CN210852998U - Unmanned aerial vehicle fuselage assembly is with assembling foling frock - Google Patents
Unmanned aerial vehicle fuselage assembly is with assembling foling frock Download PDFInfo
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- CN210852998U CN210852998U CN201921988481.6U CN201921988481U CN210852998U CN 210852998 U CN210852998 U CN 210852998U CN 201921988481 U CN201921988481 U CN 201921988481U CN 210852998 U CN210852998 U CN 210852998U
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Abstract
The utility model discloses an unmanned aerial vehicle fuselage assembly is with assembling frock that folds, including the frock frame, frame clamp plate group and locating plate group, the top sliding connection of frock frame has first fixed base group, and the frock frame passes through screw threaded connection with first fixed base group, and the quantity of first fixed base group is unanimous with the quantity of frame clamp plate group, and the top sliding connection of first fixed base group has frame clamp plate group, and first fixed base group is pegged graft through the pin is fixed with frame clamp plate group, and locating plate group includes frame clamp plate group, wing locating plate and fin locating plate. This unmanned aerial vehicle fuselage assembly is with assembling the frock that folds, through setting up each structure of pegging graft with first fixed base group and second fixed base group of frock frame fixed connection through the pin is fixed for the fuselage splices the assembly more simple and convenient, and fuselage intensity is high, and later maintenance is changed more conveniently, thereby has that wing and fin interface precision are high, fuselage intensity is high and later maintenance changes more convenient characteristics.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle makes technical field, and more specifically says, it relates to an unmanned aerial vehicle fuselage assembly is with assembling frock that folds.
Background
In the forming process of the large unmanned aerial vehicle body, split structures are mostly adopted, an upper split structure and a lower split structure are adopted in some unmanned aerial vehicle bodies, a front split structure and a rear split structure are adopted in some unmanned aerial vehicle bodies, and an integrated structure is adopted in some unmanned aerial vehicle bodies; the large unmanned aerial vehicle has a complex internal structure, the partition frame can be arranged in a key position inside the large unmanned aerial vehicle for ensuring the strength of the vehicle body, and the position precision of the partition frame directly influences the strength, the aerodynamics and the like of the vehicle. In order to facilitate the assembly and adjustment of the machine body, the tool is adopted when the machine body is folded, and the folding tool is different according to different splitting modes;
the folding tool with the split left and right bodies is adopted, a folding area can be effectively avoided when the tool is operated, the operation space is larger, the tool position of a positioning frame plate in the folding tool is better determined, but in left and right folding, a splicing seam of a machine body is always in a weak area with strength such as a hatch cover opening, the stress is large in the flying process of an airplane, the local stress is concentrated and is easy to peel off, the safe flying of the unmanned aerial vehicle is influenced, and the tool has a limit on the flying speed of the airplane;
the front and rear split folding tools are adopted, the tool design is simple, the folding and fixing are also very convenient, the splicing seam can effectively avoid an area with large stress, but the positioning of the inner frame plate is difficult, the gluing space of the frame plate is limited, the frame plate is often adhered to be inclined, and the normal flying posture and strength of the airplane are influenced;
the integrated folding tool is adopted, the cabin cover and the machine body are integrated when being formed, the size of the cabin cover is reduced as much as possible, and the requirement on connection is lowered. The machine body bonded by the tool has high requirements on a forming die, and is difficult to maintain in the later period, limited in internal space and limited in equipment;
the structure of left and right folding is adopted, in the original design of the folding tool, most of the frame plate positioning plates are all arranged outside the machine body, when the machine body is folded up and down, the frame plate positioning plates need to be disassembled, and after folding up, the frame plate positioning plates are installed, so that the folding tool is very inconvenient; in addition, the precision can be affected in the process of disassembling the frame plate of the folding tool, so that the assembling interface of the wing and the empennage is misaligned;
therefore, the folding tool for assembling the body of the large unmanned aerial vehicle is convenient to disassemble and assemble and capable of meeting the flight intensity of the unmanned aerial vehicle.
SUMMERY OF THE UTILITY MODEL
Not enough to prior art exists, the utility model aims to provide an unmanned aerial vehicle fuselage assembly is with assembling the frock that folds, it has wing and fin interface precision height, fuselage intensity height and later maintenance change more convenient characteristics.
In order to achieve the above purpose, the utility model provides a following technical scheme:
the utility model provides an unmanned aerial vehicle fuselage assembly is with assembling foling frock, including the frock frame, frame plate clamp plate group and locating plate group, the top sliding connection of frock frame has first fixed base group, frock frame and first fixed base group pass through screw threaded connection, the quantity of first fixed base group is unanimous with the quantity of frame plate clamp plate group, the top sliding connection of first fixed base group has frame plate clamp plate group, first fixed base group passes through the fixed grafting of pin with frame plate clamp plate group, locating plate group includes frame plate locating plate group, wing locating plate and fin locating plate.
