Aircraft

Abstract

The present invention relates to an aircraft in which the speed of the aircraft is adjusted to a high speed or a low speed by moving wings up and down, the aircraft comprising: a flight body (3); a control unit (5) provided on one side of the interior of the flight body (3); the first hydraulic pressure generating part (17) is arranged on one side of the interior of the flying main body (3) and is electrically connected with the control part (5) so as to generate hydraulic pressure according to a control signal of the control part (5); a second hydraulic pressure generation unit (19) that is provided on one side of the interior of the flight body (3) so as to face the first hydraulic pressure generation unit (17) at a prescribed distance, is electrically connected to the control unit (5), and generates hydraulic pressure on the basis of a control signal from the control unit (5); a first protective tube (21) provided on one side of the outer surface of the flight body (3) so as to be spaced apart from the first support part (9) by a predetermined distance; a second protective tube (23) provided on one side of the outer surface of the flight body (3) so as to be spaced apart from the first protective tube (21) by a predetermined distance and so as to face the first protective tube (21); a first slide bar (25) provided inside the first protective tube (21) so as to be capable of sliding up and down and connected to a first hydraulic pressure generation unit (17) so as to move up and down according to the hydraulic pressure of the first hydraulic pressure generation unit (17); a second slide bar (27) provided inside the second protective tube (23) so as to be capable of sliding up and down and connected to a second hydraulic pressure generation unit (19) so as to move up and down according to the hydraulic pressure of the second hydraulic pressure generation unit (19); and a third rotating part (29) rotatably provided on one side or the like of the first slide bar (25).

Description

TECHNICAL FIELD

[0001] The present application relates to an aircraft, and more particularly, to an aircraft capable of adjusting the speed of the aircraft to a high speed or a low speed by moving a wing up and down. BACKGROUND

[0002] An unmanned aerial vehicle (UAV) refers to an aircraft or a helicopter-type aircraft that can be flown and controlled by a pilot through wireless radio waves without a pilot.

[0003] The unmanned aerial vehicle can be classified into a fixed wing (Fixed Wing) type equipped with flat plate wings on both sides of the unmanned aerial vehicle body like an airplane, and a rotary wing (Rotary Wing) type equipped with a plurality of rotors around the unmanned aerial vehicle body like a helicopter.

[0004] The fixed wing unmanned aerial vehicle adopts a conventional airplane shape, and the wings thereof are fixed to generate lift by flat plate wings provided on both sides, and can obtain propulsion power to fly by the power of an electric motor or an engine.

[0005] The fixed wing unmanned aerial vehicle requires lift to maintain flight. The lift can be provided when the fixed wing unmanned aerial vehicle flies at a speed exceeding a predetermined speed (i.e., a stall speed).

[0006] In addition, in order to achieve stable flight, the fixed wing unmanned aerial vehicle includes a horizontal tail and a vertical tail in addition to a main wing.

[0007] On the other hand, the fixed wing unmanned aerial vehicle has a problem in that it cannot take off vertically.

[0008] To solve this problem, an unmanned aerial vehicle applying a plurality of rotors to an upper portion of a fixed wing unmanned aerial vehicle to enable vertical takeoff and landing is disclosed.

[0009] The unmanned aerial vehicle enabling vertical takeoff and landing using the plurality of rotors enables hovering and direction conversion by adjusting the rotation direction and rotation speed of the plurality of rotors.

[0010] In the vertical takeoff and landing, if a crosswind is applied to the vertical tail, the fixed wing unmanned aerial vehicle vibrates in a yaw direction, thereby causing a problem in that flight stability is degraded.

[0011] In addition, such an unmanned aerial vehicle flies using the plurality of rotors when the flight speed is in a range below the stall speed, and does not start the plurality of rotors and flies relying on the lift of the fixed wing when the speed increases to a flight speed above the stall speed.

