CN111824451A - Aircraft part transports guarantor type device - Google Patents
Aircraft part transports guarantor type device Download PDFInfo
- Publication number
- CN111824451A CN111824451A CN202010577602.9A CN202010577602A CN111824451A CN 111824451 A CN111824451 A CN 111824451A CN 202010577602 A CN202010577602 A CN 202010577602A CN 111824451 A CN111824451 A CN 111824451A
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- positioning
- assembly
- frame
- component
- joint
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/50—Handling or transporting aircraft components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B62—LAND VEHICLES FOR TRAVELLING OTHERWISE THAN ON RAILS
- B62D—MOTOR VEHICLES; TRAILERS
- B62D63/00—Motor vehicles or trailers not otherwise provided for
- B62D63/02—Motor vehicles
- B62D63/025—Modular vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B62—LAND VEHICLES FOR TRAVELLING OTHERWISE THAN ON RAILS
- B62D—MOTOR VEHICLES; TRAILERS
- B62D63/00—Motor vehicles or trailers not otherwise provided for
- B62D63/02—Motor vehicles
- B62D63/04—Component parts or accessories
Abstract
The invention discloses an aircraft component transferring and shape-keeping device which comprises an AGV moving platform, wherein a template frame assembly for fixing the front end of an aircraft component, an opening frame beam positioning assembly for fixing a middle frame beam of the aircraft component and a frame positioner assembly for fixing the rear end of the aircraft component are sequentially arranged from the front end to the rear end of the top of the AGV moving platform, and a seat joint positioning assembly is also arranged on the AGV moving platform corresponding to a seat on the aircraft component; the invention has the advantages of stably positioning and fixing the airplane components and effectively ensuring the pose consistency and the positioning precision of the airplane components before and after transportation.
Description
Technical Field
The invention belongs to the technical field of airplane component transferring devices, and particularly relates to an airplane component transferring and shape-maintaining device.
Background
With the gradual disjointing of the traditional airplane production and manufacturing mode in the aspects of capacity demand, process demand and the like, the automatic production concept gradually appears in the airplane manufacturing industry, such as automatic robot drilling and riveting and the like. The traditional aircraft manufacturing and assembling is mainly completed by manpower, and is assembled in a complete machine, so that time and labor are wasted, and the precision of the assembling process is difficult to guarantee. The automatic aircraft manufacturing concept is a production line-oriented operation mode, and the control on the assembly efficiency and the process precision far exceeds the traditional manufacturing mode. However, in the assembly and manufacturing process of the pipeline, the automatic transfer of the aircraft component products among different stations also has factors influencing the assembly precision, and in order to ensure the assembly precision, the shapes of the aircraft components after the transfer and after the operation of workers or automatic equipment before the transfer are required to be consistent and not deformed, and the spatial positions of the aircraft components under each station meet the requirements. In view of the technical requirements, the invention provides a transportation shape-preserving device for airplane components.
Disclosure of Invention
The invention aims to provide an aircraft component transferring and shape-maintaining device, which realizes stable transfer of aircraft components and effectively ensures the positioning accuracy of each part of the aircraft components after station transfer and transformation of the aircraft components.
The invention is realized by the following technical scheme:
the utility model provides an aircraft parts transports guarantor type device, includes AGV moving platform, the front end to the rear end at AGV moving platform's top set gradually the template frame subassembly that is used for fixed aircraft parts front end, be used for fixed aircraft parts middle part frame roof beam locating component, be used for fixed aircraft parts rear end's frame locator subassembly, it is provided with seat joint locating component still to correspond the seat on the aircraft parts on the AGV moving platform.
The template frame assembly is arranged at the front end of the top of the AGV moving platform and used for positioning and fixing a front end frame beam of the airplane component, and the fixed end of the template frame assembly is connected with a connecting structure such as a connecting pin hole or a connecting seat on the front end frame beam of the airplane component correspondingly; the frame beam positioning assembly is arranged in the center of the top of the AGV moving platform and used for positioning and fixing a middle frame beam of the airplane, and the fixed end of the frame beam positioning assembly is connected with a connecting structure such as a connecting pin hole or a connecting seat on the middle frame beam of the airplane part; the frame positioner assembly is arranged at the rear end of the top of the AGV moving platform and used for positioning and fixing a rear end frame beam of the airplane component, and the fixed end of the frame positioner assembly is connected with a connecting structure such as a connecting pin hole or a connecting seat on the rear end frame beam of the airplane component correspondingly; the seat connects locating component to be located between mouth frame roof beam locating component and the frame locator subassembly, and the stiff end that the seat connects locating component corresponds the joint setting on the aircraft part seat for carry out the location restriction to the joint on the seat.
In order to better realize the method, the template frame assembly further comprises a frame template and a base, the base is arranged at the front end of the top of the AGV moving platform, a frame template used for supporting the front end of the aircraft component is arranged at the top of the base, and a plurality of connecting pieces are arranged on one side, close to the aircraft component, of the frame template, and correspond to connecting pin holes in the aircraft component.
