CN219369453U

CN219369453U - Unmanned aerial vehicle wing fatigue strength test equipment

Info

Publication number: CN219369453U
Application number: CN202320048247.5U
Authority: CN
Inventors: 黄道远; 钟易民; 黄道博
Original assignee: Shenzhen Vispractice Intelligent Aviation Technology Co ltd
Current assignee: Shenzhen Vispractice Intelligent Aviation Technology Co ltd
Priority date: 2023-01-06
Filing date: 2023-01-06
Publication date: 2023-07-18
Anticipated expiration: 2033-01-06

Abstract

The utility model relates to the technical field of unmanned aerial vehicle testing equipment, in particular to unmanned aerial vehicle wing fatigue strength testing equipment. The apparatus includes a base; the wing fixing seat is arranged at one end of the base; the testing device is arranged at the other end of the base and comprises a driving mechanism, a swinging seat and a first clamp, the driving mechanism is fixedly arranged on the base and is in transmission connection with the swinging seat, the first clamp is arranged on the swinging seat, a pressure sensor is arranged between the first clamp and the swinging seat and is electrically connected with an electric control device of testing equipment, the pressure sensor is used for monitoring yield pressure and strength failure time of a workpiece, and further, the testing of fatigue strength of sine wave reciprocating bending of the wing workpiece can be achieved.

Description

Unmanned aerial vehicle wing fatigue strength test equipment

Technical Field

The utility model relates to the technical field of unmanned aerial vehicle testing equipment, in particular to unmanned aerial vehicle wing fatigue strength testing equipment.

Background

Unmanned aerial vehicles are unmanned planes operated by using radio remote control equipment and self-contained program control devices, and are widely applied to the military and civil fields. Unmanned aerial vehicles are various, and mainly comprise fixed wing unmanned aerial vehicles, flapping wing unmanned aerial vehicles, multi-rotor unmanned aerial vehicles and the like. The multi-rotor unmanned aerial vehicle is simple to operate and control, high in reliability, capable of taking off and landing vertically without a runway, and capable of hovering in the air after taking off, so that the multi-rotor unmanned aerial vehicle is widely applied to various fields relative to a fixed-wing unmanned aerial vehicle and a flapping-wing unmanned aerial vehicle.

In the production process of the unmanned aerial vehicle, the wing needs to be subjected to a fatigue strength test, wherein the fatigue strength refers to the maximum stress of the material under infinite alternating load without damage, and is called fatigue strength or fatigue limit. For better design and manufacture of the wing, it is quite necessary to test it for fatigue strength.

Disclosure of Invention

The utility model provides unmanned aerial vehicle wing fatigue strength testing equipment which is applied to the detection and testing of unmanned aerial vehicle wing fatigue strength.

In order to solve the above problems, the present utility model provides an unmanned aerial vehicle wing fatigue strength testing device, comprising:

a base;

the wing fixing seat is arranged at one end of the base;

the testing device is arranged at the other end of the base and comprises a driving mechanism, a swinging seat and a first clamp, wherein the driving mechanism is fixedly arranged on the base and is in transmission connection with the swinging seat, the first clamp is arranged on the swinging seat, a pressure sensor is arranged between the first clamp and the swinging seat, and the pressure sensor is electrically connected with an electric control device of testing equipment.

In one possible embodiment, preferably, the driving mechanism includes a support plate, a speed-adjusting motor, a rotating wheel and a rocker arm, the support plate is fixedly arranged on the base, the rotating wheel is rotatably arranged on the support plate, an output end of the speed-adjusting motor is in transmission connection with the rotating wheel, the rotating wheel is connected with one end of the rocker arm, and the other end of the rocker arm is connected with the swing seat.

In one possible embodiment, preferably, the driving mechanism further includes an adjustable stud, the adjustable stud is disposed between the rotating wheel and the rocker arm, the adjustable stud is fixedly connected with the rotating wheel, and the adjustable stud is rotatably connected with the rocker arm.

In one possible embodiment, preferably, the wing fixing base includes a support frame and a second clamp, the support frame is fixedly disposed on the base, the second clamp is detachably disposed on one end of the support frame away from the base, and the second clamp is used for clamping the unmanned aerial vehicle wing.

In a possible embodiment, the test device preferably further comprises an electronic control device for controlling the actuation of the drive mechanism and displaying the test data of the pressure sensor.

The beneficial effects of the utility model are as follows: the utility model provides unmanned aerial vehicle wing fatigue strength testing equipment, which comprises a base, a wing fixing seat and a testing device, wherein the wing fixing seat is arranged at one end of the base, the testing device is arranged at the other end of the base, one end of a wing is fixed on the wing fixing seat when the unmanned aerial vehicle wing fatigue strength testing equipment is used, the other end of the wing is fixed on the testing device, the testing device drives the wing to reciprocate, and further, the yield pressure and the strength failure time of the wing in the testing process are monitored through a pressure sensor, so that the wing fatigue strength is tested, and the wing is designed and manufactured better.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present utility model and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 shows a schematic overall structure of a test apparatus;

FIG. 2 shows a schematic overall structure of the test apparatus at another angle;

FIG. 3 shows a schematic overall structure of the test device;

fig. 4 shows a schematic overall structure of the test device at another view angle.

Description of main reference numerals:

100-base; 200-wing fixing seats; 210-a support frame; 220-a second clamp; 300-testing device; 310-a drive mechanism; 311-supporting plates; 312-a speed-regulating motor; 313-rotating wheel; 314-rocker arms; 315-adjustable studs; 320-swinging seat; 330-a first clamp; 340-a pressure sensor; 400-an electric control device; 500-wing.

