motions when the unmanned aerial vehicle flies; and a thrust generating unit formed in one side of the tail wing unit and providing thrust when the unmanned aerial vehicle flies in a horizontal direction. A mode of the unmanned aerial vehicle is shifted into one either a vertical landing and taking-off mode that a flight altitude is controlled by driving the lift-force generating units or a horizontal flight mode that thrust for a flight is supplied by driving the thrust generating unit when the unmanned aerial vehicle flies.

Description

Convertible Wing Type Hybrid UAV {Convertible Wing Type Hybrid UAV}

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a convertible wing type hybrid unmanned aerial vehicle, and more particularly to a convertible wing type hybrid unmanned aerial vehicle capable of switching between a vertical takeoff and landing mode and a horizontal flight mode.

In recent years, there has been considerable progress in multi-purpose miniature UAVs. Manually operated vehicles are a means of transportation that can be applied to jobs that can be expensive or risk a person's life.

For this reason, there is an increasing demand for civilian and military applicable vehicles for use in traffic monitoring, border security, monitoring of pipelines and power lines.

Unmanned aerial vehicles should fly at low speed and hovering when a specific target is needed or detailed mapping is required according to the surrounding environment, and should move at a high speed when leaving the vicinity.

Unmanned aerial vehicles generally consist of several groups. The fixed-wing type UAV has a merit that it can fly at a high speed for a long time with a simple structure. However, if the flying speed is too high, it is difficult to precisely carry out a flight between buildings in an urban environment. Also, there is a disadvantage that hovering can not be done because a runway is required when landing.

A helicopter-type UAV can be landed without a runway, but flight speed is not satisfactory. However, it has superior payload carrying ability compared to fixed wing type UAV.

Rotary wing aircraft are capable of hovering, have considerable level of mechanical complexity along with vertical landings, have agile maneuverability, and have low-speed and short-range flying ranges.

Tilt-rotor and tilt-wing unmanned aerial vehicles, which are currently under development, are more advantageous than fixed-wing unmanned aerial vehicles, and they can fly vertically and landing simultaneously and fly at long distances and at high speeds. It has the ability to be able to.

However, the main disadvantage of this unmanned aerial vehicle is that rotor and wing are required during the deformation, and additional mechanical coupling and control are complicated.

In addition, tiltrotor aircraft must overcome the negative angles generated when tilting the rotor 90 degrees while the vertical take-off and landing (VTOL) is deformed. This force is caused by the fuselage of the aircraft, which makes it difficult to control and to stabilize during flight.

A tiltrotor aircraft can not fly without an engine running. Therefore, safety design to cope with the above situation, low-speed hovering and high-speed flight design should be equipped.

Korean Patent Publication No. 10-2014-0034370

SUMMARY OF THE INVENTION The present invention has been conceived in order to solve the above-mentioned problems, and it is an object of the present invention to provide an air- The present invention provides a convertible wing type hybrid unmanned aerial vehicle capable of freely switching between the two modes.

It is another object of the present invention to provide a convertible wing type hybrid unmanned aerial vehicle capable of hovering at a low speed using a lift generating unit and capable of high-speed flight by using a propulsive force generating unit.

Another object of the present invention is to provide a convertible wing type hybrid unmanned aerial vehicle capable of compensating for the loss of lift by adjusting the rotation speed of the remaining elevating propellers when at least one of the plurality of ascending propellers does not operate.

In addition, a convertible wing-type hybrid unmanned aerial vehicle capable of reducing the air resistance and minimizing the carrying or storage space by allowing the outer wing portion to be housed inside the inner wing portion when the vertical landing and the landing is performed, The purpose is to provide.

The problems to be solved by the present invention are not limited to the above-mentioned problems, and other problems to be solved by the present invention, which are not mentioned here, can be understood by referring to the following description to those skilled in the art It will be understood clearly.

The present invention relates to a boom having a streamlined body part, a pair of main wings extending from both sides of the body part, booms extending from the main wing part respectively in forward and backward directions, A propulsive force generating unit provided at one side of the tail wing to provide a thrust during a horizontal flight; a propulsion generating unit provided at one side of the tail wing to provide a thrust during horizontal flight; A vertical takeoff and landing mode in which a flight altitude is controlled by the lift generating unit and a horizontal flight mode in which a driving force generating unit is driven and a thrust for flight is provided, .