Further, the inner wall of the tool framework is connected with a second fixed base group in a sliding mode, and the number of the second fixed base groups is consistent with the number of the positioning plate groups.
Furthermore, the second fixed base group is connected with the tool framework through screw threads, and one end of the second fixed base group is connected with the frame plate positioning plate group in a sliding mode.
Through above-mentioned technical scheme, utilize second unable adjustment base to pass through the fixed locating plate group of pegging graft of pin.
Furthermore, the frame plate positioning plate group and the second fixed base group are fixedly inserted through pins, and the frame plate positioning plate group is positioned in the tool frame.
Furthermore, the wing positioning plates are fixedly connected with the second fixed base group through pins, and the wing positioning plates are located on two sides of the inner top wall of the tool frame.
Furthermore, the empennage positioning plate is fixedly connected with the second fixed base group through a pin, and the empennage positioning plate is located at the tail part of the inner top wall of the tool framework.
Through the technical scheme, the positioning plate groups are all installed in the frame body through the pin screws, the upper frame body and the lower frame body do not need to be disassembled in the folding process, the positioning accuracy of the wings and the empennage is improved, and the aerodynamic appearance of the airplane is guaranteed.
Further, the bottom of the tool frame is fixedly connected with universal wheels.
Through the technical scheme, the universal wheels are utilized to enable the overall carrying and operation of the folding tool to be more convenient.
To sum up, the utility model discloses following beneficial effect has:
1. through setting up each structure of pegging graft through pin fixed connection with frock frame fixed connection's first fixed base group and second fixed base group, make the fuselage splice the assembly more simple and convenient, the precision is higher, wing and fin interface precision are high, later stage assembly wing and fin are convenient, the fuselage splices the tang and bonds firmly, fuselage intensity is high, can stand the test that faster flight speed brought, clamp plate and locating plate all can be dismantled, later maintenance is changed more conveniently, thereby it is high to have wing and fin interface precision, fuselage intensity is high and later maintenance changes more convenient characteristics.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic top view of the present invention;
fig. 3 is a schematic view of the fixing base structure of the present invention.
In the figure: 1. a tooling frame; 2. a frame plate pressing plate group; 3. a first fixed base group; 4. a screw; 5. a pin; 6. a frame plate positioning plate set; 7. a wing positioning plate; 8. a tail positioning plate; 9. a second fixed base group; 10. a universal wheel.
Detailed Description
Example (b):
the present invention will be described in further detail with reference to the accompanying fig. 1-3.
A folding tool for unmanned aerial vehicle body assembly is shown in figures 1-3 and comprises a tool frame 1, a frame plate pressing plate group 2 and a positioning plate group, wherein the top of the tool frame 1 is connected with a first fixed base group 3 in a sliding mode, the tool frame 1 and the first fixed base group 3 are in threaded connection through screws 4, the number of the first fixed base groups 3 is consistent with that of the frame plate pressing plate group 2, the top of the first fixed base group 3 is connected with the frame plate pressing plate group 2 in a sliding mode, the first fixed base group 3 and the frame plate pressing plate group 2 are fixedly spliced through pins 5, and the positioning plate group comprises a frame plate positioning plate group 6, a wing positioning plate 7 and a tail wing positioning plate 8;
as shown in fig. 1-3, the inner wall of the tool frame 1 is slidably connected with second fixed base groups 9, the number of the second fixed base groups 9 is equal to the number of the positioning plate groups, the second fixed base groups 9 are in threaded connection with the tool frame 1 through screws 4, one end of each second fixed base group 9 is slidably connected with a frame plate positioning plate group 6, the frame plate positioning plate groups 6 and the second fixed base groups 9 are fixedly inserted and connected through pins 5, and the frame plate positioning plate groups 6 are located inside the tool frame 1;
as shown in fig. 1 to 3, the wing positioning plate 7 is fixedly connected with the second fixed base group 9 through a pin 5, the wing positioning plate 7 is located on two sides of the inner top wall of the tooling frame 1, the tail positioning plate 8 is fixedly connected with the second fixed base group 9 through a pin 5, the tail positioning plate 8 is located at the tail of the inner top wall of the tooling frame 1, and the bottom of the tooling frame 1 is fixedly connected with a universal wheel 10.
