Automatic positioning structure for riveting fixture clamping plate of rear fuselage of unmanned aerial vehicle

Abstract

The utility model discloses an automatic positioning structure for a riveting fixture clamping plate of a rear fuselage of an unmanned aerial vehicle and belongs to the technical field of riveting of unmanned aerial vehicles. The assembling period can be shortened, efficiency is improved, and repeated positioning precision is improved. The pressing clamping plate and the supporting clamping plate are used for clamping a fuselage skin, the pressing clamping plate is rotationally connected with the supporting clamping plate through a rotating shaft on the clamping plate connecting piece, the right end of the pressing clamping plate extends outwards to be hinged to a vertically-arranged air cylinder telescopic rod, the air cylinder stretches out and draws back to drive the movable pressing clamping plate to be opened and closed, and the supporting clamping plate is connected to the main body frame through a support. An H-shaped positioning piece is fixed to the left end of the supporting clamping plate, and the left end of the pressing clamping plate is lapped on the H-shaped positioning piece and fixed to the H-shaped positioning piece through a quick-insertion positioning bolt assembly. The riveting fixture is mainly used for a rear fuselage riveting fixture of a certain unmanned aerial vehicle, is high in precision, good in retentivity and high in efficiency during assembly, and can realize quick positioning of fuselage skin and improve repeated positioning precision by adding the air cylinder and the automatic positioning bolt.

Description

Technical Field

[0001] The utility model belongs to the technical field of riveting of unmanned aerial vehicles, and in particular relates to an automatic positioning structure for a riveting frame card plate of a rear fuselage of an unmanned aerial vehicle. Background Art

[0002] Traditional detachable movable pallets are widely used in the positioning of the skin of various drones. Traditional detachable movable pallets can achieve skin positioning, but the disadvantage of this method is that the hand-tightened bolts and handle nuts at both ends need to be manually disassembled, and the movable pallet needs to be manually disassembled. This method has a long assembly cycle and low efficiency, and the repeated positioning accuracy is reduced due to the increase in the number of disassembly times. The current detachable movable pallets cannot meet their docking needs. Utility Model Content

[0003] In order to solve the problems existing in the prior art, the utility model provides an automatic positioning structure for a riveted frame card plate of a rear fuselage of an unmanned aerial vehicle, which can shorten the assembly cycle, improve efficiency, and increase repeated positioning accuracy.

[0004] The technical solution adopted by the utility model is:

[0005] An automatic positioning structure for a riveted frame pallet of a rear fuselage of an unmanned aerial vehicle comprises a clamping pallet, a supporting pallet, a pallet connector, a cylinder, an H-shaped positioning piece and a quick-insert positioning pin assembly; the clamping pallet and the supporting pallet are arranged relatively to each other up and down, and are used to clamp the fuselage skin; the right end of the clamping pallet is rotatably connected to the supporting pallet via a rotating shaft on the pallet connector, and the rotating shaft is used as a rotating fulcrum; the right end of the clamping pallet extends outward and is hinged to a vertically arranged cylinder telescopic rod; the telescopic movement of the cylinder drives the movable clamping pallet to open and close; the cylinder is fixed to the right end of the supporting pallet, and the supporting pallet is connected to the main frame via a support; an H-shaped positioning piece is fixed to the left end of the supporting pallet, and the left end of the clamping pallet is placed on the H-shaped positioning piece and fixed to the H-shaped positioning piece via a quick-insert positioning pin assembly.

[0006] Compared with the prior art, the utility model has the following beneficial effects:

[0007] 1. The utility model is mainly used for the riveting frame of the rear fuselage of a certain unmanned aerial vehicle. It has high precision, good retention and high efficiency during assembly. The utility model adds a cylinder and an automatic positioning pin, which can realize rapid positioning of the fuselage skin and improve the repeated positioning accuracy.

[0008] 2. The utility model adopts an automatic positioning latch, which has the advantages of stability, safety, portability, etc. compared with traditional latches.

[0009] 3. The opening method of the clamping plate of the utility model is that the cylinder retracts to drive the clamping plate to open, which is convenient for workers to operate, speeds up production speed, and improves repeated positioning accuracy.

