CN216887198U - Control surface suspension structure for unmanned aerial vehicle, wing and unmanned aerial vehicle - Google Patents
Control surface suspension structure for unmanned aerial vehicle, wing and unmanned aerial vehicle Download PDFInfo
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- CN216887198U CN216887198U CN202122629710.9U CN202122629710U CN216887198U CN 216887198 U CN216887198 U CN 216887198U CN 202122629710 U CN202122629710 U CN 202122629710U CN 216887198 U CN216887198 U CN 216887198U
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- aerial vehicle
- connecting rib
- suspension
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model discloses a control surface suspension structure for an unmanned aerial vehicle, a wing and the unmanned aerial vehicle, which comprise: the top of the connecting rib is provided with an installation groove; the suspension shaft comprises a fixing section and a supporting section which are connected with each other, the fixing section is detachably arranged in the mounting groove, and the supporting section extends to the outer side of the connecting rib and is used for mounting the control surface. The control surface suspension structure can effectively reduce the assembly complexity, improve the assembly efficiency and improve the maintainability of the control surface.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a control surface suspension structure for an unmanned aerial vehicle, a wing and the unmanned aerial vehicle.
Background
The large-scale medium and large-scale unmanned aerial vehicle of great medium and large-scale unmanned aerial vehicle of control surface suspended structure mainly used load, this type of unmanned aerial vehicle's control surface suspended structure generally adopts two kinds of structural style: the other is the integrated design of the control surface connecting rib and the control surface suspension shaft, and the other is the control surface suspension shaft which is separately connected on the web plate of the control surface connecting rib. These two structural forms have two problems: firstly, the requirement on the assembly precision is high, the control surface is clamped between control surface suspension shafts on two sides, one control surface suspension shaft is integrated with a control surface mounting rib, and the other control surface suspension shaft is mounted on the control surface mounting rib, so that the distance between the mounting ribs on two sides of the control surface is required to meet the tolerance requirement, otherwise, the control surface is easy to leap or not mounted; secondly, when the control surface is installed, the control surface on one side needs to be installed on the suspension shaft, and the suspension shaft on the other side is installed on the control surface and then fixed, so that the problem of disassembly and assembly is involved. Therefore, the two structural forms cause the problems of difficult assembly and disassembly and difficult construction.
Therefore, a control surface suspension structure for an unmanned aerial vehicle, a wing and the unmanned aerial vehicle are expected to be researched and developed so as to realize the quick disassembly and assembly of the control surface, reduce the processing and assembly difficulty and improve the disassembly and assembly efficiency.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a control surface suspension structure for an unmanned aerial vehicle, a wing and the unmanned aerial vehicle, overcomes the defects in the design of the traditional control surface suspension structure, improves the assembly efficiency, reduces the cost and improves the maintainability of the control surface.
In order to achieve the above object, the present invention provides a control surface suspension structure for an unmanned aerial vehicle, comprising:
the top of the connecting rib is provided with a mounting groove;
the suspension shaft comprises a fixing section and a supporting section which are connected with each other, the fixing section is detachably arranged in the mounting groove, and the supporting section extends to the outer side of the connecting rib and is used for mounting the control surface.
Optionally, the shape of the fixing section is adapted to the shape of the mounting groove, and a side of the fixing section facing the surface of the connecting rib is in conformity with the surface contour of the connecting rib.
Optionally, the suspension shaft is fixed in the mounting groove by a bolt.
Optionally, the fixed section of the suspension shaft is in a square tube shape;
the support section of hanging the axle is the cylinder type and is the echelonment, including big footpath end and path end, big footpath end connect in the one end of canned paragraph.
Optionally, the support section of the suspension shaft is coaxial with the rotation axis of the control surface.
Optionally, the connecting rib is a groove-shaped rib and comprises an upper edge strip, a lower edge strip, an end plate and a web, one end of the upper edge strip and one end of the lower edge strip are connected with each other, the other end of the upper edge strip and the other end of the lower edge strip are respectively connected to two sides of the end plate, and the web is connected to one side of the upper edge strip, one side of the lower edge strip and one side of the end plate, which face the control surface;
the mounting groove set up in the upper fringe strip.
Optionally, the fixing section and the supporting section of the suspension shaft are integrally formed.
The utility model also provides a wing, which comprises a control surface and at least one control surface suspension structure for the unmanned aerial vehicle;
the control surface suspension structure comprises a connecting rib and a suspension shaft, the connecting rib is connected to the wing back beam, and the control surface is rotatably arranged on the suspension shaft.
Optionally, the wing back spar is a C-beam;
the wing further comprises an upper skin and a lower skin, wherein the upper skin and the lower skin wrap the upper surface and the lower surface of the wing respectively.
The utility model further provides an unmanned aerial vehicle which comprises the wing.
The utility model has the beneficial effects that: the control surface suspension structure can ensure that the control surface is installed in place, reduce the assembly complexity, improve the assembly efficiency, realize the quick assembly and disassembly of the control surface, reduce the production cost and improve the maintainability of the control surface structure.
Additional features and advantages of the utility model will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 shows a schematic view of a control surface suspension structure for a drone according to one embodiment of the utility model.
