CN221214588U - A testing arrangement and unmanned aerial vehicle for unmanned aerial vehicle rudder face - Google Patents
A testing arrangement and unmanned aerial vehicle for unmanned aerial vehicle rudder face Download PDFInfo
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- CN221214588U CN221214588U CN202323232034.7U CN202323232034U CN221214588U CN 221214588 U CN221214588 U CN 221214588U CN 202323232034 U CN202323232034 U CN 202323232034U CN 221214588 U CN221214588 U CN 221214588U
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- 238000012360 testing method Methods 0.000 title claims abstract description 38
- 238000009434 installation Methods 0.000 claims description 11
- 238000013461 design Methods 0.000 abstract description 8
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- 230000005484 gravity Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a testing device for a control surface of an unmanned aerial vehicle and the unmanned aerial vehicle. The test device for the unmanned aerial vehicle control surface comprises an unmanned aerial vehicle control surface, a control surface clamping mechanism and a loading device, wherein the control surface clamping mechanism comprises an upper control surface clamp and a lower control surface clamp which are used for clamping the unmanned aerial vehicle control surface, the loading device comprises an upper loading mechanism and a lower loading mechanism, the upper loading mechanism comprises a test frame, a fixed pulley is arranged at the top of the test frame, an upper rope is wound on the fixed pulley, one end of the upper rope is fixed on the upper control surface clamp, and the other end of the upper rope bypasses the fixed pulley to be hung with a weight; the bottom of the lower control surface clamp is connected with a lower rope, and the lower rope is hung with a weight. According to the deflection aspect of the control surface of the unmanned aerial vehicle, the upper loading mechanism or the lower loading mechanism is used for carrying out a loading test on the control surface of the unmanned aerial vehicle to verify whether the angle variation of the control surface of the unmanned aerial vehicle meets the design requirement.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a testing device for a control surface of an unmanned aerial vehicle and the unmanned aerial vehicle.
Background
With the rapid development of navigation industry in recent years, unmanned aircraft tends to be a development trend of the industry, and the fixed-wing unmanned aerial vehicle rapidly occupies the unmanned aerial vehicle market by virtue of the inherent advantages in the aspects of fuel economy, safety and the like. In the fixed wing unmanned aerial vehicle assembly process, because there is the installation error and receives the transportation influence, can exist the position error usually between the actual position of unmanned aerial vehicle control surface and the design position, in order to guarantee unmanned aerial vehicle flight safety, need carry out loading test to unmanned aerial vehicle control surface through testing arrangement and verify whether the angle variation of unmanned aerial vehicle control surface satisfies the design requirement.
The information disclosed in this background section is only for enhancement of understanding of the general background of the utility model and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person of ordinary skill in the art.
Disclosure of utility model
The utility model aims to overcome the defects in the prior art, and provides a testing device for an unmanned aerial vehicle control surface and an unmanned aerial vehicle, which are used for carrying out a loading test on the unmanned aerial vehicle control surface to verify whether the angle variation of the unmanned aerial vehicle control surface meets the design requirement.
In order to achieve the above purpose, the utility model is realized by adopting the following technical scheme:
in one aspect, the utility model provides a testing device for a control surface of an unmanned aerial vehicle, which comprises the control surface of the unmanned aerial vehicle, a control surface clamping mechanism and a loading device, wherein the control surface clamping mechanism comprises an upper control surface clamp and a lower control surface clamp for clamping the control surface of the unmanned aerial vehicle, the loading device comprises an upper loading mechanism and a lower loading mechanism, the upper loading mechanism comprises a testing frame, a fixed pulley is arranged at the top of the testing frame, an upper rope is wound on the fixed pulley, one end of the upper rope is fixed on the upper control surface clamp, and the other end of the upper rope bypasses the fixed pulley to hang a weight; the bottom of the lower control surface clamp is connected with a lower rope, and the lower rope is hung with a weight.
Further, the upper control surface clamp is arranged at the top of the unmanned aerial vehicle control surface, the lower control surface clamp is arranged at the bottom of the unmanned aerial vehicle control surface, and the two ends of the upper control surface clamp and the two ends of the lower control surface clamp are fixedly connected through connecting parts.
Further, the connecting portion comprises two connecting pieces, one end of each connecting piece is fixedly connected with the upper control surface clamp through a screw, and the other end of each connecting piece is fixedly connected with the lower control surface clamp through a screw.
Further, the test frame comprises two bottom beams, wherein a stiffening beam is connected to the middle of each bottom beam, two vertical beams are respectively arranged on the bottom beams, two mounting beams are connected to the tops of the vertical beams, the length of each mounting beam is greater than the distance between the two vertical beams, a mounting part is arranged at the extending end of each mounting beam, and fixed pulleys are fixedly connected to the mounting parts.
Further, a first connecting part connected with the upper rope is arranged on the upper control surface clamp, and a second connecting part connected with the lower rope is arranged on the lower control surface clamp.
On the other hand, the utility model provides an unmanned aerial vehicle, which comprises the testing device for the control surface of the unmanned aerial vehicle.