[0010] 4. The utility model adds an in-place sensor to prevent the product from colliding with the clamping plate when it is closed, thereby causing safety hazards. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is the front view of the utility model;

[0012] Figure 2 This is a schematic diagram of the structure of the quick-insert positioning pin assembly of the utility model;

[0013] Figure 3 It is a side view of the utility model when it is installed on the main frame;

[0014] Figure 4 This is the main view of the utility model when it is installed on the main frame;

[0015] Figure 5 It is a top view of the utility model when it is installed on the main frame;

[0016] Among them: 2. Clamping card; 3. Support card; 4. Card connector; 5. Cylinder connector; 6. Cylinder; 7. Y-type connector; 8. In-position sensor; 9. H-type positioning piece; 10. Quick-insert positioning pin assembly; 11. Pin; 12. Stopper; 13. Support. DETAILED DESCRIPTION

[0017] In order to better understand the purpose, structure and function of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings.

[0018] like Figure 1 to Figure 5 As shown, the utility model provides an automatic positioning structure for the riveted frame card of the rear fuselage of an unmanned aerial vehicle, including a clamping card 2, a supporting card 3, a card connector 4, a cylinder 6, an H-shaped positioning member 9 and a quick-insert positioning pin assembly 10; the clamping card 2 and the supporting card 3 are arranged opposite to each other up and down, and the fuselage skin is clamped therebetween. The right end of the clamping card 2 is rotatably connected to the supporting card 3 through a rotating shaft on the card connector 4, and the rotating shaft is used as a rotating fulcrum. The right end of the clamping card 2 extends outward and is hinged with a telescopic rod of a vertically arranged cylinder 6. The telescopic movement of the cylinder 6 drives the movable clamping card 2 to open and close. The cylinder 6 is fixed on the right end of the supporting card 3, and the supporting card 3 is connected to the main frame through a support 13. An H-shaped positioning member 9 is fixed to the left end of the supporting card 3, and the left end of the clamping card 2 is placed on the H-shaped positioning member 9 and fixed to the H-shaped positioning member 9 through a quick-insert positioning pin assembly 10.

[0019] like Figure 1As shown, the in-place sensor 8 is arranged at the left end of the pressing card plate 2 to monitor the position of the left end of the pressing card plate 2 , and the in-place sensor 8 is installed on the supporting card plate 3 .

[0020] like Figure 1 , Figure 2 As shown, the quick-insert positioning pin assembly 10 includes a pin 11; the lower end of the H-shaped positioning member 9 is inserted into the supporting card plate 3 and fixedly connected to the supporting card plate 3, the upper end of the H-shaped positioning member 9 is provided with a through hole 1, and the left end of the clamping card plate 2 is provided with a through hole 2 corresponding to the through hole 1, and the pin 11 passes through the through hole 1 and the through hole 2 in sequence to connect the clamping card plate 2 to the H-shaped positioning member 9.

[0021] like Figure 2 As shown, the quick-insert positioning pin assembly 10 also includes a stopper 12; the stopper 12 adopts a sleeve structure, a through hole is set on the left side wall of the stopper 12, and is sleeved on the pin 11 through the through hole gap. The stopper 12 is fixedly connected to the left side wall of the H-shaped positioning member 9, and an annular protrusion is set on the pin 11 located inside the stopper 12, and the diameter of the annular protrusion is larger than the diameter of the through hole of the stopper 12.

[0022] like Figure 1 As shown, the cylinder 6 is fixed on the supporting clamp 3 via a cylinder connecting member 5 .

[0023] like Figure 1 As shown, the telescopic rod of the cylinder 6 is connected to the lower end of the Y-shaped joint 7, and the clamping card 2 is hinged to the connecting shaft of the Y-shaped joint 7. The Y-shaped joint 7 is an existing component.

[0024] like Figure 1 As shown, the upper end of the cardboard connector 4 is fixedly connected to the clamping cardboard 2, and the lower end of the cardboard connector 4 is provided with a rotation, and is rotatably connected to the supporting cardboard 3 through a rotating shaft.

[0025] like Figure 1 , Figure 2 As shown, during positioning, the cylinder 6 extends to drive the clamping plate 2 to clamp the rear fuselage skin and reaches the tooling limit position. At this time, the in-position sensor 8 senses the clamping plate 2 and transmits a signal to the cylinder 6. The cylinder 6 stops moving, and the worker pushes the latch 11 in to position the clamping plate 2.