Wherein the lift generating unit is constituted by a plurality of ascending propellers, and when one ascending propeller of the ascending propeller is not operated, the revolving speed of the remaining ascending propeller is adjusted to compensate lift by the ascending propeller.

The main wing portion includes an inner wing portion and an outer wing portion. The outer wing portion is accommodated in the inner wing portion and is drawn out to the outside in a horizontal flight mode.

The main wing portion includes an inner wing portion and an outer wing portion. The outer wing portion is hinged to the boom and is folded on the upper or lower portion of the inner wing portion. The horizontal wing portion is extended on an extension of the inner wing portion in the horizontal flight mode. .

Further comprising a direction elevating key hinged to the tail wing so as to vary the direction of movement of the UAV, and an aileron hinged to one side of the outer wing to control the rolling moment of the UAV .

And a measuring device provided at a front end of the body part for measuring the speed of the UAV.

And a monitoring device provided at a lower end of the body part and monitoring a surrounding situation.

According to the solution of the above-mentioned problems, the convertible wing type hybrid unmanned aerial vehicle of the present invention has the effect of freely switching to the vertical landing mode or the horizontal flight mode by using the lift generating unit.

Further, hovering can be performed at a low speed using the lift generating unit, and high-speed flight can be performed using the propulsion generating unit.

Further, when at least one of the plurality of rising propellers is not operated, the rotation speed of the remaining rising propeller is adjusted to compensate for the lost lift.

In addition, when the airplane is vertically moved or landed, the outer wing portion is received in the inner wing portion or folded to the lower portion of the inner wing portion, thereby reducing the air resistance and minimizing the carrying or storage space.

1 is a perspective view showing the overall configuration of a convertible wing type hybrid unmanned aerial vehicle according to an embodiment of the present invention;
2 is a perspective view illustrating an operation state of a main wing portion of a convertible wing type hybrid unmanned aerial vehicle according to an embodiment of the present invention;
3 is a perspective view illustrating an operation state of a main wing portion of a convertible wing type hybrid unmanned aerial vehicle according to another embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. However, the present invention is not limited to or limited by the embodiments. Like reference symbols in the drawings denote like elements.

BRIEF DESCRIPTION OF THE DRAWINGS The advantages and features of the present invention, and the manner of achieving them, will be apparent from and elucidated with reference to the embodiments described hereinafter in conjunction with the accompanying drawings.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described in more detail with reference to the accompanying drawings.

FIG. 1 is a perspective view showing the entire configuration of a convertible wing type hybrid unmanned aerial vehicle according to an embodiment of the present invention. FIG. 2 is a perspective view of a main wing 20 of a convertible wing type hybrid unmanned aerial vehicle according to an embodiment of the present invention. FIG. 3 is a perspective view showing an operation state of a main wing portion of a convertible wing type hybrid unmanned aerial vehicle according to another embodiment of the present invention. FIG.

1, a convertible wing type hybrid unmanned aerial vehicle according to an embodiment of the present invention includes a body 10, a main wing 20, a boom 30, a lift generator 40, a tail wing (50), and an impulse generating unit (60).

First, a body 10 constituting a central portion of the UAV 100 is provided. The body 10 has a general shape of a streamlined shape so that the resistance of the air is small and the capacity is increased and the resistance due to the interference of the airflow generated at the coupling portion with the main wing 20 to be described below is made as small as possible do.

Next, a main wing portion 20 extending to both sides of the body 10 is provided. The pair of main wing portions 20 is a wing for holding the lifting force of the entire UAV 100, and is structured so as to be robust and to withstand a large wing face load.

The main wing portion 20 includes an inner wing portion 21 and an outer wing portion 22. The inner wing portion 21 extends from a side surface of the body portion 10 and the outer wing portion 22 extends from a side surface of the inner wing portion 21. [

The aileron 23 hinged to one side of the outer wing 22 is provided. The aileron 23 is an adjusting surface attached to an end face of the transverse shape of the outer wing portion 22 of the UAV 100 to adjust the rolling moment to prevent rotation or rotation of the UAV 100 And the like.

As shown in FIG. 2, in the embodiment, the inner wing portion 21 forms a space therein, and the outer wing portion 22 is accommodated in the space. In the horizontal flight mode, And is drawn out to the outside of the wing portion (21).

