KR20170103344A - Backward movement possible flight vehicle equipped fixed wing - Google Patents

Backward movement possible flight vehicle equipped fixed wing Download PDF

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Publication number
KR20170103344A
KR20170103344A KR1020160026069A KR20160026069A KR20170103344A KR 20170103344 A KR20170103344 A KR 20170103344A KR 1020160026069 A KR1020160026069 A KR 1020160026069A KR 20160026069 A KR20160026069 A KR 20160026069A KR 20170103344 A KR20170103344 A KR 20170103344A
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KR
South Korea
Prior art keywords
wing
fixed
main body
mode
flight
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KR1020160026069A
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Korean (ko)
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KR101804489B1 (en
Inventor
남명우
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유콘시스템 주식회사
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Priority to KR1020160026069A priority Critical patent/KR101804489B1/en
Publication of KR20170103344A publication Critical patent/KR20170103344A/en
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Publication of KR101804489B1 publication Critical patent/KR101804489B1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C37/00—Convertible aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/12—Canard-type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/02—Tailplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/10—Stabilising surfaces adjustable

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a fixed-wing aircraft in which a shape and a flight direction of a flying object are switched by rapidly raising a moving body by rotating an angle of the wing during flight and then rotating the wing.
The backward-travelable flying object according to the present invention includes a body portion constituting a body of a flying body, a wing portion which is engaged with a first rotation shaft protruding in one direction and the other direction of the body portion and a first wing portion, And a second wing portion that is coupled to the second rotation shaft so as to be rotatable.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001]

More particularly, the present invention relates to a fixed-wing aircraft capable of instantly changing the direction and shape of a flight during flight, and more particularly, To a fixed-wing aircraft.

In general, a fixed-wing aircraft refers to a passenger who has fixed wings on a fuselage, an airplane for transporting cargo, or a fighter aircraft, and refers to an entire airplane other than a flywheel represented by a helicopter.

These fixed-wing aircraft are more suitable for long-haul flights because they have less energy consumption and faster flying speeds than flywheel aircraft, but unlike flywheel aircraft that can perform vertical takeoff and landing, immediate turning and fixed flight, the runway for takeoff and landing There is a disadvantage in that it requires a wide turning radius when turning and turning, and it is not possible to fly fixedly.

As an invention relating to a fixed-wing aircraft for solving such a problem, a "unmanned aerial vehicle" of Korean Patent Laid-Open Publication No. 10-2013-0005501 has been proposed and disclosed.

In Korean Unexamined Patent Publication No. 10-2013-0005501, an unmanned aerial vehicle capable of vertical takeoff and landing, stopping flight, cruise and turning flight is provided with a single flywheel and a fixed wing.

However, the above conventional technique solves the problem of vertical takeoff and landing and fixed flight. However, since the flywheel is used only in the vertical takeoff and landing mode and the flywheel is used in the cruise mode, I hold the problem.

Therefore, there is a demand for a fixed-wing aircraft which does not require a wide turning radius during flight and can change the direction immediately.

Korean Patent Publication No. 10-2013-0005501 (Jan. 01, 2013)

The present invention is directed to solve the problems of the prior art as described above,

A conventional flying object equipped with a fixed wing can not be reversed, and a problem that a wide turning radius is required for switching the flight direction has arisen. Therefore, the object of the present invention is to provide a solution to this problem.

In order to realize the above-mentioned object, according to the present invention,

A main body constituting a body of the air vehicle; A long-waved portion that is coupled to the first rotation shaft so as to be rotatable so as to protrude in one direction and the other direction of the main body; And a second wing portion which is spaced apart from the first rotation shaft and is coupled to the second rotation shaft so as to be rotatable in one direction and the other direction of the main body, so as to be rotatable.

In the backward-travelable vehicle according to the present invention,

It is possible to instantly change the direction of flight by rotating the long and short wings while raising the body by adjusting the angles of the wings and / or the wings during flight.

1 is an external perspective view showing a case where a backward-capable flight body according to the present invention is in a conventional mode.
FIG. 2 is an external perspective view of a canard mode in which a backward flightable vehicle according to the present invention is in a canard mode; FIG.
FIG. 3 is a view illustrating positions of a first rotation shaft and a second rotation shaft, which are engaged with a wing portion of a flightable object according to the present invention;
FIGS. 4 (a) to 4 (b) are flowcharts showing a manner in which a backward-capable flight body according to the present invention is switched from a conventional mode to a canard mode.

The present invention relates to an aircraft capable of instantaneous switching of a flight direction and a shape during flight,

A main body 100 constituting a body of a flying body; A long-wing portion 120 fastened to the first rotation shaft 110 so as to be rotatable protruding from one side and the other side of the main body 100; A cutout 140 which is separated from the first rotation shaft 110 and is rotatably coupled to a second rotation shaft 130 protruding from one side and the other side of the main body 100; To a backward-travelable vehicle.