[0012] To solve the problem, an application was filed with the Korean Intellectual Property Office on December 31, 2020, with Application No. 10-2020-0188982 (Invention Title: Unmanned Aerial Vehicle), referring to the corresponding Figure 1 And looking at the claims, specifically: "An unmanned aerial vehicle, comprising: an unmanned aerial vehicle body; a main wing configured at a front end of the unmanned aerial vehicle body to generate lift; a horizontal tail wing configured at a rear end of the unmanned aerial vehicle body to provide longitudinal balance and stability; a vertical tail wing configured at the rear end of the unmanned aerial vehicle body to provide lateral balance and stability; a propulsion part installed at the unmanned aerial vehicle body to provide a propulsion force for propelling the unmanned aerial vehicle body forward; a rotor part installed at the unmanned aerial vehicle body or the main wing; a propeller part driven to rotate by the rotor part; a control part for controlling the actions of the rotor part and the propulsion part; a first sensor part for measuring the flight speed of the unmanned aerial vehicle body; a first alarm part for displaying the flight state of the unmanned aerial vehicle body controlled by the control part based on the flight speed measured by the first sensor part; and an attitude stabilization rotor part configured on one side of the vertical tail wing of the unmanned aerial vehicle body and for reducing rotation of the unmanned aerial vehicle body due to external wind, and the rotor part comprises: first to fourth unit motors installed at the body and configured at four corners of a virtual quadrilateral in order; and first to fourth propellers installed at the first to fourth unit motors."

[0013] As described above, aerial vehicles are currently in a continuous research and development stage.

[0014] The present applicant aims to propose an aerial vehicle capable of adjusting the speed of the aerial vehicle to high speed or low speed by moving the wing part up and down in addition to the above-mentioned unmanned aerial vehicle. SUMMARY

[0015] Problems to be Solved by the Invention

[0016] Therefore, the present invention is an improvement invention to solve the many problems existing in the above-mentioned prior art, and the purpose of the present invention is to provide an aerial vehicle capable of adjusting the speed of the aerial vehicle to high speed or low speed by moving the wing part up and down.

[0017] However, the purpose of the present invention is not limited to the purpose mentioned in the above-mentioned content, and those skilled in the art will be able to clearly understand other purposes not mentioned by the following description.

[0018] Means for Solving the Problem

[0019] To achieve the above-mentioned purpose, the aerial vehicle according to the present invention comprises:

[0020] a flight body 3;

[0021] The control unit 5 is disposed on the inner side of the flight body 3.

[0022] The first support unit 9 is protrusively disposed on the front upper surface of the flight body 3.

[0023] The second support unit 11 is protrusively disposed on the front upper surface of the flight body 3 in a manner spaced apart from the first support unit 9 by a predetermined distance and in an opposite manner.

[0024] The first rotation unit 13 is rotatably disposed on the side of the first support unit 9.

[0025] The second rotation unit 15 is rotatably disposed on the side of the second support unit 11.

[0026] The aerial vehicle further includes:

[0027] The communication unit 7 is disposed on the inner side of the flight body 3 in a manner spaced apart from the control unit 5 by a predetermined distance and is electrically connected to the control unit 5.

[0028] The first hydraulic pressure generating unit 17 is disposed on the inner side of the flight body 3 in a manner spaced apart from the second rotation unit 15 by a predetermined distance and is electrically connected to the control unit 5, to generate hydraulic pressure according to a control signal of the control unit 5.

[0029] The second hydraulic pressure generating unit 19 is disposed on the inner side of the flight body 3 in a manner spaced apart from the first hydraulic pressure generating unit 17 by a predetermined distance and in an opposite manner and is electrically connected to the control unit 5, to generate hydraulic pressure according to a control signal of the control unit 5.

[0030] The first protection tube 21 is disposed on the outer surface of the flight body 3 in a manner spaced apart from the first support unit 9 by a predetermined distance.

[0031] The second protection tube 23 is disposed on the outer surface of the flight body 3 in a manner spaced apart from the first protection tube 21 by a predetermined distance and in an opposite manner to the first protection tube 21.

[0032] The first sliding rod 25 is disposed inside the first protection tube 21 in a manner capable of sliding up and down and is connected to the first hydraulic pressure generating unit 17, to move up and down according to the hydraulic pressure of the first hydraulic pressure generating unit 17.

[0033] The second sliding rod 27 is disposed inside the second protection tube 23 in a manner capable of sliding up and down and is connected to the second hydraulic pressure generating unit 19, to move up and down according to the hydraulic pressure of the second hydraulic pressure generating unit 19.

[0034] The third rotation unit 29 is rotatably disposed on the side of the first sliding rod 25.

[0035] A fourth rotating portion 31 is rotatably provided on one side of the second sliding rod 27.

[0036] A wing portion 33 is provided on the first rotating portion 13, the second rotating portion 15, the third rotating portion 29, and the fourth rotating portion 31 to adjust the speed of the aircraft according to the upward and downward movement of the third rotating portion 29 and the fourth rotating portion 31.

[0037] Inventive Effects

[0038] As described above, the aircraft according to the present application has the effect of adjusting the speed of the aircraft to be high or low by moving the wing portion upward and downward.