Fig. 2 shows a schematic view of a connecting rib according to an embodiment of the utility model.
Figure 3 shows a schematic view of a trailing edge portion of an upper skin according to one embodiment of the utility model.
FIG. 4 illustrates a schematic view of a trailing edge portion of a lower skin according to one embodiment of the utility model.
FIG. 5 shows a schematic view of a wing back spar according to one embodiment of the utility model.
FIG. 6 shows a schematic view of a suspension shaft according to an embodiment of the utility model.
Description of the reference numerals
1. Covering the skin; 2. a lower skin; 3. a wing back spar; 4. a connecting rib; 5. a suspension shaft; 6. a control surface; 7. a bolt; 8. mounting grooves; 9. a fixed section; 10. a support section.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the utility model to those skilled in the art.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the utility model and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the utility model.
The utility model discloses a control surface suspension structure for an unmanned aerial vehicle, which comprises:
the top of the connecting rib is provided with an installation groove;
the suspension shaft comprises a fixing section and a supporting section which are connected with each other, the fixing section is detachably arranged in the mounting groove, and the supporting section extends to the outer side of the connecting rib and is used for mounting the control surface.
Particularly, the control surface suspension structure can ensure that the control surface is installed in place, reduces the assembly complexity, improves the assembly efficiency, realizes the quick assembly and disassembly of the control surface, reduces the production cost and improves the maintainability of the control surface structure.
Alternatively, the shape of the fixing section is adapted to the shape of the mounting groove, and the side of the fixing section facing the surface of the connecting rib is in accordance with the surface contour of the connecting rib.
Specifically, the shape of one side of the fixed section facing the surface of the connecting rib is consistent with the shape of the surface of the connecting rib, so that the flatness of the wing can be guaranteed.
Alternatively, the suspension shaft is fixed in the mounting groove by a bolt.
Specifically, when the rudder surface is assembled, the rudder surface can be firstly installed on the wing through the suspension shaft, the connection hole is formed after the position and the distance of the suspension shaft are adjusted, and the rudder surface suspension shaft is fixed in the installation groove through the bolt.
As an alternative, the fixed section of the suspension shaft is in a square tube shape;
the support section of the suspension shaft is cylindrical and stepped and comprises a large-diameter end and a small-diameter end, and the large-diameter end is connected to one end of the fixing section.
Particularly, the fixing section is designed to be of a square tubular structure, so that the stability is good; the support section is designed to be cylindrical, so that the control surface can rotate conveniently.
As an alternative, the suspension shaft support section is coaxial with the rotation axis of the control surface.
As an alternative scheme, the connecting ribs are groove-shaped ribs and comprise upper edge strips, lower edge strips, end plates and web plates, one ends of the upper edge strips and the lower edge strips are connected with each other, the other ends of the upper edge strips and the lower edge strips are respectively connected to two sides of the end plates, and the web plates are connected to one sides, facing the control surface, of the upper edge strips, the lower edge strips and the end plates;
the mounting groove sets up in the upper fringe strip.
Specifically, the mounting groove and the upper edge strip are integrally formed and can be manufactured in a machining mode.
Furthermore, allowance is reserved at the installation position of the suspension shaft of the control surface connecting rib, and the axial position of the suspension shaft is adjusted in the assembling process to ensure that the control surface is installed in place, so that the assembling complexity is reduced.
Alternatively, the fixed section and the support section of the suspension shaft are integrally formed.
The utility model also discloses a wing, which comprises a control surface and at least one control surface suspension structure for the unmanned aerial vehicle;
the control surface suspension structure comprises a connecting rib and a suspension shaft, the connecting rib is connected to the rear wing beam, and the control surface is rotatably arranged on the suspension shaft.
Specifically, the wing overcomes the defects of the design of the traditional wing control surface suspension structure, improves the assembly efficiency, reduces the cost and improves the maintainability of the control surface.
As an alternative, the wing back spar is a C-beam;
the wing also comprises an upper skin and a lower skin, wherein the upper skin and the lower skin respectively wrap the upper surface and the lower surface of the wing.
The utility model also discloses an unmanned aerial vehicle, which comprises the wing.
Examples
The embodiment discloses a control surface suspension structure for an unmanned aerial vehicle, as shown in fig. 1.
As shown in fig. 2, the connecting rib 4 is a groove-shaped rib, and is composed of four surfaces, including an upper edge strip, a lower edge strip, an end plate and a web plate, wherein an installation groove 8 is arranged on the upper edge strip of the connecting rib 4, the installation groove 8 penetrates through the upper edge strip of the connecting rib 4 along the span direction of the wing, the end plate of the connecting rib 5 is connected to the wing back beam 3, and the wing back beam 3 is a C-shaped beam as shown in fig. 5;
as shown in fig. 6, the suspension shaft 5 includes a fixing section 9 and a supporting section 10 which are connected to each other in the axial direction, the fixing section 9 and the supporting section 10 are integrally formed, the fixing section 9 is in a square tube shape and detachably disposed in the mounting groove 8 through the bolt 7, the bottom surface and both sides of the fixing section 9 are respectively attached to the bottom surface and the side walls of the mounting groove 8, and the top surface of the fixing section 9 and the upper edge strip of the connecting rib 4 have the same shape; the supporting section 10 is cylindrical and stepped and comprises a large-diameter end and a small-diameter end, the large-diameter end is connected to one end of the fixing section 9, the supporting section 10 extends to the outer side of the connecting rib and is used for installing the control surface 6, and an included angle is formed between the axis of the fixing section 9 of the suspension shaft 5 and the axis of the supporting section 10, so that the supporting section 10 is coaxial with a rotating shaft of the control surface.