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

First, as shown in FIGS. 1 and 2, a backward flightable object according to the present invention includes a main body 100 constituting a body of a flying object.

3, the main body 100 is provided with a first rotation axis 110 protruding in one direction and the other direction, and the first rotation axis 110 is protruded in one direction and the other direction, respectively. The first rotation axis 110 may pass through the main body 100 or each of the first rotation axes 110 may penetrate or be coupled to the main body 100, And protrudes in one direction and in the other direction.

3, the main body 100 is provided with a second rotation shaft 130 protruding in one direction and the other direction, respectively. The second rotation axis 130 protrudes in one direction and the other direction The second rotary shaft 130 may pass through the main body 100 or may be connected to the main body 100 through the second rotary shaft 130. [ 100, respectively.

 The first rotating shaft 110 and the second rotating shaft 130 are spaced apart from each other and the first rotating shaft 110 and the second rotating shaft 130 are connected to one side and the other side of the main body 100 The first rotating shaft 110 and the second rotating shaft 130 may pass through the main body 100 or may be fastened to the main body 100 at different heights .

That is, the first rotary shaft 110 and the second rotary shaft 130 are constituent elements in which the fixed wings of the fixed-wing flight body are inserted, respectively. Considering the size and shape of the fixed wings, The first rotary shaft 110 and the second rotary shaft 130 are disposed on one side and the other side of the main body 100, The direction of protrusion should be the same.

The fixed blade is a name including both the blade 120 and the blade 140 of the reversible flywheel according to the present invention.

In order to achieve the mechanical stability of the fixed-wing aircraft in consideration of the length and shape of the main body 100 and the distance between the first rotation shaft 110 and the second rotation shaft 130, The height of the position at which the first rotary shaft 110 and the second rotary shaft 130 pass through the main body 100 can be adjusted.

As described above, the fixed wings of the fixed-wing flight body are respectively fitted to the first rotary shaft 110 and the second rotary shaft 130. The first rotary shaft 110 is provided with a wing- (120) is fitted in the second rotary shaft (130), and a cutout (140) corresponding to a tail of a general air vehicle is fitted to the second rotary shaft (130).

The wing portion 120 is not an integral shape of a single object but is a generic name of two fixed wings having a shape symmetrical with respect to the body portion 100. The wing wing 120 has a square wing, , A triangular profile, a recessive profile, and the like.

In addition, the cutout 140 is not an integral shape of a single object but is a name collectively denoting two fixed wings having a shape symmetrical with respect to the main body 100, The shape may be configured differently from the shape of the wing portion 120. However, since the function realized by the shape of the wing portion 120 and the shape of the cutout portion 140 is configured to have the same shape It would be desirable.

A first fitting hole 115 into which the first rotation shaft 110 is fitted is formed on one side of the main wing 120 contacting the main body 100 and a second fitting hole 115 is formed in the first wing portion 110, 120 are fitted, the wing 120 is not separated from the first rotary shaft 110 but is rotatable about the first rotary shaft 110.

The method in which the wing 120 is rotated about the first rotary shaft 110 is a method in which the position of the wing 120 before rotation and the position of the wing 120 after rotation are the same And is configured so as not to rotate.

That is, the first fitting hole 115 is not located in the center of the one side of the main wing 120 facing the main body 100, or is biased to one side So that the wing 120 moves on the first rotation axis 110 as it rotates.

A second fitting hole 135 in which the second rotating shaft 130 is fitted is formed at one side of the cutout 140 contacting the main body 100. The second fitting hole 135 is formed in the second rotating shaft 130, The step 140 is not separated from the second rotation shaft 130 but is rotatable about the second rotation axis 130. In other words,

At this time, in the method in which the cutout 140 is rotated about the second rotation axis 130, the position of the cutout 120 before rotation and the position of the cutout 120 after rotation are changed It is a fixed rotation method.

That is, the second fitting hole 135 is formed in the center of one side surface of the cutout 140 facing the main body 100 or facing the main body 100, So that the position is fixed even if the second rotary shaft 130 is rotated about the axis.

The reason why the blade 120 rotates about the first rotating shaft 110 and the rotating shaft 140 rotates about the second rotating shaft 130 will be described below.

The wing 120 and the wing 140 are components that generate lifting force during flight of the wing-wing flight. It is desirable that the functions implemented due to the shape are formed in the same shape so that they do not conflict with each other, It must be rotated at the same time.

However, the direction of rotation of the blade 120 and the rotation axis 140 may be the same or different from each other.

