KR101790556B1 - Propeller for unmanned aeriar vehicle - Google Patents

Propeller for unmanned aeriar vehicle Download PDF

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Publication number
KR101790556B1
KR101790556B1 KR1020150189495A KR20150189495A KR101790556B1 KR 101790556 B1 KR101790556 B1 KR 101790556B1 KR 1020150189495 A KR1020150189495 A KR 1020150189495A KR 20150189495 A KR20150189495 A KR 20150189495A KR 101790556 B1 KR101790556 B1 KR 101790556B1
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KR
South Korea
Prior art keywords
blade
radial position
twist angle
cord length
propeller
Prior art date
Application number
KR1020150189495A
Other languages
Korean (ko)
Other versions
KR20170079194A (en
Inventor
강희정
위성용
김덕관
Original Assignee
한국항공우주연구원
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Priority to KR1020150189495A priority Critical patent/KR101790556B1/en
Publication of KR20170079194A publication Critical patent/KR20170079194A/en
Application granted granted Critical
Publication of KR101790556B1 publication Critical patent/KR101790556B1/en

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    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • 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
    • 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
    • B64C2201/108—
    • B64C2700/6283—

Abstract

The present invention relates to a propeller for an unmanned aerial vehicle, comprising: a propeller for a UAV, comprising three blades, wherein the blade has a cord length (r / R) of 0.14 to 0.29 r / C is increased and the cord length C of the blade is reduced at a radial position (r / R) of 0.29 to 1.0r / R of the blade.

Description

PROPELLER FOR UNMANNED AERIAR VEHICLE [0002]

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

Unmanned Aerial Vehicle (UAV) means an airplane capable of flying, by remote control or by autonomous flight control device, without pilot, to measure, search, and take pictures of reconnaissance, surveillance, weather, etc. .

Especially, in order to acquire high resolution image data in a desired area, an unmanned airplane is taken in the sky to take an image of a relevant area, and acquisition of image data using an unmanned airplane is performed by a military related organization, a disaster prevention organization, It is widely used in business organizations, traffic situation organizations, forest fire monitoring organizations, and special organizations for crime prediction and tracking.

The main performance of such an unmanned aerial vehicle can be determined by the performance efficiency of the propeller, the efficiency of the motor, and the capacity of the battery.

Among them, the propeller is a device that generates thrust and maneuvering force for the flight of the UAV through rotation, and is one of the key components for determining the performance of the UAV.

In particular, the performance efficiency of the propeller can be determined by the thrust and the drag, and it is important to minimize the drag to improve the efficiency of the propeller.

Accordingly, there is a demand for development of a propeller capable of improving the performance of an unmanned aerial vehicle.

Accordingly, an object of the present invention is to provide a propeller for an unmanned airplane capable of improving the stopping flight efficiency of an unmanned airplane and reducing the required power.

In order to accomplish the above object, the present invention provides a propeller for an unmanned aerial vehicle including three blades, wherein the blade has a cord length C (r / R) of 0.14 to 0.29 r / ) Is increased and the cord length (C) of the blade is reduced at a radial position (r / R) of 0.29 to 1.0r / R of the blade.

As described above, the propeller for an unmanned aerial vehicle according to the embodiment of the present invention is formed so as to optimize the twist angle and the cord length with respect to the blade length up to the radius, thereby improving the stopping flight efficiency of the UAV and reducing the required power have.

1 is a perspective view of a propeller for an unmanned aerial vehicle according to an embodiment of the present invention;
2 is a cross-sectional view of a propeller for an unmanned aerial vehicle according to an embodiment of the present invention.
FIGS. 3A and 3B are graphs comparing performance of the present invention with the performance of a conventional unmanned aerial vehicle using a propeller.

Hereinafter, specific embodiments of the present invention will be described with reference to the drawings. It is to be understood, however, that the specific structural and functional descriptions are only for purposes of illustrating the embodiments of the invention, and that the embodiments of the invention may be practiced in various forms and are not intended to be limited to the embodiments described herein , All changes, equivalents, and alternatives falling within the spirit and scope of the present invention.

In the following description, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear.

FIG. 1 is a perspective view of a propeller for an unmanned aerial vehicle according to an embodiment of the present invention, and FIG. 2 is a cross-sectional view of a propeller for an unmanned aerial vehicle according to an embodiment of the present invention.

1 and 2, the propeller 100 for an unmanned aerial vehicle according to an embodiment of the present invention may be provided with three blades 110. However, the present invention is not limited thereto, and the number of blades 110 may be changed.

1 and 2, R denotes a radius of the blade, r / R denotes an arbitrary radial position of the blade, c denotes a cord length of a straight line connecting the leading and trailing edges of the blade, Can be expressed.

Accordingly, the radial position of the blade 110 is 1.0r / R, which corresponds to the blade tip position. At this time, the radius R of the blade 110 may be 235 mm.

