KR101726652B1 - Blade for unmanned aerial vehicle - Google Patents

Blade for unmanned aerial vehicle Download PDF

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Publication number
KR101726652B1
KR101726652B1 KR1020150109055A KR20150109055A KR101726652B1 KR 101726652 B1 KR101726652 B1 KR 101726652B1 KR 1020150109055 A KR1020150109055 A KR 1020150109055A KR 20150109055 A KR20150109055 A KR 20150109055A KR 101726652 B1 KR101726652 B1 KR 101726652B1
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KR
South Korea
Prior art keywords
wing
unmanned aerial
hinge
fitting
aerial vehicle
Prior art date
Application number
KR1020150109055A
Other languages
Korean (ko)
Other versions
KR20170014961A (en
Inventor
천이진
Original Assignee
한국항공우주연구원
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Application filed by 한국항공우주연구원 filed Critical 한국항공우주연구원
Priority to KR1020150109055A priority Critical patent/KR101726652B1/en
Publication of KR20170014961A publication Critical patent/KR20170014961A/en
Application granted granted Critical
Publication of KR101726652B1 publication Critical patent/KR101726652B1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/28—Collapsible or foldable blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C2201/024—
    • B64C2201/102—
    • B64C2201/108—
    • B64C2700/628—

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

Abstract

It is a technical object of the present invention to provide a wing for a unmanned aerial vehicle which can minimize damage to wings and objects even when it hits an object. To this end, the wing for the unmanned aerial vehicle of the present invention comprises: a wing for a unmanned aerial vehicle rotated by a rotating shaft; a first wing portion coupled to the rotating shaft; A second wing portion connected to the first wing portion; And a hinge portion rotatably connecting the first and second wings.

Description

{Blade for unmanned aerial vehicle}

The present invention relates to a wing for an unmanned aerial vehicle.

Generally, an unmanned aerial vehicle, also called a "drone", is a helicopter-shaped unmanned airplane flying by induction of a radio wave without a person being driven, and is being used for surveillance, high-speed shooting, or logistics delivery.

1 is a perspective view schematically showing an existing unmanned aerial vehicle.

1, a conventional unmanned aerial vehicle includes a main body 10 mounted with a main board for controlling flight operations, a plurality of motors 20 whose rotational speed is controlled by the main board, Each of the support frames 30 branched in the radial direction in the main body portion 10 to support the support shaft 20 and each of the blades 40 which is coupled to the rotation axis of the plurality of motors 20 and exerts thrust . Therefore, each of the wings is rotated by the rotation of each motor, so that the unmanned aerial vehicle is driven by the driving force.

However, the conventional unmanned aerial vehicle has a problem that the wing 40 breaks when the rotating wing 40 hits an object. Particularly, when a cultural asset is hit in a cultural property while shooting in the air, there is a problem that not only the damage of the wing 40 but also the destruction of the cultural property, and further, the damage of the wing 40 is not smoothly controlled, There is a problem that leads to an accident.

Disclosure of Invention Technical Problem [8] The present invention provides a wing for a unmanned aerial vehicle capable of minimizing damage to wings and objects even when it hits an object.

According to an aspect of the present invention, there is provided a wing for an unmanned aerial vehicle, comprising: a wing for a unmanned aerial vehicle rotated by a rotation shaft; A second wing portion connected to the first wing portion; And a hinge portion rotatably connecting the first and second wings.

The first and second wing portions may be sequentially disposed in a radial direction of the rotation axis.

The hinge unit may include a hinge shaft disposed in parallel with the rotation axis.

The hinge unit may include a first stepped portion formed at an end of the first wing portion and having a first fitting groove and a first fitting protrusion; And a second stepped portion having a second fitting protrusion and a second fitting groove formed at an end portion of the second wing portion so as to be fitted to the first fitting groove and the first fitting protrusion, respectively.

Wherein the hinge axis is perpendicular to the first and second fitting protrusions, and an end surface of the first fitting protrusion has an arc shape centering on the hinge axis, and the end of the first fitting protrusion of the second fitting protrusion The surface facing the end surface may have an arc shape centering on the hinge axis.

In addition, the end surface of the second fitting protrusion has an arc shape centering on the hinge axis, and a surface of the first fitting protrusion, which faces the end surface of the second fitting protrusion, has a circular arc shape centered on the hinge axis Lt; / RTI >

For example, the wing for the unmanned aerial vehicle according to the above-described embodiment of the present invention may be provided with two teeth at intervals of 180 degrees on the rotating shaft.

As another example, the wing for the unmanned aerial vehicle according to the above-described embodiment of the present invention may be provided with four wings at intervals of 90 degrees on the rotating shaft.

