CN217990698U - Quick riveting tool for airplane multi-size components with specified tracks - Google Patents
Quick riveting tool for airplane multi-size components with specified tracks Download PDFInfo
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- CN217990698U CN217990698U CN202222168009.6U CN202222168009U CN217990698U CN 217990698 U CN217990698 U CN 217990698U CN 202222168009 U CN202222168009 U CN 202222168009U CN 217990698 U CN217990698 U CN 217990698U
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Abstract
The utility model discloses a rapid riveting tool for multi-size components of an airplane with an appointed track, which comprises a bracket component, a positioning component and a slide rail component, wherein the positioning component and the slide rail component are both arranged on the bracket component; the support assembly comprises a frame and a support platform, and the frame is arranged on the support platform; the sliding rail assembly comprises a first sliding rail, a second sliding rail and three sliding rails, the first sliding rail and the second sliding rail are arranged on the frame, the number of the third sliding rails is two, the two third sliding rails are arranged on the support table, and sliding blocks are arranged on the first sliding rail, the second sliding rail and the two third sliding rails in a sliding mode; the positioning assembly comprises two first baffle plates and two second baffle plates, and one ends of the two first baffle plates are respectively connected with the sliding blocks on the two third sliding rails; compared with the prior art, the utility model realize improving the purpose of positioning size scope and precision on the basis that reduces manual operation intensity by a wide margin.
Description
Technical Field
The utility model relates to a rivet dress frock technical field, concretely relates to quick rivet dress frock of many sizes parts of aircraft of appointed orbit.
Background
In the field of current aircraft riveting, component riveting is an important ring in whole machine assembly, and component products are characterized by large weight, multiple size types, wide hole position distribution needing coordinated riveting and high interchangeability requirement;
the existing positioning riveting tool is designed for a riveting tool of a certain airplane part, but the scheme of the existing positioning riveting tool is basically a fixing scheme aiming at a single part and utilizes the specific positioning mode and the exit state requirements of a positioner.
Disclosure of Invention
The utility model provides a quick riveting frock of many sizes of aircraft part of appointed orbit, the purpose is solved among the current technique riveting frock and can only carry out the problem of fixing to single part.
In order to solve the technical problem, the utility model discloses the technical scheme who adopts is:
a rapid riveting tool for airplane multi-size components with specified tracks comprises a support assembly, a positioning assembly and a sliding rail assembly, wherein the positioning assembly and the sliding rail assembly are arranged on the support assembly;
the support assembly comprises a frame and a support platform, and the frame is arranged on the support platform;
the sliding rail assembly comprises a first sliding rail, a second sliding rail and three sliding rails, the first sliding rail and the second sliding rail are arranged on the frame, the number of the third sliding rails is two, the two third sliding rails are arranged on the support table, and sliding blocks are arranged on the first sliding rail, the second sliding rail and the two third sliding rails in a sliding mode;
the positioning assembly comprises two first baffles and two second baffles, one ends of the two first baffles are respectively connected with the sliding blocks on the two third sliding rails, the other ends of the two first baffles slide above the mounting table, one ends of the second baffles are connected with the sliding blocks on the first sliding rails, and the other ends of the second baffles are connected with the sliding blocks on the second sliding rails.
Further inject, first baffle includes L template and mounting panel, and the L template setting is on the up end of mounting panel, and the slider on mounting panel and the third slide rail can be dismantled and be connected, and the L template is used for the top at the mount table to slide.
Further optimize, be provided with the splice bar between L template and the connecting plate.
Further inject, all be provided with locating component on the slider that is located first slide rail, second slide rail and third slide rail upper end, locating component is used for locking the slider on slide rail set spare.
Further inject, locating component is including setting up the bolt on the slider and setting up the pinhole on the slide rail, and the bolt is used for with pinhole interference fit.
Further optimize, the both ends of first slide rail, second slide rail and third slide rail all are provided with the stopper.