Next, a boom (30) is provided extending from the main wing (20) in forward and backward directions. The boom (30) is formed in a bar shape and is installed in each of the pair of main wing parts (20). A plurality of landing stands 31 are mounted on both lower ends of the boom 30 so that the UAV 100 can support the ground without shaking.

3, the outer wing portion 22 of the other embodiment is hinged to the boom 30 and is folded to the lower portion of the inner wing portion 21. In the horizontal flight mode, And is configured to rotate in an axial extension line with the inner wing portion 21.

The outer wing portion 22 may be folded to the upper portion of the inner wing portion 21 and may be designed to be rotated in the horizontal extension mode with the inner wing portion 21 in the horizontal flight mode .

The boom 30 functions as a boundary between the inner wing portion 21 and the outer wing portion 22 and supports the lift generating portion 40 to be described below.

Next, a lift generation unit 40 is provided on both ends of the boom 30, respectively. The lift generation unit 40 is composed of a plurality of ascending propellers. Specifically, the elevating propellers are respectively provided in four pairs, symmetrically with respect to the same axial direction and with respect to the moving body 10, and serve to provide lifting force to the UAV 100.

The lift generation unit 40 is configured to be capable of forward rotation and reverse rotation, and can be raised or lowered in a vertical direction.

When one of the plurality of rising propellers is not operated, the rotation speed of the remaining rising propellers, that is, the output is adjusted to compensate for the lost lift of the inoperative rising propeller.

Next, a tail wing 50 formed vertically at the rear end of the body 10 is provided. The tail wing 50 is in a V-shape and is attached to the horizontal plane of the base body at the rear end of the body 10 of the UAV 100 to stabilize the radial direction along the direction of travel.

A direction elevating key 51 hinged to the tail wing 50 is provided to control the movement direction of the UAV 100 with respect to the vertical axis to provide stability.

Next, an impulse generating unit 60 is provided on one side of the tail wing unit 50. The driving force generating unit 60 is coupled to the rear end of the body 10 and the tail wing unit 50 to control the rudder and the elevator of the direction elevating key 51, And controls the yaw moment, which is a phenomenon in which the aircraft 100 is tilted to the left or right.

The thrust generating unit 60 provides thrust to the UAV 100 during horizontal flight.

Next, a measuring device 70 is provided at the front end of the body 10. The measuring device 70 is a measuring sensor for measuring a flow velocity of a fluid, and is used for a speedometer, a wind tunnel, etc. of the UAV 100. And measures the speed of the UAV 100 to a certain extent or higher.

The pitot tube is formed in the shape of a pointed pipe having a hole formed in the front and a side thereof. When the fluid is flowed in accordance with the flow of the fluid, the total pressure added to the positive pressure of the fluid plus the dynamic pressure and the positive pressure are applied to the side hole, The velocity of the flow is determined according to Bernoulli's theorem.

Next, a monitoring device 80 is provided at the lower end of the body 10. The monitoring device 80 includes a rider 81 and a camera 82.

The rider 81 is a telemetry device, as a laser image detecting and distance measuring instrument. The rider 81 is also referred to as a 'Laser Radar', and the measurement technique is similar to a radar. Instead of using radio waves, the radar 81 uses infrared rays.

The camera 82 includes a 2-D camera 82a disposed behind the measurement device 70 for measuring the landing altitude for precise landing and a video camera 82b for recording the surrounding situation And a gimbal 83 extending from the lower end of the body 10 and supporting the image camera 82b.

The monitoring device 80 monitors the surroundings of the UAV 100.

[0054] Describing the operation of the convertible wing type hybrid unmanned air vehicle 100 having the above configuration,

When the UAV 100 is operated, the lift generating unit 40 rotates. When the required number of revolutions per minute is reached, the UAV 100 ascends vertically. The propulsive force generating section 60 does not operate unless the maximum altitude is reached.

When the required flying height is reached, the main wing 20 is operated.

In an embodiment, as shown in FIG. 2, the outer wing portion 22 accommodated in the inner wing portion 21 is drawn out while sliding.

In another embodiment, as shown in FIG. 3, the inner wing portion 21 is folded on the lower portion thereof and rotated on the axial extension line with the inner wing portion 21.