[0039] Thus, the present application has the effect of providing convenience for the user. BRIEF DESCRIPTION OF DRAWINGS

[0040] Figure 1 FIG. 1 is a diagram illustrating an unmanned aircraft according to the related art.

[0041] Figure 2 FIG. 1 is a diagram illustrating an unmanned aircraft according to the related art.

[0042] Figure 3 FIG. 1 is a diagram illustrating an unmanned aircraft according to the related art. Figure 2

[0043] Figure 4 FIG. 1 is a diagram illustrating an unmanned aircraft according to the related art. Figure 2

[0044] Figure 5a FIG. 1 is a diagram illustrating an unmanned aircraft according to the related art. Figure 5b Figure 2 FIG. 1 is a diagram illustrating an unmanned aircraft according to the related art.

[0045] Explanation of Reference Numerals

[0046] 1: Aircraft

[0047] 3: Flight body

[0048] 5: Control portion

[0049] 7: Communication portion

[0050] 9: First support portion

[0051] 11: Second support portion

[0052] 13: First rotating portion

[0053] 15: Second rotating portion

[0054] 17: First hydraulic pressure generating portion

[0055] 19: Second hydraulic pressure generating portion​​​

[0056] 21: first protection tube

[0057] 23: second protection tube

[0058] 25: first sliding rod

[0059] 27: second sliding rod

[0060] 29: third rotating part

[0061] 31: fourth rotating part

[0062] 33: wing part DETAILED DESCRIPTION

[0063] Hereinafter, a preferred embodiment of the aerial vehicle according to the present application will be described.

[0064] Further, in explaining the present application, when it is determined that a detailed explanation of a related well-known function or configuration can obscure the gist of the present application, a detailed explanation thereof will be omitted.

[0065] Figure 2 is a view showing an aerial vehicle according to the present application, Figure 3 is a view schematically showing Figure 2 a configuration of the aerial vehicle, Figure 4 is an exploded view of a key part of the aerial vehicle. Figure 2 As shown in

[0066] , the aerial vehicle 1 according to the present application includes: Figures 2 to 4 a flight body 3;

[0067] a control part 5 provided at an inner side of the flight body 3;

[0068] a communication part 7 provided at an inner side of the flight body 3 at a prescribed distance from the control part 5 and electrically connected to the control part 5;

[0069] a first support part 9 protrusively provided at one side of an upper front surface of the flight body 3;

[0070] a second support part 11 protrusively provided at one side of the upper front surface of the flight body 3 at a prescribed distance from and opposite to the first support part 9;

[0071] a first rotating part 13 rotatably provided at one side of the first support part 9;

[0072] a second rotating part 15 rotatably provided at one side of the second support part 11;

[0073]

[0074] ​A first hydraulic pressure generating portion 17 is disposed at an inner side of the flight body 3 at a predetermined distance apart from the second rotating portion 15 and is electrically connected to the control portion 5 to generate hydraulic pressure according to a control signal of the control portion 5;

[0075] A second hydraulic pressure generating portion 19 is disposed at an inner side of the flight body 3 at a predetermined distance apart from and opposite to the first hydraulic pressure generating portion 17 and is electrically connected to the control portion 5 to generate hydraulic pressure according to a control signal of the control portion 5;

[0076] A first protection tube 21 is disposed at an outer surface of the flight body 3 at a predetermined distance apart from the first support portion 9;

[0077] A second protection tube 23 is disposed at an outer surface of the flight body 3 at a predetermined distance apart from and opposite to the first protection tube 21;

[0078] A first sliding rod 25 is disposed inside the first protection tube 21 to be slidable up and down and is connected to the first hydraulic pressure generating portion 17 to move up and down according to hydraulic pressure of the first hydraulic pressure generating portion 17;

[0079] A second sliding rod 27 is disposed inside the second protection tube 23 to be slidable up and down and is connected to the second hydraulic pressure generating portion 19 to move up and down according to hydraulic pressure of the second hydraulic pressure generating portion 19;

[0080] A third rotating portion 29 is rotatably disposed at one side of the first sliding rod 25;

[0081] A fourth rotating portion 31 is rotatably disposed at one side of the second sliding rod 27;

[0082] A wing portion 33 is disposed at the first rotating portion 13, the second rotating portion 15, the third rotating portion 29, and the fourth rotating portion 31 to move up and down according to rotation of the third rotating portion 29 and the fourth rotating portion 31 to adjust a speed of the aircraft.