Further inject, be provided with the connecting plate on the second baffle, be provided with the clamp on the connecting plate, the connecting plate is used for placing the part of treating the riveting, and the clamp is used for treating the riveted part and fixes.
Further optimize, still be provided with the crossbeam on the frame.
Further inject, all be provided with the nylon pad on connecting plate and the mount table.
Further optimize, the four corners position of the bottom of mount table all is provided with the stabilizer blade.
Compared with the prior art, the utility model discloses following beneficial effect has:
the utility model mainly comprises a bracket component, a slide rail component and a positioning component, wherein the bracket component is used as a main bearing body of the whole structure, in the actual use process, a worker places airplane components to be riveted on an installation table, adjusts the front and back positions of a first baffle according to components with different thicknesses, and finally clamps the components to be riveted between the first baffle and a frame through a fixed slider; the worker can also place the airplane component to be riveted on the frame, adjust the distance between the two second baffles through components with different sizes, and fix the large-size component by fixing the sliding block according to the actual position of the component; the advantage of setting up like this can improve the assembly precision of aircraft part assembly by a wide margin, reduces repeated positioning error, reduces the positioning assembly error of human factor, reduces workman intensity of labour simultaneously, improves work efficiency.
Drawings
In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings which are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and that for those skilled in the art, other related drawings can be obtained according to these drawings without inventive efforts.
Fig. 1 is one of the schematic structural diagrams of the present invention.
Fig. 2 is an explosion diagram of the present invention.
Fig. 3 is a second schematic structural diagram of the present invention.
In the figure, 101-a frame, 102-a support platform, 103-a first slide rail, 104-a second slide rail, 105-a third slide rail, 106-a slide block, 107-a first baffle, 108-a second baffle, 109-an L-shaped plate, 110-a mounting plate, 111-a connecting rib, 112-a positioning component, 113-a limiting block, 114-a connecting plate, 115-a clamp, 116-a cross beam, 117-a nylon cushion and 118-a support leg.
Detailed Description
The present invention will be further described with reference to the following examples, which are intended to illustrate only some, but not all, of the embodiments of the present invention. Based on the embodiments in the present invention, other embodiments used by those skilled in the art without creative efforts all belong to the protection scope of the present invention.
Example one
Referring to fig. 1-3, the embodiment discloses a rapid riveting tool for airplane multi-size components with a designated track, which includes a bracket assembly, a positioning assembly 112 and a slide rail assembly, wherein the positioning assembly 112 and the slide rail assembly are both arranged on the bracket assembly;
the supporting assembly comprises a frame 101 and a supporting platform 102, wherein the frame 101 is arranged on the supporting platform 102;
the slide rail assembly comprises a first slide rail 103, a second slide rail 104 and a third slide rail 105, the first slide rail 103 and the second slide rail 104 are both arranged on the frame 101, the number of the third slide rails 105 is two, the two third slide rails 105 are both arranged on the support platform 102, and sliding blocks 106 are respectively arranged on the first slide rail 103, the second slide rail 104 and the two third slide rails 105 in a sliding manner;
the positioning assembly 112 comprises two first baffle plates 107 and two second baffle plates 108, one ends of the two first baffle plates 107 are respectively connected with the sliding blocks 106 on the two third sliding rails 105, the other ends of the two first baffle plates slide above the mounting table, one ends of the second baffle plates 108 are connected with the sliding blocks 106 on the first sliding rails 103, and the other ends of the second baffle plates 108 are connected with the sliding blocks 106 on the second sliding rails 104;
the utility model mainly comprises a bracket component, a slide rail component and a positioning component 112, wherein the bracket component is used as a main bearing body of the whole structure, the slide rail component is connected with the bracket component in a dense thread rigid connection mode, and the working stability of a first slide rail 103, a second slide rail 104 and a third slide rail 105 is ensured to the utmost extent; the positioning component 112 is tightly connected with the sliding rail component in a threaded rigid connection mode, so that the positioning rigidity and the effectiveness of fixing parts are improved; in the actual using process, a worker places the aircraft component to be riveted on the mounting table, adjusts the position of the first baffle plate 107 according to components with different thicknesses, and finally clamps the component to be riveted between the first baffle plate 107 and the frame 101 through the fixing slide block 106; the worker can also place the aircraft component to be riveted on the frame 101, adjust the distance between the two second baffles 108 through components with different sizes, and fix the large-size component by fixing the sliding block 106 according to the actual position of the component; the advantage of setting up like this can improve the assembly precision of aircraft part assembly by a wide margin, reduces repeated positioning error, reduces the positioning assembly error of human factor, reduces workman intensity of labour simultaneously, improves work efficiency.