Through setting up and 1 fixed connection's of frock frame first fixed base group 3 and second fixed base group 9 through each structure of 5 fixed grafting of pin, it is more simple and convenient to make the fuselage splice the assembly, the precision is higher, wing and fin interface precision are high, later stage assembly wing and fin are convenient, the fuselage splices the tang and bonds firmly, fuselage intensity is high, can stand the examination that faster flight speed brought, clamp plate and locating plate all can be dismantled, later maintenance is changed more conveniently, thereby it is high to have wing and fin interface precision, fuselage intensity is high and the more convenient characteristics of later maintenance change.
The working principle is as follows: at first the equipment closes the frock, fixes universal wheel 10, will treat the unmanned aerial vehicle of equipment and arrange in on the frock frame 1, adjust unmanned aerial vehicle and close the frock and align, and the fixed grafting is carried out through pin 5 to connection frame board clamp plate group 2 and locating plate group, splices fixedly and the bonding frame, when needs dismantle the maintenance, takes pin 5 out, and separation frame board clamp plate group 2, locating plate group isotructure can.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications to the present embodiment without inventive contribution as required after reading the present specification, but all of them are protected by patent laws within the scope of the claims of the present invention.
Claims (7)
1. The utility model provides an unmanned aerial vehicle fuselage assembly is with assembling close up frock, includes that frock frame (1), deckle board clamp plate group (2) and locating plate group, its characterized in that: the top sliding connection of frock frame (1) has first fixed base group (3), frock frame (1) and first fixed base group (3) are through screw (4) threaded connection, the quantity of first fixed base group (3) is unanimous with the quantity of frame plate clamp plate group (2), the top sliding connection of first fixed base group (3) has frame plate clamp plate group (2), first fixed base group (3) and frame plate clamp plate group (2) are through pin (5) fixed grafting, the locating plate group includes frame plate locating plate group (6), wing locating plate (7) and fin locating plate (8).
2. The unmanned aerial vehicle fuselage assembly of claim 1 is with folding frock, characterized in that: the inner wall of the tool frame (1) is connected with second fixed base groups (9) in a sliding mode, and the number of the second fixed base groups (9) is consistent with the number of the positioning plate groups.
3. The unmanned aerial vehicle fuselage assembly of claim 2 is with healing frock, its characterized in that: the second fixed base group (9) is in threaded connection with the tool frame (1) through a screw (4), and one end of the second fixed base group (9) is connected with the frame plate positioning plate group (6) in a sliding mode.
4. The unmanned aerial vehicle fuselage assembly of claim 3 is with folding frock, characterized in that: the frame plate positioning plate group (6) and the second fixed base group (9) are fixedly inserted through the pins (5), and the frame plate positioning plate group (6) is located inside the tool frame (1).
5. The unmanned aerial vehicle fuselage assembly of claim 1 is with folding frock, characterized in that: the wing positioning plate (7) is fixedly connected with the second fixed base group (9) through a pin (5), and the wing positioning plate (7) is located on two sides of the inner top wall of the tool frame (1).
6. The unmanned aerial vehicle fuselage assembly of claim 1 is with folding frock, characterized in that: the tail fin positioning plate (8) is fixedly connected with the second fixed base group (9) through a pin (5), and the tail fin positioning plate (8) is located at the tail of the inner top wall of the tool frame (1).
7. The unmanned aerial vehicle fuselage assembly of claim 1 is with folding frock, characterized in that: the bottom of the tool frame (1) is fixedly connected with universal wheels (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921988481.6U CN210852998U (en) | 2019-11-18 | 2019-11-18 | Unmanned aerial vehicle fuselage assembly is with assembling foling frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921988481.6U CN210852998U (en) | 2019-11-18 | 2019-11-18 | Unmanned aerial vehicle fuselage assembly is with assembling foling frock |
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| Publication Number | Publication Date |
|---|---|
| CN210852998U true CN210852998U (en) | 2020-06-26 |
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| CN201921988481.6U Active CN210852998U (en) | 2019-11-18 | 2019-11-18 | Unmanned aerial vehicle fuselage assembly is with assembling foling frock |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722318A (en) * | 2021-01-18 | 2021-04-30 | 成都纵横鹏飞科技有限公司 | Unmanned aerial vehicle assembly and debugging rack |
-
2019
- 2019-11-18 CN CN201921988481.6U patent/CN210852998U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722318A (en) * | 2021-01-18 | 2021-04-30 | 成都纵横鹏飞科技有限公司 | Unmanned aerial vehicle assembly and debugging rack |
| CN112722318B (en) * | 2021-01-18 | 2023-06-23 | 成都纵横鹏飞科技有限公司 | Unmanned aerial vehicle assembly debugging rack |
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