[0083] Hereinafter, a general manufacturing process of the aircraft 1 according to the present application including the above configuration will be described.

[0084] Herein, the general manufacturing process of the aircraft 1 according to the present application can be arbitrarily changed according to a manufacturer.

[0085] First, after the flight body 3 is positioned, the control portion 5 is disposed at an inner side of the flight body 3.

[0086] Next, after the communication portion 7 is disposed at an inner side of the flight body 3 at a predetermined distance apart from the control portion 5, the communication portion 7 is electrically connected to the control portion 5.

[0087] Next, the first support part 9 is protrusively arranged on one side of the upper surface of the front of the flight main body 3, and then the second support part 11 is protrusively arranged on one side of the upper surface of the front of the flight main body 3 at a distance apart from and opposite to the first support part 9.

[0088] Next, the first rotation part 13 is rotatably arranged on one side of the first support part 9, and then the second rotation part 15 is rotatably arranged on one side of the second support part 11.

[0089] Next, the first hydraulic pressure generating part 17 is arranged on the inner side of the flight main body 3 at a distance apart from the second rotation part 15, and then the first hydraulic pressure generating part 17 is electrically connected to the control part 5.

[0090] The first hydraulic pressure generating part 17 generates hydraulic pressure according to the control signal of the control part 5.

[0091] Next, the second hydraulic pressure generating part 19 is arranged on the inner side of the flight main body 3 at a distance apart from and opposite to the first hydraulic pressure generating part 17, and then the second hydraulic pressure generating part 19 is electrically connected to the control part 5.

[0092] The second hydraulic pressure generating part 19 generates hydraulic pressure according to the control signal of the control part 5.

[0093] Next, the first protection pipe 21 is arranged on one side of the outer surface of the flight main body 3 at a distance apart from the first support part 9, and then the second protection pipe 23 is arranged on one side of the outer surface of the flight main body 3 at a distance apart from and opposite to the first protection pipe 21.

[0094] Next, the first sliding rod 25 is arranged inside the first protection pipe 21 to be able to slide up and down, and the first sliding rod 25 is connected to the first hydraulic pressure generating part 17.

[0095] The first sliding rod 25 moves up and down along the inside of the first protection pipe 21 according to the hydraulic pressure of the first hydraulic pressure generating part 17.

[0096] Next, the second sliding rod 27 is arranged inside the second protection pipe 23 to be able to slide up and down, and the second sliding rod 27 is connected to the second hydraulic pressure generating part 19.

[0097] The second sliding rod 27 moves up and down along the inside of the second protection pipe 23 according to the hydraulic pressure of the second hydraulic pressure generating part 19.

[0098] Next, a third rotating portion 29 is rotatably provided to one side of the first sliding rod 25, and a fourth rotating portion 31 is rotatably provided to one side of the second sliding rod 27.

[0099] Next, a wing portion 33 is provided to the first rotating portion 13, the second rotating portion 15, the third rotating portion 29, and the fourth rotating portion 31.

[0100] The wing portion 33 moves up and down according to the rotation of the third rotating portion 29 and the fourth rotating portion 31, so as to adjust the speed of the aircraft to high speed or low speed.

[0101] The operation of the aircraft 1 manufactured as described above will be described as follows.

[0102] When the aircraft 1 needs to fly at high speed, an intelligent terminal (not shown) sends a high-speed flight instruction signal to the communication portion 7. At this time, the communication portion 7 receives the high-speed flight instruction signal and sends the received high-speed flight instruction signal to the control portion 5.

[0103] Next, the control portion 5 sends a control signal to the first hydraulic pressure generating portion 17 and the second hydraulic pressure generating portion 19.

[0104] The first hydraulic pressure generating portion 17 generates hydraulic pressure according to the control signal of the control portion 5. At this time, due to the generated hydraulic pressure, the first sliding rod 25 slides to the upper side along the inside of the first protection pipe 21.

[0105] The second hydraulic pressure generating portion 19 generates hydraulic pressure according to the control signal of the control portion 5. At this time, due to the generated hydraulic pressure, the second sliding rod 27 slides to the upper side along the inside of the second protection pipe 23.

[0106] As described above, when the first sliding rod 25 and the second sliding rod 27 slide to the upper side, the third rotating portion 29 rotatably provided to one side of the first sliding rod 25 rotates in the clockwise direction while pushing the rear portion of the wing portion 33 to the upper side, and the fourth rotating portion 31 rotatably provided to one side of the second sliding rod 27 rotates in the clockwise direction while pushing the rear portion of the wing portion 33 to the upper side. At this time, the first rotating portion 13 and the second rotating portion 15 rotate in the clockwise direction, and with the rotation of the first rotating portion 13 and the second rotating portion 15, the front portion of the wing portion 33 descends to the lower side.