Further, the first baffle plate 107 comprises an L-shaped plate 109 and a mounting plate 110, the L-shaped plate 109 is arranged on the upper end surface of the mounting plate 110, the mounting plate 110 is detachably connected with the sliding block 106 on the third sliding rail 105, and the L-shaped plate 109 is used for sliding above the mounting table; in the actual use process, the worker adjusts the sliding block 106 on the third sliding rail 105, clamps the component to be riveted between the L-shaped plate 109 and the frame 101, and fixes the sliding block 106, thereby completing clamping and fixing of the component to be riveted.
Further preferably, a connecting rib 111 is arranged between the L-shaped plate 109 and the connecting plate 114, and the connecting rib 111 is arranged to make the connection relationship between the L-shaped plate 109 and the connecting plate 114 more stable.
Further, the sliding blocks 106 at the upper ends of the first sliding rail 103, the second sliding rail 104 and the third sliding rail 105 are all provided with a positioning assembly 112, and the positioning assembly 112 is used for locking the sliding blocks 106 on the sliding rail assemblies.
Further, the positioning assembly 112 includes a pin disposed on the sliding block 106 and a pin hole disposed on the sliding rail, the pin is used to cooperate with the pin hole, and the pin hole are used to fix the sliding block 106 during actual use.
Further preferably, the two ends of the first slide rail 103, the second slide rail 104 and the third slide rail 105 are provided with limit blocks 113, and the purpose of the limit blocks 113 is to prevent the slide block 106 from being disengaged from the first slide rail 103, the second slide rail 104 or the third slide rail 105.
Further, a connecting plate 114 is arranged on the second baffle 108, a clamp 115 is arranged on the connecting plate 114, the connecting plate 114 is used for placing a part to be riveted, and the clamp 115 is used for fixing the part to be riveted.
Further preferably, the frame 101 is further provided with a cross beam 116, and the cross beam 116 is used for improving the stability of the frame 101.
Further optimize, the four corners position of the bottom of mount table all is provided with stabilizer blade 118, sets up the stability that stabilizer blade 118 is the improvement mount table.
Example two
Referring to fig. 1 and fig. 2, the present embodiment is further optimized based on the first embodiment, in the present embodiment, the connecting plate 114 and the mounting platform are both provided with nylon pads 117;
in actual use, the purpose of the nylon pads 117 provided on the connection plate 114 is to prevent the clamp 115 from crushing the aircraft component to be riveted, and the purpose of the nylon pads 117 provided on the mounting table is to provide cushioning for the aircraft component to be riveted.
While the preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following appended claims be interpreted as including the preferred embodiment and all such alterations and modifications as fall within the scope of the invention. The above description is only exemplary of the present invention and should not be taken as limiting, and all changes, equivalents, and improvements made within the spirit and principles of the present invention should be understood as being included in the scope of the present invention.