Compared with the prior art, the utility model has the beneficial effects that:
According to the deflection aspect of the control surface of the unmanned aerial vehicle, the upper loading mechanism or the lower loading mechanism is used for carrying out a loading test on the control surface of the unmanned aerial vehicle to verify whether the angle variation of the control surface of the unmanned aerial vehicle meets the design requirement, and the unmanned aerial vehicle control surface deflection test device is simple in structure and strong in operability.
Drawings
FIG. 1 is a schematic structural diagram of a control surface testing device for an unmanned aerial vehicle according to an embodiment of the present utility model;
fig. 2 is a schematic structural diagram of a control surface testing device for an unmanned aerial vehicle according to an embodiment of the present utility model;
FIG. 3 is a schematic diagram of an upper loading mechanism according to an embodiment of the present utility model;
FIG. 4 is a schematic diagram of a lower loading mechanism according to an embodiment of the present utility model;
FIG. 5 is a schematic view of a test rack according to an embodiment of the present utility model;
In the figure: 1: unmanned plane control surface; 2: an upper control surface clamp; 3: a lower control surface clamp; 4: an upper loading mechanism; 5: a lower loading mechanism; 6: a test rack; 7: a fixed pulley; 8: a rope is arranged; 9: a weight; 10: a lower rope; 11: a connecting sheet; 12: a bottom beam; 13: a stiffening beam; 14: a vertical beam; 15: mounting a beam; 16: a mounting part; 17: a first connection portion; 18: and a second connecting part.
Detailed Description
The utility model is further described below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present utility model, and are not intended to limit the scope of the present utility model.
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", 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 devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus 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", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
Embodiment one:
As shown in fig. 1-4, the embodiment provides a test device for a control surface of an unmanned aerial vehicle, which comprises a control surface 1 of the unmanned aerial vehicle, a control surface clamping mechanism and a loading device, wherein the control surface clamping mechanism comprises an upper control surface clamp 2 and a lower control surface clamp 3 for clamping the control surface 1 of the unmanned aerial vehicle.
In this embodiment, the upper control surface clamp 2 is installed at the top of the unmanned aerial vehicle control surface 1, the lower control surface clamp 3 is installed at the bottom of the unmanned aerial vehicle control surface 1, and two ends of the upper control surface clamp 2 and the lower control surface clamp 3 are fixedly connected through a connecting portion.
In this embodiment, the connecting portion includes two connecting pieces 11, one end of each connecting piece 11 is fixedly connected to the upper control surface clamp 2 through a screw, and the other end is fixedly connected to the lower control surface clamp 3 through a screw.
Specifically, go up control surface clamp 2 with control surface clamp 3 both ends are all through connection piece 11 and screw fixation down for go up control surface clamp 2 and control surface clamp 3 can not follow unmanned aerial vehicle control surface 1 and go out, can guarantee that control surface clamping mechanism presss from both sides tight unmanned aerial vehicle control surface 1, control surface clamping mechanism easy dismounting that this embodiment provided is applicable to different unmanned aerial vehicle control surfaces 1, easy operation.
In this embodiment, the loading device includes an upper loading mechanism 4 and a lower loading mechanism 5, the upper loading mechanism 4 includes a test frame 6, a fixed pulley 7 is installed at the top of the test frame 6, an upper rope 8 is wound on the fixed pulley 7, one end of the upper rope 8 is fixed on the upper control surface clamp 2, and the other end bypasses the fixed pulley 7 to load a weight 9.
Specifically, referring to fig. 5, the test frame 6 includes two bottom beams 12, two middle parts of the bottom beams 12 are connected with a stiffening beam 13, two vertical beams 14 are respectively installed on the bottom beams 12, two top parts of the vertical beams 14 are connected with an installation beam 15, the length of the installation beam 15 is greater than the distance between the two vertical beams 14, an installation portion 16 is installed at the extending end of the installation beam 15, and the fixed pulley 7 is fixedly connected on the installation portion 16.
In this embodiment, the upper control surface clamp 2 is provided with a first connecting portion 17 connected to the upper rope 8, one end of the upper rope 8 is connected to the upper control surface clamp 2 through the first connecting portion 17, and the other end bypasses the fixed pulley 7 fixed to the mounting portion 16 and is connected to a load 9.
Specifically, because unmanned aerial vehicle need dismantle the working element in the transportation, wait for the during operation, install each part on the fuselage again, in order to guarantee unmanned aerial vehicle flight security, need carry out position detection to each control surface of unmanned aerial vehicle before the work.
During the test, use the measuring tape to measure the mounted position of unmanned aerial vehicle rudder surface 1 earlier, then compare the aspect of deflection of design position judgement unmanned aerial vehicle rudder surface 1, when measuring unmanned aerial vehicle rudder surface 1 and deflect downwards, use loading mechanism 4 to provide a reverse upward pulling force loading to unmanned aerial vehicle rudder surface 1 this moment, specifically, be connected with unmanned aerial vehicle rudder surface 1 with last rope 8 one end, the other end is walked around behind the fixed pulley 7 and is connected and hang weight 9, and at this moment, the downward gravity of weight 9 shifts into the upward pulling force that applys to unmanned aerial vehicle rudder surface 1 through fixed pulley 7, can change the pulling force of unmanned aerial vehicle rudder surface 1 upward loading through the weight of adjustment weight 9.