Detailed Description

Embodiments of the present utility model are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the utility model.

In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present utility model.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

In the present utility model, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.

Referring to fig. 1 and 2, the present utility model provides an unmanned aerial vehicle wing fatigue strength testing device (hereinafter referred to as device for short), which comprises a base 100, a wing fixing seat 200 and a testing device 300, wherein the wing fixing seat 200 is fixedly arranged at one end of the base 100, the testing device 300 is arranged at the other end of the base 100, when in use, one end of a wing 500 is fixed on the wing fixing seat 200, and the other end of the wing 500 is fixed on the testing device 300.

Specifically, the testing device 300 includes a driving mechanism 310, a swinging seat 320 and a first clamp 330, the driving mechanism 310 is fixedly disposed on the base 100, an output end of the driving mechanism 310 is in transmission connection with the swinging seat 320, the first clamp 330 is fixedly disposed on the swinging seat 320, a pressure sensor 340 is disposed between the first clamp 330 and the swinging seat 320, and the pressure sensor 340 is electrically connected with an electronic control device 400 of the testing apparatus.

In the above scheme, one end of the wing 500 is fixed on the wing fixing seat 200, the other end of the wing 500 is fixed on the first clamp 330, the driving mechanism 310 drives the swing seat 320 to reciprocate, and the further pressure sensor 340 monitors the strength failure time and yield pressure of the wing 500 in the testing process, so as to further realize the testing of the fatigue strength of the sine wave reciprocating bending of the wing 500.

Referring to fig. 3 and 4, on the basis of the above-mentioned scheme, preferably, the driving mechanism 310 includes a supporting plate 311, a speed regulating motor 312, a rotating wheel 313 and a rocker arm 314, the supporting plate 311 is fixedly disposed on the base 100, the swing seat 320 is slidably disposed on the supporting plate 311, the first clamp 330 is fixedly disposed on the swing seat 320, a pressure sensor 340 is disposed between the swing seat 320 and the first clamp 330, the rotating wheel 313 is rotatably disposed on the supporting plate 311, the rotating wheel 313 is in driving connection with the speed regulating motor 312, the rotating wheel 313 is rotatably connected with one end of the rocker arm 314, the other end of the rocker arm 314 is rotatably connected with the swing seat 320, and then the swing seat 320 can be driven to reciprocate on the supporting plate 311 when the speed regulating motor 312 acts, so that the wing 500 can be driven to reciprocate, and at this time, the pressure sensor 340 can transmit the strength failure time and yield pressure data of the wing 500 to the electronic control device 400.

It should be explained that the device includes an electric control device 400, the electric control device 400 is used for controlling the action frequency of the speed regulating motor 312 to meet the requirements of different wings 500, meanwhile, the electric control device 400 is used for displaying the test data of the wings 500, and the working principle of how the electric control device 400 operates is the mature prior art, and meanwhile, the device does not belong to the improvement scope of the scheme, so that excessive redundant description is not performed on the device.

With continued reference to fig. 1 and fig. 2, based on the above-mentioned scheme, the wing fixing base 200 includes a support frame 210 and a second clamp 220, where the support frame 210 is fixedly disposed on the base 100, and meanwhile, the second clamp 220 is detachably disposed on an end of the support frame 210 away from the base 100, and the second clamp 220 is used for fixing the wing 500.

Referring to fig. 3 and 4, on the basis of the above scheme, the driving mechanism 310 further includes an adjustable stud 315, the adjustable stud 315 is fixedly disposed on the rotating wheel 313, and meanwhile, the adjustable stud 315 is rotationally connected with the rocker arm 314, and the reciprocating motion amplitude of the driving mechanism 310 can be adjusted by adjusting the adjustable stud 315, and meanwhile, the driving mechanism is matched with the action of the debugging motor 312, so that the testing requirements of different wings 500 can be met.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present utility model have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the utility model, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the utility model.

Claims

1. Unmanned aerial vehicle wing fatigue strength test equipment, characterized in that includes:

a base;

the wing fixing seat is arranged at one end of the base;

2. The unmanned aerial vehicle wing fatigue strength test device according to claim 1, wherein the driving mechanism comprises a supporting plate, a speed regulating motor, a rotating wheel and a rocker arm, the supporting plate is fixedly arranged on the base, the rotating wheel is rotatably arranged on the supporting plate, the output end of the speed regulating motor is in transmission connection with the rotating wheel, the rotating wheel is connected with one end of the rocker arm, and the other end of the rocker arm is connected with the swing seat.

3. The unmanned aerial vehicle wing fatigue strength testing device of claim 2, wherein the drive mechanism further comprises an adjustable stud disposed between the rotating wheel and the rocker arm, the adjustable stud being fixedly connected to the rotating wheel, the adjustable stud being rotatably connected to the rocker arm.

4. The unmanned aerial vehicle wing fatigue strength test device of claim 1, wherein the wing fixing base comprises a support frame and a second clamp, the support frame is fixedly arranged on the base, the second clamp is detachably arranged on one end of the support frame away from the base, and the second clamp is used for clamping the unmanned aerial vehicle wing.

5. The unmanned aerial vehicle wing fatigue strength testing device of claim 1, further comprising an electronic control for controlling the actuation of the drive mechanism and displaying the test data of the pressure sensor.