Claims (10)
1. The utility model provides a quick riveting frock of many sizes of aircraft part of appointed orbit which characterized in that: the device comprises a bracket component, a positioning component (112) and a sliding rail component, wherein the positioning component (112) and the sliding rail component are arranged on the bracket component;
the supporting assembly comprises a frame (101) and a supporting platform (102), and the frame (101) is arranged on the supporting platform (102);
the sliding rail assembly comprises a first sliding rail (103), a second sliding rail (104) and three sliding rails (105), the first sliding rail (103) and the second sliding rail (104) are arranged on the frame (101), the number of the third sliding rails (105) is two, the two third sliding rails (105) are arranged on the support platform (102), and sliding blocks (106) are arranged on the first sliding rail (103), the second sliding rail (104) and the two third sliding rails (105) in a sliding manner;
the positioning assembly (112) comprises two first baffle plates (107) and two second baffle plates (108), one end of each first baffle plate (107) is connected with a sliding block (106) on the third sliding rail (105), the other end of each first baffle plate slides above the mounting table, one end of each second baffle plate (108) is connected with the sliding block (106) on the first sliding rail (103), the other end of each second baffle plate is connected with the sliding block (106) on the second sliding rail (104), and the other second baffle plate (108) is fixedly connected with the frame (101).
2. The rapid riveting tool for the multi-size components of the airplane with the designated track according to claim 1, is characterized in that: first baffle (107) include L template (109) and mounting panel (110), and L template (109) set up on the up end of mounting panel (110), and slider (106) on mounting panel (110) and third slide rail (105) can be dismantled and be connected, and L template (109) are used for sliding in the top of mount table.
3. The rapid riveting tool for the multi-size components of the airplane with the designated track according to claim 2, is characterized in that: a connecting rib (111) is arranged between the L-shaped plate (109) and the connecting plate (114).
4. The rapid riveting tool for the multi-size components of the airplane with the designated track according to claim 1, is characterized in that: and the positioning components (112) are arranged on the sliding blocks (106) positioned at the upper ends of the first sliding rail (103), the second sliding rail (104) and the third sliding rail (105), and the positioning components (112) are used for locking the sliding blocks (106) on the sliding rail components.
5. The rapid riveting tool for the multi-size components of the airplane with the specified track according to claim 4, characterized in that: the positioning assembly (112) comprises a plug pin arranged on the sliding block (106) and a pin hole arranged on the sliding rail, and the plug pin is used for being in interference fit with the pin hole.
6. The rapid riveting tool for the multi-size components of the airplane with the designated track according to claim 1, is characterized in that: the two ends of the first sliding rail (103), the second sliding rail (104) and the third sliding rail (105) are provided with limiting blocks (113).
7. The rapid riveting tool for the multi-size components of the airplane with the designated track according to claim 1, is characterized in that: the second baffle (108) is provided with a connecting plate (114), the connecting plate (114) is provided with a clamp (115), the connecting plate (114) is used for placing a part to be riveted, and the clamp (115) is used for fixing the part to be riveted.
8. The rapid riveting tool for the multi-size components of the airplane with the designated track according to claim 1, is characterized in that: the frame (101) is also provided with a cross beam (116).
9. The rapid riveting tool for the multi-size components of the airplane with the specified track according to claim 1, characterized in that: nylon pads (117) are arranged on the connecting plate (114) and the mounting table.
10. The rapid riveting tool for the multi-size components of the airplane with the specified track according to claim 1, characterized in that: four corners of the bottom of the mounting table are provided with support legs (118).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222168009.6U CN217990698U (en) | 2022-08-17 | 2022-08-17 | Quick riveting tool for airplane multi-size components with specified tracks |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222168009.6U CN217990698U (en) | 2022-08-17 | 2022-08-17 | Quick riveting tool for airplane multi-size components with specified tracks |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217990698U true CN217990698U (en) | 2022-12-09 |
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ID=84321443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222168009.6U Active CN217990698U (en) | 2022-08-17 | 2022-08-17 | Quick riveting tool for airplane multi-size components with specified tracks |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217990698U (en) |
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2022
- 2022-08-17 CN CN202222168009.6U patent/CN217990698U/en active Active
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