The blade 110 has a length 110 of the blade 110 at a radial position r / R of 0.14 to 0.29 r / R and a length c of the blade 110 at a radial position r / R of 0.29 to 1.0 r / May be formed so as to be reduced.

At this time, the blade 110 increases the cord length c of the blade 110 from 0.044 m to 0.058 m at a radial position (r / R) of 0.14 to 0.29 r / R, / R) 0.29 to 1.0 r / R, the cord length c of the blade 110 is reduced from 0.058 m to 0.014 m.

Specifically, the blade 110 has a cord length c of 0.044 m at a radial position r / R of 0.14 r / R, and a radial position r / R of the blade 110, The cord length c of the blade 110 can be gradually increased until the radial position r / R reaches 0.29 r / R along the radial direction at 0.14 r / R. At this time, the cord length c of the blade 110 at the radial position (r / R) of 0.29r / R of the blade 110 may be 0.058m.

Further, until the radial position (r / R) along the radial direction at the radial position (r / R) 0.29r / R of the blade 110 reaches 1.0r / R, that is, the end of the blade 110, (C) of the first electrode 110 may be reduced. At this time, the cord length c of the blade 110 at the end of the blade 110 may be 0.014 m.

On the other hand, the twist angle t of the blade 110 is increased at the radial position (r / R) of 0.14 to 0.29 r / R and the blade 110 is rotated at the radial position r / R of 0.29 to 1.0 r / The twist angle (t) of the light guide plate 110 can be made small.

At this time, the twist angle t of the blade 110 is increased from 15.7 ° to 29.8 ° at a radial position (r / R) of 0.14 to 0.29r / R, the radius position r / The twist angle t of the blade 110 at 1.0r / R can be formed to be reduced from 29.8 ° to 7.8 °.

Specifically, the blade 110 has a twist angle t of 15.7 degrees at a radial position r / R of 0.14 r / R, and a radial position r / R of the blade 110, The twist angle t of the blade 110 gradually increases until the radial position r / R reaches 0.29 r / R along the radial direction at 0.14 r / R. At this time, the twist angle (t) of the blade 110 at the radial position (r / R) of 0.29r / R of the blade 110 may be 29.8 °.

Further, until the radial position (r / R) along the radial direction at the radial position (r / R) 0.29r / R of the blade 110 reaches 1.0r / R, that is, the end of the blade 110, The torsional angle (t) of the torsion coil spring 110 may be reduced. At this time, the twist angle t of the blade 110 at the end of the blade 110 may be 7.8 °.

At this time, the code length C and the twist angle t for each of the radial positions of the blade 110 can be formed as shown in Table 1 below.

Radial position (r / R) Code length (C) The twist angle (t) 0.14r / R 0.044m 15.7 [deg.] 0.23r / R 0.056m 27.5 DEG 0.29r / R 0.058m 29.8 [deg.] 0.50r / R 0.044m 20.6 [deg.] 0.77r / R 0.030m 15.3 [deg.] 0.94r / R 0.027 m 10 ° 1.0r / R 0.014 m 7.8 °

Accordingly, the blade 110 has a maximum cord length C and a maximum twist angle t at a radial position r / R = 0.29r / R and a minimum Can be formed in a wire form having a cord length (C) and a minimum twist angle (t).

FIGS. 3A and 3B are graphs comparing the performance of an unmanned aerial vehicle using a propeller for a conventional unmanned aerial vehicle according to the present invention.

Here, the conventional blades of the propeller for unmanned aerial vehicles have a cord length (C) and a twist angle (t) per radial position (r / R) as shown in Table 2 below. The blade of the propeller may have a cord length (C) and a twist angle (t) according to the radial position (r / R) as shown in Table 1 above.
Radial position (r / R) Code length (C) The twist angle (t) 0.27r / R 0.038m 28.2 [deg.] 0.40r / R 0.041 m 25.7 [deg.] 0.52r / R 0.040 m 22 ° 0.65r / R 0.038m 18.1 DEG 0.78r / R 0.032m 14.9 [deg.] 0.90r / R 0.022m 12.7 [deg.] 1.0r / R 0m 14 °

As can be seen from FIG. 3A, the unmanned airplane using the propeller for unmanned airplane according to the embodiment of the present invention has a stopping flight efficiency of 0.5 to 5,000 RPM in the range of 2000 to 6000 RPM, compared with the conventional unmanned airplane using the unmanned airplane propeller. 0.7, while the present invention is improved by more than 15% from 0.7 to 0.8.

As can be seen from FIG. 3B, the unmanned airplane using the propeller for unmanned airplane according to the embodiment of the present invention, compared to the unmanned airplane in which the conventional unmanned airplane propeller is applied, 100 to 800 W is required, whereas the present invention requires 100 to 700 W, so that the required power is reduced by about 100 W.

