CN217673174U

CN217673174U - Variable-pitch propeller for unmanned aerial vehicle

Info

Publication number: CN217673174U
Application number: CN202221986534.2U
Authority: CN
Inventors: 周丹; 黄友; 陆国敬; 张文; 周军
Original assignee: Chongqing Zongshen Aircraft Engine Manufacturing Co ltd
Current assignee: Chongqing Zongshen Aviation Engine Manufacturing Co.,Ltd.
Priority date: 2022-07-29
Filing date: 2022-07-29
Publication date: 2022-10-28
Anticipated expiration: 2032-07-29

Abstract

The utility model relates to a propeller, in particular to a pitch-variable propeller for an unmanned aerial vehicle, which comprises a blade body formed by sequentially and smoothly transiting fourteen airfoil sections distributed along the length direction of the blade, wherein the chord length c of the airfoil section is 134 mm-57 mm; taking the first airfoil section of the root of the blade body as a reference, and setting the distances r from the rest airfoil sections to the first airfoil section of the root of the blade body to be 48 mm-624 mm; taking a plane A defined by a chord length line of a first airfoil section positioned at the root of the blade body and a rotation center line of the blade body as a reference, and forming an included angle beta between the chord length line of the other airfoil sections and the plane A at 3.3-21.8 degrees; the distance from the front edge of each airfoil section to the rotation center of the blade body is 38-42% of the chord length. This scheme has solved when the small and medium-size unmanned aerial vehicle screw diameter is 1.92 meters magnitude of a matter in the prior art, take-off distance is short and the high altitude problem of cruising inefficiency for a long time.

Description

Variable-pitch propeller for unmanned aerial vehicle

Technical Field

The utility model relates to a screw specifically is a displacement screw for unmanned aerial vehicle.

Background

At present, propellers with 100KW level power are mainly used for small manned airplanes, and the flying altitude of the propellers is lower. The propellers applied to the small-sized fixed wing unmanned aerial vehicle with the flying height of 10 ㎞ are few. In order to meet the requirements of small unmanned aerial vehicles on high altitude and long cruising, a propeller matched with the 100KW level is necessary to be designed.

For example, when the diameter of a propeller of a small-sized fixed-wing unmanned aerial vehicle is required to be 1.92 meters, how to ensure the short-distance takeoff and high-altitude long-time cruise of the small-sized fixed-wing unmanned aerial vehicle becomes a problem which needs to be solved urgently.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a displacement screw for unmanned aerial vehicle to solve the problem that the screw of the middle-size and small-size fixed wing unmanned aerial vehicle of prior art can't realize that the short distance takes off and high altitude is cruised for a long time when the diameter requires to be 1.92 meters volume level.

In order to achieve the above object, the present invention provides a pitch-variable propeller for unmanned aerial vehicles, which comprises a blade body formed by sequentially and smoothly transitioning fourteen airfoil sections distributed along the length direction of the blade, wherein the chord length of the airfoil section is c; taking the first airfoil section of the root of the blade body as a reference, and taking the distance from the rest airfoil sections to the first airfoil section of the root of the blade body as r; taking a plane A defined by a chord length line of a first airfoil section positioned at the root of the blade body and a rotation center line of the blade body as a reference, and forming included angles beta between chord length lines of other airfoil sections and the plane A; the distance from the front edge of each airfoil section to the rotation center of the blade body is 38% -42% of the chord length; the parameters for each airfoil section are shown in the following table: the serial numbers of the airfoil section from the root to the tip of the blade body are sequentially from 1 to 14,

further, the distance from the first airfoil section of the root of the blade body to the rotation axis of the propeller is 336 mm.

Further, the shape of the blade body is in a low-speed needle shape, and the tip of the blade body is straight and has sweepback.

Further, the paddle bodies are three, and the included angle between every two adjacent paddle bodies is 120 degrees.

Further, the thickness of the blade body is gradually reduced from the root to the tip.

The beneficial effect of this scheme lies in: by adopting the arrangement, when the diameter of the propeller is required to be 1.92 meters, the requirement of short take-off distance of the small-sized fixed-wing unmanned aerial vehicle is realized, and meanwhile, the requirement of the unmanned aerial vehicle during high-altitude long-endurance flight can be met.

Drawings

Fig. 1 is a schematic view of an embodiment of a variable pitch propeller for an unmanned aerial vehicle according to the present invention;

FIG. 2 is a schematic structural view of the blade body of FIG. 1;

FIG. 3 is a schematic view of one of the airfoil sections of FIG. 2.

Detailed Description

The following is further detailed by way of specific embodiments:

reference numerals in the drawings of the specification include: root 1, airfoil section 2, leading edge 3, trailing edge 4, tip 5.