The sliding method and the rotating method as described above can reduce the air resistance due to the external wind during the landing of the UAV 100, and the portable or storage space can be minimized so that the UAV 100 can be easily carried or stored.

If the vertical takeoff is completely performed, the propulsive force generating unit 60 is operated slowly, and the RPM of the lift generating unit 40 is reduced while gradually increasing the RPM.

In the UAV 100, the driving force generating unit 60 is driven in the vertical take-off and landing mode in which the lift generator 40 is driven and the flight altitude is controlled, thereby switching to a horizontal flight mode in which thrust for flight is provided. During the horizontal flight, only the thrust generating unit 60 is used and the power of the lift generating unit 40 is interrupted.

The directional elevating key 51 can reach the high speed due to the driving force generating unit 60 and can obtain high maneuverability and the direction elevating key 51 hinged to the tail wing unit 50 can control the moving direction of the UAV 100 have.

The aileron 23 hinged to the outer wing 22 can control the rolling moment of the UAV 100.

When the UAV 100 completes its mission, the thrust generating unit 60 is stopped again, and the lift generating unit 40 is operated to perform a vertical landing.

The lift generating unit 40 may solve the instability of the UAV 100 by using the direction elevating key 51.

The propulsive force generating unit 60 can control the directional lifting key 51 and the aileron 23 when horizontally flying so that the propulsive force generating unit 60 can lift the propelling force And can go out of the danger zone at the maximum speed and land vertically using the lift generation unit 40 again.

In addition, the lift generation unit 40 compensates for the loss of lift by regulating the rotational speed of the remaining elevating propellers even if one or more rising propellers are not operated.

In addition, a pitot tube, which is a speed measuring device 70 of the UAV 100, is provided at the front end of the body 10 to measure an atmospheric velocity of the UAV 100, And to obtain a safe access speed.

In addition, a monitoring device 80 is provided at the lower end of the body 10, so that it is possible to recapture the surroundings or record images or the like.

As described above, it is to be understood that the technical structure of the present invention can be embodied in other specific forms without departing from the spirit and essential characteristics of the present invention.

Therefore, it should be understood that the above-described embodiments are to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than the foregoing description, All changes or modifications that come within the scope of the equivalent concept are to be construed as being included within the scope of the present invention.

10. Body part 20. Main wing part
21. Inner wing 22. Outer wing
23. Aileron 30. Boom
31. Landing stand 40. Lift generator
50. Tail wing 51. Orient lift key
60. Propulsion generating part 70. Measuring device
80. Monitoring device 81. Rider
82. Camera 83. Gimbal

Claims (7)

A streamlined body part;
A pair of main wings extending from both sides of the body part;
A boom extending from the main wing portion forward and backward;
A lift generating unit provided on both ends of the boom, respectively, and selectively operated during vertical takeoff and landing flight;
A tail wing provided vertically to a rear end of the trunk for stable movement during navigation;
And an impulse generating unit provided at one side of the tail wing to provide a thrust during horizontal flight,
And a horizontal flight mode in which the propulsive force generating unit is driven and a thrust for flight is provided, is switched to a vertical takeoff and landing mode in which the lift altitude is controlled by the lift generating unit during operation, . The method according to claim 1,
Wherein the lift generator is constituted by a plurality of rising propellers,
Wherein when one of the elevating propellers is deactivated, the rotational speed of the remaining elevating propeller is adjusted to compensate for lift by the inoperating elevating propeller. The method according to claim 1,
Wherein the main wing portion includes an inner wing portion and an outer wing portion,
Wherein the outer wing portion is accommodated in the inner wing portion and is drawn out to the outside in a horizontal flight mode. The method according to claim 1,
Wherein the main wing portion includes an inner wing portion and an outer wing portion,
Wherein the outer wing portion is hinged to the boom and is folded at an upper portion or a lower portion of the inner wing portion and is rotated on an extension line of the inner wing portion in a horizontal flight mode to be unfolded. The method according to claim 1,
A direction elevating key hinged to the tail wing so as to vary the direction of movement of the UAV; And
Further comprising an aileron hinged to one side of the outer wing to control a rolling moment of the unmanned airplane. The method according to claim 1,
And a measuring device provided at a front end of the body part for measuring a speed of the UAV. The method according to claim 1,
And a monitoring device provided at a lower end of the body part and monitoring a circumstance of the wing type hybrid unmanned air vehicle.

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