As described above, the wing for the unmanned aerial vehicle according to the embodiment of the present invention can have the following effects.

According to the embodiment of the present invention, since the technical configuration including the first wing portion, the second wing portion, and the hinge portion is provided, the second wing portion can be expanded by the centrifugal force during the flight, The second wing portion is rotated and folded by the hinge portion, so that damage to the wing or the object can be minimized. Further, the second wing portion can be folded through the hinge portion, so that storage can be facilitated.

1 is a perspective view schematically showing an existing unmanned aerial vehicle.
2 is a perspective view schematically illustrating a state where a wing for an unmanned aerial vehicle according to an embodiment of the present invention is coupled to a rotating shaft.
FIG. 3 is a cross-sectional view of the wing of FIG. 2 taken along line III-III.
4 is a plan view of the wing for unmanned aerial vehicle of FIG. 2 viewed from above.
5 is a view schematically showing a state in which a wing collapses when an object hits it.
6 is a perspective view schematically showing a state where a wing for an unmanned aerial vehicle according to another embodiment of the present invention is coupled to a rotating shaft.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings, which will be readily apparent to those skilled in the art to which the present invention pertains. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

FIG. 2 is a perspective view schematically showing a state where a wing for an unmanned aerial vehicle according to an embodiment of the present invention is coupled to a rotation shaft, and FIG. 3 is a sectional view taken along line III-III of FIG.

FIG. 4 is a plan view of the wing for unmanned aerial vehicle of FIG. 2 viewed from above, and FIG. 5 is a view schematically illustrating a state where wings are folded when an object hits the wing.

2 to 5, the wing 100 for a unmanned aerial vehicle according to an embodiment of the present invention is a wing for a unmanned aerial vehicle rotated by a rotating shaft 1 and includes a first wing 110 and a second wing 110, A second wing portion 120, and a hinge portion 130. As shown in Fig. Hereinafter, each component will be described in detail with reference to Figs. 2 to 5. Fig.

2, the first wing portion 110 is coupled to the rotating shaft 1, and the second wing portion 120 is coupled to the first wing portion 110. As shown in FIG. In particular, the first and second wings 110 and 120 may be sequentially disposed in any radial direction of the rotating shaft 1, as shown in FIG.

Further, as shown in FIG. 2, the third, fourth, and fifth wings 140, 150, and 160 may be further included in consideration of the length of the wings of the present invention. In this case, the third, fourth, and fifth wing portions 140, 150, and 160 may be sequentially disposed in the radial direction of the rotating shaft 1 successively to the second wing portion 120.

The hinge unit 130 rotatably connects the first and second wings 110 and 120, as shown in FIGS. In particular, the hinge unit 130 may include a hinge shaft 131 disposed in parallel with the rotation axis 1. [ Therefore, as shown in FIGS. 4 and 5, when the wings of the present invention are viewed in the axial direction of the rotary shaft 1, that is, when the wings of the present invention are viewed from above, The second, third, fourth and fifth wing parts 120, 140, 150 and 160 can be smoothly folded with respect to the respective hinge shafts 131 when the first, second, third,

In addition, the hinge portion 130 may further include a first step portion 132 and a second step portion 133, as shown in FIGS. The first stepped portion 132 may be formed at an end of the first wing portion 110 and may have a first fitting groove 132b and a first fitting protrusion 132a, A second fitting protrusion 133a and a second fitting groove 133b formed at an end portion of the second wing portion 120 so as to be fitted to the first fitting protrusion 132b and the first fitting protrusion 132a, respectively .

Accordingly, the first and second wing parts 110 and 120 are inserted into the first and second wing parts 110 and 120 through the first and second step parts 132 and 133, It is possible to prevent the first and second wing parts 110 and 120 from being bent in the vertical direction with respect to each other.

Further, the hinge shaft 131 is provided perpendicularly to the first and second fitting protrusions 132a and 133a, and the end surface of the first fitting protrusion 132a has an arc shape centered on the hinge shaft 131 The surface of the second fitting groove 133b opposed to the end surface of the first fitting protrusion 132a may have an arc shape centering on the hinge shaft 131. [ Accordingly, while the first and second wing parts 110 and 120 are rotated about the hinge shaft 131, smooth rotation can be performed through the arc-shaped structure, and the first and second wings 110 and 120 can be smoothly rotated, It is possible to sufficiently support the first and second wings 110 and 120 in the vertical direction and to prevent the first and second wings 110 and 120 from being bent upward and downward with respect to each other.