As the wing 120 rotates about the first rotation axis 110 and the rotation axis 140 rotates about the second rotation axis 130, It is possible to switch to the canadic mode in which the tip 140 is positioned on the front surface of the blade 120 in the conventional mode in which the blade 120 is positioned on the front surface of the blade 140. [

The present invention is also applicable to the case where the present invention is applied to a case where the present invention is applied to the present invention It is clear that the backward-capable air vehicle can be switched back from the canned mode to the conventional mode.

When the windshield 120 is positioned on the front surface of the stem 140 or the stem 140 is positioned on the front surface of the stem 120, Direction.

The present invention is characterized in that the wing portion 120 moves and rotates without being fixedly rotated about the first rotating shaft 110 and the rotating portion 140 rotates about the second rotating shaft 130, And a canard mode in which the tip 140 is positioned on the front surface of the blade 120 in a conventional mode in which the wind-up unit 120 is positioned on the front surface of the blade 140, This is possible.

The main blade portion 120 in the conventional mode is disposed at a middle portion of the main body portion 100 to perform a main blade function. The main blade portion 120 in the canard mode, however, Lt; RTI ID = 0.0 > 100 < / RTI > to perform the role of the main wing.

Therefore, it is preferable that the blade 120 is moved and rotated about the first rotating shaft 110 as an axis.

In the conventional mode, the cutout 140 is positioned at the distal end of the main body 100 to serve as a tail wing. In the canned mode, The position of the main wing may be changed according to the mode of the main wing.

Therefore, it is preferable that the cutout 140 is fixedly rotated about the second rotation shaft 130. [

1 and 2 are merely examples of the reversible flywheel flight according to the present invention. In the limit of flight of the flywheel flywheel, the longwing portion 120 is rotated by the first rotation axis 110 Or the rotary shaft 140 may be rotated around the second rotary shaft 130. [0064]

The first fitting hole 115 may be in contact with the main body 100 or may be in contact with the main body 100 when the main shaft part 120 rotates about the first rotating shaft 110. [ The second fitting hole 135 is formed in the center of one side of the main wing 120 and when the first turning portion 140 moves around the second rotating shaft 130, (120) of the main body part (100) facing the main body part (100), or is not positioned in the center of one side surface of the main body part (120).

The first and second rotary shafts 110 and 140 are rotated in the first and second rotary shafts 110 and 140 according to the changeover from the conventional mode to the canadic mode or the canal mode to the conventional mode, And the upper end of the wing portion 120 and the lower end portion 140 are changed in position to the lower end by the rotation of the rotary shaft 130. The rotation of the wing portion 120 and the end portion 140 are changed in position to the upper end.

At this time, the angle between the angle of the windshield 120 and the angle of the windshield 120 before rotation and the angle of the windshield 120 and the windshield 140 after rotation are equal to each other, The rotation angle of the blade 140 is preferably 180 degrees.

In addition, the wing 120 and the cutout 140 are configured to have the same shape before and after rotation so as to be symmetrically winged so that the wing functions in the conventional mode and the canard mode are implemented in the same manner.

The wing of the airplane raises the airplane by generating lift, and the center of gravity of the airplane tries to descend the airplane by the action of gravity.

When the lift and the center of gravity are formed at different points, the upward force and the downward force are not canceled but generate a rotational force to rotate the flight body and balance each other.

Therefore, if the center of gravity is formed near the wing of the aircraft where the lift is generated, the upward force and the downward force are largely offset from each other and no rotational force for rotating the flight body occurs.

For this reason, it is preferable that the center of gravity of the backward-travelable vehicle according to the present invention, which is the conventional mode and the canard mode, is formed in the vicinity of the point where the wing portion 120 is fastened to both sides.

As shown in FIGS. 1 and 2, the shape of the fixed-wing flight body in the conventional mode is a shape in which a part of the main body 100 protrudes in front of the wing-like portion 120, The shape of the fixed-wing flight body is such that a part of the main body 100 does not protrude from the rear end of the wing-

The center of gravity of the fixed-wing flight body in the conventional mode is located at one side of the wing-wing portion 120, and the center of gravity of the fixed- Wherein the center of gravity of the fixed-wing flight in the canard mode is formed in front of the propulsion prop (150), and the center of gravity of the air- The center of gravity of the flying object in the mode of FIG.

 Hereinafter, an embodiment in which the reversible flywheel according to the present invention is switched from the conventional mode to the canard mode will be described in detail with reference to the accompanying drawings.

First, it is assumed that the reversible flywheel according to the present invention is in a flight state in the conventional mode.

4 (a), the thrust of the fixed-wing aircraft is further increased or the angle of the wing portion 120 is adjusted to increase the angle of attack, so that the lift force is increased, .