An upper skin 1 and a lower skin 2 wrap the upper surface and the lower surface of the wing respectively, fig. 3 is a schematic view of a trailing edge part of the upper skin, and fig. 4 is a schematic view of a trailing edge part of the lower skin.
The embodiment comprises the following steps in practical application:
1) manufacturing a pair of connecting ribs according to the appearance of the wing of the unmanned aerial vehicle, arranging installation grooves on the upper edges of the connecting ribs, and then installing the two connecting ribs on a rear wing beam according to a designed distance;
2) a pair of suspension shafts are processed according to the three-dimensional digital-analog numerical control, and the connecting holes are processed in a numerical control mode from the upper surfaces of the suspension shafts to the lower side;
3) during assembly, firstly, mounting a suspension shaft on one side on a connecting rib on one side, then mounting one side of a control surface on the suspension shaft, then mounting a suspension shaft on the other side of the control surface, then placing the suspension shaft into a mounting groove on the other connecting rib, and then drilling connecting holes on the connecting rib according to the connecting holes on the suspension shaft;
4) and taking the suspension shaft off the connecting ribs, mounting a supporting plate nut on the connecting ribs, then mounting the suspension shaft into the control surface, mounting the suspension shaft into the clamping groove of the connecting ribs of the control surface together, and connecting the suspension shaft and the control surface by using connecting bolts.
In other embodiments, a control surface suspension structure can be provided, which is only used for fixing one side of the control surface and can realize the quick assembly and disassembly of the control surface.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. A control surface suspended structure for unmanned aerial vehicle, its characterized in that includes:
the top of the connecting rib is provided with a mounting groove;
the suspension shaft comprises a fixing section and a supporting section which are connected with each other, the fixing section is detachably arranged in the mounting groove, and the supporting section extends to the outer side of the connecting rib and is used for mounting the control surface.
2. The control surface suspension structure for unmanned aerial vehicle of claim 1, wherein the shape of the fixing section is adapted to the shape of the mounting groove, and the side of the fixing section facing the surface of the connecting rib is in accordance with the surface contour of the connecting rib.
3. The control surface suspension structure for unmanned aerial vehicle of claim 1, wherein the suspension shaft is fixed in the mounting groove by a bolt.
4. The control surface suspension structure for unmanned aerial vehicle of claim 1, wherein the fixed section of the suspension shaft is square tubular;
the support section of hanging the axle is the cylinder type and is the echelonment, including big footpath end and path end, big footpath end connect in the one end of canned paragraph.
5. Control surface suspension structure for unmanned aerial vehicles according to claim 1, characterized in that the support section of the suspension shaft is coaxial with the rotation axis of the control surface.
6. The rudder surface suspension structure for unmanned aerial vehicles according to claim 1, wherein the connecting rib is a groove-shaped rib including an upper rim, a lower rim, end plates and a web, one end of the upper rim and the lower rim are connected to each other, the other end of the upper rim and the lower rim are respectively connected to both sides of the end plates, and the web is connected to the upper rim, the lower rim and one side of the end plates facing the rudder surface;
the mounting groove set up in the upper fringe strip.
7. The control surface suspension structure for unmanned aerial vehicle of claim 1, wherein the fixed section and the support section of the suspension shaft are integrally formed.
8. An airfoil, characterized in that it comprises a control surface and at least one control surface suspension structure for a drone according to any one of claims 1 to 7;
the control surface suspension structure comprises a connecting rib and a suspension shaft, the connecting rib is connected to the rear wing beam, and the control surface is rotatably arranged on the suspension shaft.
9. The airfoil of claim 8, wherein the airfoil back spar is a C-beam;
the wing further comprises an upper skin and a lower skin, wherein the upper skin and the lower skin wrap the upper surface and the lower surface of the wing respectively.
10. A drone, characterized in that it comprises a wing according to claim 8 or 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122629710.9U CN216887198U (en) | 2021-10-29 | 2021-10-29 | Control surface suspension structure for unmanned aerial vehicle, wing and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122629710.9U CN216887198U (en) | 2021-10-29 | 2021-10-29 | Control surface suspension structure for unmanned aerial vehicle, wing and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216887198U true CN216887198U (en) | 2022-07-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122629710.9U Active CN216887198U (en) | 2021-10-29 | 2021-10-29 | Control surface suspension structure for unmanned aerial vehicle, wing and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216887198U (en) |
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2021
- 2021-10-29 CN CN202122629710.9U patent/CN216887198U/en active Active
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