In addition, while the first and second wing parts 110 and 120 are rotated about the hinge shaft 131, smooth rotation is performed and the first and second wing parts 110 and 120 are rotated up and down The end face of the second fitting protrusion 133a also has an arc shape centering on the hinge shaft 131 so as to sufficiently support the swinging motion in the first fitting groove 132b, The surface opposed to the end surface of the fitting projection 133a may have an arc shape centered on the hinge shaft 131. [

As shown in FIGS. 2 and 4, the wing 100 for an unmanned aerial vehicle according to an embodiment of the present invention may be provided with two rotation axis 1 at intervals of 180 degrees.

Hereinafter, referring to FIG. 6, a wing 200 for a manless vehicle according to another embodiment of the present invention will be described in detail.

6 is a perspective view schematically showing a state where a wing for an unmanned aerial vehicle according to another embodiment of the present invention is coupled to a rotating shaft.

The wing 200 for an unmanned aerial vehicle according to another embodiment of the present invention is the same as the above-described embodiment of the present invention except that four wings 200 are provided on the rotating shaft 1 at intervals of 90 degrees.

As described above, the wing 100 (200) for an unmanned aerial vehicle according to the embodiments of the present invention can have the following effects.

According to the embodiments of the present invention, since the technical constitution including the first wing part 110, the second wing part 120, and the hinge part 130 is provided, The wing portion 120 can be expanded to fly and the second wing portion 120 is rotated and folded by the hinge portion 130 even if the wing collides with the object during the flight so that damage to the wing or the object can be minimized . When the situation where the wing collides is terminated, the second wing part 120 is expanded by the centrifugal force again, and the flight can be possible. Further, the second wing portion 120 can be folded through the hinge portion 130, so that storage can be facilitated.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed exemplary embodiments, Of the right.

100, 200: wing for unmanned aerial vehicle 110: first wing
120: second wing part 130: hinge part
131: Hinge shaft 132: First step
132a: first fitting projection 132b: first fitting groove
133: second step 133a: first fitting projection
133b: second fitting groove 140: third wing portion
150: fourth wing portion 160: fifth wing portion
P: object

Claims (8)

delete delete delete A wing for a unmanned aerial vehicle rotated by a rotary shaft,
A first wing portion coupled to the rotation shaft;
A second wing portion connected to the first wing portion; And
And a hinge portion for rotatably connecting the first and second wings
Lt; / RTI >
Wherein the first and second wing portions are sequentially disposed in a radial direction of the rotation shaft,
The hinge unit includes:
And a hinge shaft disposed parallel to the rotation axis,
The hinge unit includes:
A first stepped portion formed at an end of the first wing portion and having a first fitting groove and a first fitting protrusion; And
A second fitting protrusion formed at an end portion of the second wing portion so as to be fitted into the first fitting groove and the first fitting protrusion, and a second step protrusion having a second fitting groove,
Further comprising
Wings for unmanned aerial vehicles. 5. The method of claim 4,
Wherein the hinge shaft is provided in the first and second fitting projections,
Wherein an end surface of the first fitting projection has an arc shape centering on the hinge axis,
Wherein a surface of the second fitting groove facing the end surface of the first fitting projection has an arc shape centered on the hinge axis
Wings for unmanned aerial vehicles. The method of claim 5,
Wherein an end surface of the second fitting projection has an arc shape centering on the hinge axis,
Wherein a surface of the first fitting groove facing the end surface of the second fitting projection has an arc shape centered on the hinge axis
Wings for unmanned aerial vehicles. delete delete
KR1020150109055A 2015-07-31 2015-07-31 Blade for unmanned aerial vehicle KR101726652B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020150109055A KR101726652B1 (en) 2015-07-31 2015-07-31 Blade for unmanned aerial vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020150109055A KR101726652B1 (en) 2015-07-31 2015-07-31 Blade for unmanned aerial vehicle

Publications (2)

Publication Number Publication Date
KR20170014961A KR20170014961A (en) 2017-02-08
KR101726652B1 true KR101726652B1 (en) 2017-04-13

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11661177B2 (en) 2020-07-23 2023-05-30 Wing Aviation Llc Fold-out propeller tip extensions

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107891968B (en) * 2017-12-19 2024-06-07 深圳市道通智能航空技术股份有限公司 Folding screw, power component and unmanned aerial vehicle
CN113232853B (en) * 2021-04-02 2022-11-04 陈�峰 Short-distance take-off and landing aircraft

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101067017B1 (en) * 2009-04-08 2011-09-22 건국대학교 산학협력단 Rotor blade for rotorcraft to change sweep-back angle of the blade tip actively

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11661177B2 (en) 2020-07-23 2023-05-30 Wing Aviation Llc Fold-out propeller tip extensions

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