Thereafter, when the engine of the fixed-wing air vehicle, which rises sharply and forms an angle of 45 ° to 90 ° with the ground, is stopped, a thrust suddenly decreases and a point is temporarily stopped in the air just before the stall.

When the fixed-wing flight body is temporarily stopped, the wing portion 120 is rotated and rotated about the first rotation axis 110, and the cut-away portion 140 is fixedly rotated about the second rotation axis 130, The wicket vehicle is switched from the conventional mode to the canard mode.

4 (b) is an exemplary view showing a state in which the winder 120 and the winder 140 of the fixed-wing aircraft are rotated. FIG. 4 (c) is a view illustrating the winder 120 and the winder 140 is completed and is switched from the conventional mode to the canadic mode.

4 (d), when the engine of the fixed-wing air vehicle, which has been switched to the canard mode, is driven again, the fixed-wing air vehicle descends along the rapidly rising section in the previous conventional mode, And the flight state is maintained again.

With such a configuration, the fixed-wing flight body can change its direction to the opposite direction, which is the extreme opposite direction during flight in one direction.

The embodiments described above are provided by way of example for the purpose of enabling a person skilled in the art to sufficiently transfer the technical idea of the present invention to a person skilled in the art, But may be embodied in other forms without limitation.

In order to clearly explain the present invention, parts not related to the description are omitted from the drawings, and in the drawings, the width, length, thickness, etc. of the components may be exaggerated or reduced for convenience.

Further, like reference numerals designate like elements throughout the specification.

100: main body 110: first rotating shaft
115: first fitting hole 120:
130: second rotation shaft 135: second fitting hole
140: Short sprocket 150: Prop Prop

Claims (5)

A main body 100 constituting a body of a flying body;
A long-wing portion 120 fastened to the first rotation shaft 110 so as to be rotatable protruding from one side and the other side of the main body 100;
A cutout 140 which is separated from the first rotation axis 110 and is rotatably coupled to a second rotation axis 130 protruding from one side and the other side of the main body; And a second fixed-wing-wing aircraft.
The method according to claim 1,
The long blade portion 120 and the short blade portion 140,
Wherein the wing is a symmetric wing.
The method according to claim 1,
The winder 120 is moved and rotated around the first rotating shaft 110,
Wherein the step portion (140) is fixedly rotated about the second rotation axis (130).
The method according to claim 1,
The fixed-
A conventional mode in which the blade 120 is positioned on the front surface of the cutout 140; And
A canard mode in which the cutout 140 is positioned on the front surface of the wing 120; Wherein the movable member is capable of being switched to the fixed wing.
5. The method of claim 4,
In the conventional mode, the center of gravity of the fixed-wing flight body is formed at the rear of the prop shaft 150 provided at one side of the wing-like portion 120,
Wherein the center of gravity of the fixed-wing flight body in the canard mode is formed in front of the propulsion prop (150).
KR1020160026069A 2016-03-04 2016-03-04 Backward movement possible flight vehicle equipped fixed wing KR101804489B1 (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112606997A (en) * 2020-12-29 2021-04-06 北京北航天宇长鹰无人机科技有限公司 Unmanned cargo airplane of tailless overall arrangement
CN113665306A (en) * 2021-10-25 2021-11-19 中国空气动力研究与发展中心空天技术研究所 Cross-medium aircraft water-air dual-purpose empennage
KR20220083134A (en) 2020-12-11 2022-06-20 장건우 Laptop water cooling cooler pad

Families Citing this family (1)

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Publication number Priority date Publication date Assignee Title
KR20240039989A (en) 2022-09-16 2024-03-27 노동신 Airship having direction switching function

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8070090B2 (en) * 2008-09-05 2011-12-06 The United States Of America As Represented By The Secretary Of The Navy Stop-rotor rotary wing aircraft
JP2010254264A (en) * 2009-04-24 2010-11-11 Kenta Yasuda Unmanned aircraft landing and departing perpendicularly by tilt wing mechanism
JP2012111475A (en) 2010-11-28 2012-06-14 Kenta Yasuda Vertical takeoff and landing unmanned aircraft by wing-rotor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20220083134A (en) 2020-12-11 2022-06-20 장건우 Laptop water cooling cooler pad
CN112606997A (en) * 2020-12-29 2021-04-06 北京北航天宇长鹰无人机科技有限公司 Unmanned cargo airplane of tailless overall arrangement
CN112606997B (en) * 2020-12-29 2021-10-22 北京北航天宇长鹰无人机科技有限公司 Unmanned cargo airplane of tailless overall arrangement
CN113665306A (en) * 2021-10-25 2021-11-19 中国空气动力研究与发展中心空天技术研究所 Cross-medium aircraft water-air dual-purpose empennage

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