[0026] Such as 1. Figure 2 As shown, after assembly, after pulling the latch 11 to disengage the clamping plate 2, the stopper 12 can limit the latch 11 from being pulled out, which is convenient for workers to operate. The cylinder 6 contracts to drive the clamping plate 2 to open, and the rear fuselage is lowered.

[0027] It is understood that the present invention is described by some embodiments, and those skilled in the art are aware that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. In addition, under the teachings of the present invention, these features and embodiments may be modified to adapt to specific circumstances and materials without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the scope of protection of the present invention.

Claims

1. An automatic positioning structure for riveting jigs and plates of a rear fuselage of an unmanned aerial vehicle, characterized in that: The invention comprises a clamping card plate (2), a supporting card plate (3), a card plate connecting piece (4), a cylinder (6), an H-shaped positioning piece (9) and a quick-insertion positioning pin assembly (10); the clamping card plate (2) and the supporting card plate (3) are arranged opposite to each other in the upper and lower parts, and are used to clamp the fuselage skin; the right end of the clamping card plate (2) is rotatably connected to the supporting card plate (3) via a rotating shaft on the card plate connecting piece (4), and the rotating shaft is used as a rotation fulcrum, and the right end of the clamping card plate (2) extends outward and is connected to the vertical The telescopic rod of the cylinder (6) is hinged, and the cylinder (6) is telescopic to drive the movable clamping plate (2) to open and close. The cylinder (6) is fixed to the right end of the supporting clamping plate (3), and the supporting clamping plate (3) is connected to the main frame through a support (13). An H-shaped positioning piece (9) is fixed to the left end of the supporting clamping plate (3), and the left end of the clamping clamp (2) is placed on the H-shaped positioning piece (9) and fixed to the H-shaped positioning piece (9) through a quick-insert positioning pin assembly (10).

2. The automatic positioning structure for riveting jigs and pallets of the rear fuselage of an unmanned aerial vehicle according to claim 1, characterized in that: The in-position sensor (8) is arranged at the left end of the pressing card plate (2) and is used to monitor the position of the left end of the pressing card plate (2). The in-position sensor (8) is mounted on the supporting card plate (3).

3. The automatic positioning structure for riveting jigs and plates of the rear fuselage of an unmanned aerial vehicle according to claim 2, characterized in that: The quick-insert positioning pin assembly (10) comprises a pin (11); the lower end of the H-shaped positioning piece (9) is inserted into the supporting card plate (3) and fixedly connected to the supporting card plate (3); the upper end of the H-shaped positioning piece (9) is provided with a first through hole; the left end of the clamping card plate (2) is provided with a second through hole corresponding to the first through hole; the pin (11) passes through the first through hole and the second through hole in sequence to connect the clamping card plate (2) to the H-shaped positioning piece (9).

4. The automatic positioning structure for riveting jigs and plates of the rear fuselage of an unmanned aerial vehicle according to claim 3, characterized in that: The quick-insert positioning pin assembly (10) further comprises a stopper (12); the stopper (12) adopts a sleeve structure, a through hole is provided on the left side wall of the stopper (12), and the stopper (12) is sleeved on the pin (11) through a gap in the through hole, the stopper (12) is fixedly connected to the left side wall of the H-shaped positioning member (9), and an annular protrusion is provided on the pin (11) located inside the stopper (12), and the diameter of the annular protrusion is greater than the diameter of the through hole of the stopper (12).

5. The automatic positioning structure for riveting jigs and plates of the rear fuselage of an unmanned aerial vehicle according to claim 1, characterized in that: The cylinder (6) is fixed on the supporting clamping plate (3) via a cylinder connecting piece (5).

6. The automatic positioning structure for riveting jigs and plates of the rear fuselage of an unmanned aerial vehicle according to claim 5, characterized in that: The telescopic rod of the cylinder (6) is connected to the lower end of the Y-shaped joint (7), and the pressing clamp (2) is hinged to the connecting shaft of the Y-shaped joint (7).

7. The automatic positioning structure for riveting jigs and plates of the rear fuselage of an unmanned aerial vehicle according to claim 1, characterized in that: The upper end of the cardboard connecting piece (4) is fixedly connected to the pressing cardboard (2), and the lower end of the cardboard connecting piece (4) is provided with a rotation mechanism and is rotationally connected to the supporting cardboard (3) via a rotating shaft.

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