The embodiment is basically as shown in the attached figures 1 to 3: the utility model provides a variable pitch propeller for unmanned aerial vehicle, includes the paddle body, and in this embodiment, the paddle body is provided with threely to the contained angle between the adjacent paddle body is 120. The blade body is formed by sequentially and smoothly transitioning fourteen airfoil sections 2 distributed along the length direction of the blade, and the thickness of the blade body is gradually reduced from a root part 1 to a blade tip 5. The chord length of the airfoil section 2 is c; taking the first airfoil section of the root 1 of the blade body as a reference, and taking the distance from the rest airfoil sections to the first airfoil section of the root of the blade body as r; taking a plane A defined by a chord length line of a first airfoil section positioned at the root of the blade body and a rotation center line of the blade body as a reference, and forming included angles beta between chord length lines of other airfoil sections and the plane A; the distance from the leading edge of each airfoil section to the rotation center of the blade body is 38% -42% of the chord length, the preferred embodiment is 40%, and of course, 38%, 42% and the like can be selected; the parameters for each airfoil section are shown in the following table: the serial numbers of the airfoil section from the root to the tip of the blade body are sequentially from 1 to 14,

in this embodiment, the distance from the first airfoil section at the root of the blade body to the axis of rotation of the propeller is 336 mm. In this embodiment, the blade body is low-speed needle-shaped in appearance, and the tip of the blade body is straight and has sweepback.

This scheme of adoption, when the diameter requirement of screw is under the prerequisite of 1.92 meters magnitude of force, the thrust that makes the screw produce is bigger to satisfy the requirement that small-size fixed wing unmanned aerial vehicle take-off distance is short, simultaneously, can satisfy the efficiency requirement of unmanned aerial vehicle high altitude long endurance again.

The above description is only an example of the present invention, and the common general knowledge of the known specific structures and characteristics of the embodiments is not described herein. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent.

Claims

1. The utility model provides a variable pitch propeller for unmanned aerial vehicle which characterized in that: the blade comprises a blade body formed by sequentially and smoothly transitioning fourteen airfoil sections distributed along the length direction of the blade, wherein the chord length of each airfoil section is c; taking the first airfoil section of the root of the blade body as a reference, and taking the distances from the rest airfoil sections to the first airfoil section of the root of the blade body as r; taking a plane A defined by a chord length line of a first airfoil section positioned at the root of the blade body and a rotation center line of the blade body as a reference, and forming included angles beta between chord length lines of other airfoil sections and the plane A; the distance from the front edge of each airfoil section to the rotation center of the blade body is 38-42% of the chord length; the parameters of each airfoil section are as follows: the serial numbers of the airfoil section from the root to the tip of the blade body are sequentially from 1 to 14,

section number 1: r is 0 mm, C is 134 mm, and beta is 0 degree;

section number 2: r is 48 mm, C is 132 mm, β is 3.3 degrees;

section number 3: r is 96 mm, C is 130.5 mm, β is 6 degrees;

section number 4: r is 144 mm, C is 129 mm, β is 8.2 degrees;

section No. 5: r is 192 mm, C is 126.8 mm, β is 10.2 degrees;

section number 6: r is 240 mm, C is 124.1 mm, β is 11.8 degrees;

section number 7: r is 288 mm, C is 120.9 mm, beta is 13.1 degrees;

section number 8: r is 336 mm, C is 116.8 mm, and β is 14.6 degrees;

section number 9: r is 384 mm, C is 111.4 mm, β is 16.1 degrees;

section number 10: r is 432 millimeters, C is 105.1 millimeters, and β is 17.4 degrees;

section number 11: r is 480 mm, C is 96.8 mm, β is 18.7 degrees;

section number 12: r is 528 mm, C is 88 mm, β is 19.8 degrees;

section number 13: r is 576 mm, C is 75 mm, β is 20.8 degrees;

section number 14: r is 624 mm, C is 57 mm, and β is 21.8 degrees.

2. The variable-pitch propeller for the unmanned aerial vehicle according to claim 1, wherein: the distance from the first airfoil section of the root of the blade body to the rotation axis of the propeller is 336 mm.

3. A variable pitch propeller for unmanned aerial vehicles according to claim 1 or 2, wherein: the outer shape of the blade body is low-speed needle-shaped, and the blade tip of the blade body is straight and has sweepback.

4. The variable-pitch propeller for the unmanned aerial vehicle as claimed in claim 3, wherein: the paddle body is provided with three to the contained angle between the adjacent paddle body is 120.

5. The variable-pitch propeller for the unmanned aerial vehicle as claimed in claim 4, wherein: the thickness of the blade body is gradually reduced from the root to the tip.