KR101804489B1 - Backward movement possible flight vehicle equipped fixed wing - Google Patents
Backward movement possible flight vehicle equipped fixed wing Download PDFInfo
- Publication number
- KR101804489B1 KR101804489B1 KR1020160026069A KR20160026069A KR101804489B1 KR 101804489 B1 KR101804489 B1 KR 101804489B1 KR 1020160026069 A KR1020160026069 A KR 1020160026069A KR 20160026069 A KR20160026069 A KR 20160026069A KR 101804489 B1 KR101804489 B1 KR 101804489B1
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- KR
- South Korea
- Prior art keywords
- wing
- mode
- main body
- flight
- fixed
- Prior art date
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
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- 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
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.
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
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
3, the
3, the
The first rotating
That is, the first
The fixed blade is a name including both the
In order to achieve the mechanical stability of the fixed-wing aircraft in consideration of the length and shape of the
As described above, the fixed wings of the fixed-wing flight body are respectively fitted to the first
The
In addition, the
A
The method in which the
That is, the
A
At this time, in the method in which the
That is, the
The reason why the
The
However, the direction of rotation of the
As the
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
The present invention is characterized in that the
The
Therefore, it is preferable that the
In the conventional mode, the
Therefore, it is preferable that the
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
The first
The first and second
At this time, the angle between the angle of the
In addition, the
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
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
The center of gravity of the fixed-wing flight body in the conventional mode is located at one side of the wing-
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
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
4 (b) is an exemplary view showing a state in which the
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 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 control unit,
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; Respectively,
By increasing the thrust during flight in one direction or increasing the angle of attack by adjusting the angle of the wing portion 120, the engine is stopped in a state of 45 ° to 90 ° from the ground after the sudden rise , The thrust suddenly decreases, and after switching from the conventional mode to the canadic mode or from the canadic mode to the conventional mode at the time of stopping in the air, descending along the abruptly ascended section, And the direction can be changed to another direction.
The long blade portion 120 and the short blade portion 140,
Wherein the wing is a symmetric wing.
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).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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KR1020160026069A KR101804489B1 (en) | 2016-03-04 | 2016-03-04 | Backward movement possible flight vehicle equipped fixed wing |
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Application Number | Priority Date | Filing Date | Title |
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KR1020160026069A KR101804489B1 (en) | 2016-03-04 | 2016-03-04 | Backward movement possible flight vehicle equipped fixed wing |
Publications (2)
Publication Number | Publication Date |
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KR20170103344A KR20170103344A (en) | 2017-09-13 |
KR101804489B1 true KR101804489B1 (en) | 2017-12-04 |
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KR1020160026069A KR101804489B1 (en) | 2016-03-04 | 2016-03-04 | Backward movement possible flight vehicle equipped fixed wing |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20240039989A (en) | 2022-09-16 | 2024-03-27 | 노동신 | Airship having direction switching function |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20220083134A (en) | 2020-12-11 | 2022-06-20 | 장건우 | Laptop water cooling cooler pad |
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 |
CN113665306B (en) * | 2021-10-25 | 2022-01-04 | 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 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100230547A1 (en) * | 2008-09-05 | 2010-09-16 | The Government Of The Us, 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 |
-
2016
- 2016-03-04 KR KR1020160026069A patent/KR101804489B1/en active IP Right Grant
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100230547A1 (en) * | 2008-09-05 | 2010-09-16 | The Government Of The Us, 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 (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20240039989A (en) | 2022-09-16 | 2024-03-27 | 노동신 | Airship having direction switching function |
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KR20170103344A (en) | 2017-09-13 |
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