[0107] As described above Figure 5b When the rear portion of the wing portion 33 ascends to the upper side and the front portion of the wing portion 33 descends to the lower side, the aircraft 1 will fly at high speed.

[0108] When the aircraft 1 needs to fly at low speed, the intelligent terminal (not shown in the figure) sends a low-speed flight instruction signal to the communication unit 7. At this time, the communication unit 7 receives the low-speed flight instruction signal and sends the received low-speed flight instruction signal to the control unit 5.

[0109] Next, the control unit 5 sends a control signal to the first hydraulic pressure generating unit 17 and the second hydraulic pressure generating unit 19.

[0110] The first hydraulic pressure generating unit 17 releases the generated hydraulic pressure according to the control signal of the control unit 5. At this time, due to the release of the hydraulic pressure, the first sliding rod 25 slides downward along the inside of the first protection pipe 21.

[0111] The second hydraulic pressure generating unit 19 releases the hydraulic pressure according to the control signal of the control unit 5. At this time, due to the release of the hydraulic pressure, the second sliding rod 27 slides downward along the inside of the second protection pipe 23.

[0112] As described above, when the first sliding rod 25 and the second sliding rod 27 slide downward, the third rotating unit 29 rotatably provided on one side of the first sliding rod 25 rotates in the counterclockwise direction while pulling the rear part of the wing part 33 downward, and the fourth rotating unit 31 rotatably provided on one side of the second sliding rod 27 rotates in the counterclockwise direction while pulling the rear part of the wing part 33 downward. At this time, the first rotating unit 13 and the second rotating unit 15 will rotate in the counterclockwise direction, and with the rotation of the first rotating unit 13 and the second rotating unit 15, the front part of the wing part 33 will rise upward.

[0113] As described above Figure 5a When the rear part of the wing part 33 descends downward and the front part of the wing part 33 rises upward, the aircraft 1 will fly at low speed.

[0114] Therefore, the present application adjusts the speed of the aircraft to high speed or low speed by moving the wing part up and down.

[0115] The detailed description of the present application is only an exemplary description of the present application, and is only used to illustrate the invention, and is not used to limit the meaning or limit the scope of the present application recited in the claims.

[0116] Therefore, it can be understood by those skilled in the art that various modifications and other equivalent embodiments can be made. Therefore, the true technical protection scope of the present application should be based on the technical idea of the appended claims.

Claims

1. An aircraft comprising: The aerial vehicle is characterized by further comprising: a communication unit (7) disposed on an inner side of the aerial body (3) at a predetermined distance from the control unit (5) and electrically connected to the control unit (5), a first hydraulic pressure generating unit (17) disposed on an inner side of the aerial body (3) at a predetermined distance from the second rotating unit (15) and electrically connected to the control unit (5) to generate hydraulic pressure according to a control signal of the control unit (5), a second hydraulic pressure generating unit (19) disposed on an inner side of the aerial body (3) at a predetermined distance from the first hydraulic pressure generating unit (17) and electrically connected to the control unit (5) to generate hydraulic pressure according to a control signal of the control unit (5), a first protection pipe (21) disposed on an outer side of the aerial body (3) at a predetermined distance from the first support unit (9), a second protection pipe (23) disposed on an outer side of the aerial body (3) at a predetermined distance from the first protection pipe (21) and opposite to the first protection pipe (21), a first sliding rod (25) slidably disposed in the first protection pipe (21) and connected to the first hydraulic pressure generating unit (17) to move up and down according to hydraulic pressure of the first hydraulic pressure generating unit (17), a second sliding rod (27) slidably disposed in the second protection pipe (23) and connected to the second hydraulic pressure generating unit (19) to move up and down according to hydraulic pressure of the second hydraulic pressure generating unit (19), a third rotating unit (29) rotatably disposed on a side of the first sliding rod (25), a fourth rotating unit (31) rotatably disposed on a side of the second sliding rod (27), and a wing unit (33) disposed on the first rotating unit (13), the second rotating unit (15), the third rotating unit (29), and the fourth rotating unit (31) to adjust a speed of the aerial vehicle according to up-and-down movement of the third rotating unit (29) and the fourth rotating unit (31). ​

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