As described above, the propeller 100 for an unmanned aerial vehicle according to the embodiment of the present invention has a cord length (r / R) at an arbitrary radial position (r / R) of the blade 110 with respect to the radial length R of the blade 110 c and the twist angle t are configured and optimized as described above, the stopping flight efficiency of the UAV can be improved and the required power can be reduced.

Reference throughout this specification to " one embodiment ", etc. of the principles of the invention, and the like, as well as various modifications of such expression, are intended to be within the spirit and scope of the appended claims, it means. Thus, the appearances of the phrase " in one embodiment " and any other variation disclosed throughout this specification are not necessarily all referring to the same embodiment.

It will be understood that the term " connected " or " connecting ", and the like, as used in the present specification are intended to include either direct connection with other components or indirect connection with other components. In addition, the singular forms herein include plural forms unless the context clearly dictates otherwise. Also, components, steps, operations, and elements referred to in the specification as " comprises " or " comprising " refer to the presence or addition of one or more other components, steps, operations, elements, and / or devices.

The present invention has been described with reference to the preferred embodiments. It is to be understood that all embodiments and conditional statements disclosed herein are intended to assist the reader in understanding the principles and concepts of the present invention to those skilled in the art, It will be understood that the invention may be embodied in various other forms without departing from the spirit or essential characteristics thereof. Therefore, the disclosed embodiments should be considered in an illustrative rather than a restrictive sense. The scope of the present invention is defined by the appended claims rather than by the foregoing description, and all differences within the scope of equivalents thereof should be construed as being included in the present invention.

100: Propeller
110: blade

Claims (7)

A propeller for a UAV, comprising three blades,
The blade length C of the blade is gradually increased in a region where the radial position r / R of the blade is 0.29 r / R at 0.14 r / R, and the radial position r / R of the blade is 0.29 the code length (C) of the blade gradually decreases in a period of 1.0 r / R in r / R,
The torsion angle t of the blade gradually increases in a section where the radial position r / R of the blade is 0.29 r / R at 0.14 r / R and the radial position r / R of the blade is 0.29 r / R The torsional angle (t) of the blade is gradually reduced in a period of 1.0 r /
Wherein the blade has a maximum cord length (C) and a maximum twist angle (t) at a radial position (r / R) of the blade of 0.29 r / R and a radial position (r / R) / RTI > is formed in a wired form having a minimum cord length (C) and a minimum twist angle (t) at a location of the wind tunnel.
delete delete The method according to claim 1,
The blade gradually increases in cord length (C) of the blade (110) from 0.044 m to 0.058 m in a section where the radial position (r / R) of the blade is 0.29 r / R at 0.14 r / R, Wherein the cord length of the blade (110) is gradually reduced from 0.058 m to 0.014 m in a region where the radial position (r / R) is 0.29 r / R to 1.0 r / R.
The method according to claim 1,
The blade gradually increases in the twist angle t of the blade 110 from 15.7 DEG to 29.8 DEG in a region where the radial position r / R of the blade is 0.29 r / R at 0.14 r / R, Wherein the twist angle (t) of the blade (110) is gradually reduced from 29.8 ° to 7.8 ° in a section where the radial position (r / R) is 0.29r / R to 1.0r / R.
The method according to claim 1,
Wherein the radius (R) of the blade is 235 mm.
The method according to claim 1,
The blade
The cord length C is 0.044 m and the twist angle t is 15.7 degrees at the radial position r / R of 0.14 r / R,
The cord length C is 0.056 m and the twist angle t is 27.5 DEG at a position where the radial position r / R is 0.23r / R,
The cord length C is 0.058 m and the twist angle t is 29.8 degrees at the position where the radial position r / R is 0.29 r / R,
The cord length C is 0.044 m and the twist angle t is 20.6 deg. At the position where the radial position r / R is 0.50 r / R,
The cord length C is 0.030 m and the twist angle t is 15.3 deg. At the position where the radial position r / R is 0.77 r / R,
The cord length C is 0.027 m and the twist angle t is 10 DEG at a position where the radial position r / R is 0.94r / R,
A propeller for unmanned aerial vehicles having a cord length (C) of 0.014 m and a torsion angle (t) of 7.8 ° at a radial position (r / R) of 1r / R.
KR1020150189495A 2015-12-30 2015-12-30 Propeller for unmanned aeriar vehicle KR101790556B1 (en)

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KR101790556B1 true KR101790556B1 (en) 2017-10-26

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Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102015601B1 (en) * 2017-10-25 2019-08-28 한국항공우주연구원 Blade for quad-tilt rotor unmanned aerial vehicles
KR102338703B1 (en) * 2021-07-26 2021-12-13 한국전력기술 주식회사 Propeller for drone

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070110582A1 (en) * 2005-05-31 2007-05-17 Sikorsky Aircraft Corporation Rotor blade twist distribution for a high speed rotary-wing aircraft

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070110582A1 (en) * 2005-05-31 2007-05-17 Sikorsky Aircraft Corporation Rotor blade twist distribution for a high speed rotary-wing aircraft

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