In this embodiment, a second connection portion 18 is installed at the bottom of the lower control surface clamp 3, the second connection portion 18 is connected with a lower rope 10, and the weight 9 is mounted on the lower rope 10.
Specifically, when the unmanned aerial vehicle control surface 1 is measured to deflect upwards, a reverse downward pulling force is provided by the lower loading mechanism 5 and is loaded to the unmanned aerial vehicle control surface 1, one end of the lower rope 10 is connected with the lower control surface clamp 3, one end of the lower rope is connected with the loading weight 9, the downward gravity of the weight 9 is the downward pulling force of the unmanned aerial vehicle control surface 1, and the downward loading pulling force of the unmanned aerial vehicle control surface 1 can be changed by adjusting the weight of the weight 9.
According to the embodiment, the change angles of the unmanned aerial vehicle control surfaces 1 are observed and recorded by loading the tensile force on the different unmanned aerial vehicle control surfaces 1, so that the state of the unmanned aerial vehicle control surfaces 1 under different tensile forces is obtained, whether the angle change quantity of the unmanned aerial vehicle control surfaces 1 meets the design requirement is verified, and important reference data are provided for unmanned aerial vehicle design.
Embodiment two:
The embodiment provides an unmanned aerial vehicle, which comprises the test device for the control surface of the unmanned aerial vehicle.
In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between 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 in a specific case.
Claims (6)
1. The testing device for the control surface of the unmanned aerial vehicle is characterized by comprising the control surface (1) of the unmanned aerial vehicle, a control surface clamping mechanism and a loading device, wherein the control surface clamping mechanism comprises an upper control surface clamp (2) and a lower control surface clamp (3) for clamping the control surface (1) of the unmanned aerial vehicle, the loading device comprises an upper loading mechanism (4) and a lower loading mechanism (5), the upper loading mechanism (4) comprises a testing frame (6), a fixed pulley (7) is arranged at the top of the testing frame (6), an upper rope (8) is wound on the fixed pulley (7), one end of the upper rope (8) is fixed on the upper control surface clamp (2), and the other end of the upper rope bypasses the fixed pulley (7) to hang a weight (9); the bottom of the lower control surface clamp (3) is connected with a lower rope (10), and the lower rope (10) is hung with a weight (9).
2. The test device for the control surface of the unmanned aerial vehicle according to claim 1, wherein the upper control surface clamp (2) is installed at the top of the control surface (1) of the unmanned aerial vehicle, the lower control surface clamp (3) is installed at the bottom of the control surface (1) of the unmanned aerial vehicle, and two ends of the upper control surface clamp (2) and two ends of the lower control surface clamp (3) are fixedly connected through connecting parts.
3. The test device for the control surface of the unmanned aerial vehicle according to claim 2, wherein the connecting part comprises two connecting pieces (11), one end of each connecting piece (11) is fixedly connected with the upper control surface clamp (2) through a screw, and the other end is fixedly connected with the lower control surface clamp (3) through a screw.
4. The test device for the control surface of the unmanned aerial vehicle according to claim 1, wherein the test frame (6) comprises two bottom beams (12), a stiffening beam (13) is connected to the middle of each bottom beam (12), two vertical beams (14) are respectively installed on each bottom beam (12), an installation beam (15) is connected to the top of each vertical beam (14), the length of each installation beam (15) is larger than the distance between the two vertical beams (14), an installation part (16) is installed at the extending end of each installation beam (15), and the fixed pulleys (7) are fixedly connected to the installation parts (16).
5. The test device for the control surface of the unmanned aerial vehicle according to claim 1, wherein the upper control surface clamp (2) is provided with a first connecting part (17) connected with the upper rope (8), and the lower control surface clamp (3) is provided with a second connecting part (18) connected with the lower rope (10).
6. An unmanned aerial vehicle comprising the test device for a control surface of an unmanned aerial vehicle according to any of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323232034.7U CN221214588U (en) | 2023-11-28 | 2023-11-28 | A testing arrangement and unmanned aerial vehicle for unmanned aerial vehicle rudder face |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323232034.7U CN221214588U (en) | 2023-11-28 | 2023-11-28 | A testing arrangement and unmanned aerial vehicle for unmanned aerial vehicle rudder face |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221214588U true CN221214588U (en) | 2024-06-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323232034.7U Active CN221214588U (en) | 2023-11-28 | 2023-11-28 | A testing arrangement and unmanned aerial vehicle for unmanned aerial vehicle rudder face |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221214588U (en) |
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2023
- 2023-11-28 CN CN202323232034.7U patent/CN221214588U/en active Active
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