In order to better realize the invention, the frame beam positioning assembly further comprises a pressing device, a first connecting support seat and a second connecting support seat which are sequentially arranged from the front end to the rear end, the pressing device is used for pressing the front end of the middle frame beam of the airplane component, and a plurality of connecting pieces are arranged on the first connecting support seat and the second connecting support seat corresponding to the connecting pin holes in the middle frame beam of the airplane component.
In order to better realize the method, the frame positioner component comprises a component framework, an upper outline positioning block, a middle outline positioning block and a lower outline positioning block, wherein the component framework is arranged at the rear end of the top of the AGV moving platform, the upper outline positioning blocks are symmetrically arranged at two ends of the top of the component framework, the middle outline positioning block is arranged at the middle position of the top of the component framework, and the lower outline positioning blocks are symmetrically arranged at two ends of the bottom of the component framework.
In order to better realize the invention, the seat joint positioning assembly comprises a seat positioning pin, a seat joint and an assembly supporting column, the assembly supporting column is arranged between the opening frame beam positioning assembly and the frame positioner assembly, the top and the side surface of the assembly supporting column are provided with the seat joint, one end of the seat joint, which is far away from the assembly supporting column, is a U-shaped connecting seat, and the U-shaped connecting seat is provided with the seat positioning pin in a penetrating manner.
In order to better realize the invention, the invention further comprises an inclined plate positioning assembly for fixing the plate ribs of the airplane component, a joint positioning assembly for fixing the joints of the airplane component and a section positioning assembly for fixing the section of the airplane component, wherein the inclined plate positioning assembly is arranged close to one side of the template frame assembly, the joint positioning assembly is arranged close to one side of the seat joint positioning assembly, and the section positioning assembly is arranged close to the mouth frame beam positioning assembly.
In order to better realize the invention, the swash plate positioning assembly further comprises a swash plate side positioning piece and a swash plate middle positioning piece, the swash plate middle positioning piece is arranged corresponding to the middle part of the front end swash plate of the aircraft component, a fixed wedge block for fixing the middle part of the front end swash plate of the aircraft component is arranged on the swash plate middle positioning piece, swash plate side positioning pieces are symmetrically arranged on two sides of the swash plate middle positioning piece, and connecting pieces for fixing two sides of the front end swash plate of the aircraft component are arranged on the top of the swash plate side positioning piece.
In order to better realize the invention, the joint positioning assembly further comprises a positioning head, a joint positioning pin, a joint cylindrical pin and a joint positioning strut, the joint positioning strut is arranged close to one side of the seat joint positioning assembly, the top of the joint positioning strut is provided with the positioning head, and two ends of the positioning head are respectively provided with the joint positioning pin and the joint cylindrical pin.
In order to better realize the method, the profile positioning assembly further comprises positioning pressing plates, profile positioning pillars and butterfly pressing nuts, the profile positioning pillars are arranged on two sides of the top of the AGV moving platform, the positioning pressing plates are arranged on the tops of the profile positioning pillars in a sliding mode, adjusting sliding grooves are formed in two sides of each positioning pressing plate, and the butterfly pressing nuts are installed on the top of the positioning pressing plates in a threaded mode.
In order to better realize the invention, furthermore, a lock pin drill jig assembly is arranged on one side of the template frame assembly, and a front drill jig assembly is arranged on the other side of the template frame assembly; and a rear drill jig assembly is arranged between the frame beam positioning assembly and the frame positioner assembly.
Compared with the prior art, the invention has the following advantages and beneficial effects:
(1) according to the invention, the template frame assembly, the mouth frame beam positioning assembly and the frame positioner assembly are sequentially arranged at the front end, the middle part and the rear end of the top of the AGV moving platform, the front end of an aircraft component is effectively positioned and fixed through the template frame assembly, the middle part of the aircraft component is effectively positioned and fixed through the mouth frame beam positioning assembly, and the rear end of the aircraft component is effectively positioned and fixed through the frame positioner assembly, so that the positioning and fixing of the integral structure of the aircraft component are realized, and the pose consistency of the aircraft component before and after transportation is effectively ensured; meanwhile, the seat of the aircraft component is effectively positioned and fixed by arranging the seat joint positioning assembly, so that the positioning precision of the aircraft component after transfer is further ensured;
(2) according to the invention, the inclined plate positioning assembly is arranged on the AGV moving platform and positioned on one side of the template frame assembly, and the inclined plate positioning assembly is used for positioning and fixing the irregular and fragile inclined plate at the front end of the aircraft component, so that the deformation and damage of the inclined plate in the transferring process of the aircraft component are avoided, and meanwhile, the pose consistency and the positioning accuracy of the inclined plate before and after transferring are effectively ensured;
(3) according to the invention, the joint positioning assemblies are arranged on the AGV moving platform corresponding to the joints at different positions on the aircraft part, and the joints on the aircraft part are effectively positioned and fixed through the joint positioning assemblies, so that the deformation and damage of the joints in the transferring process are avoided, and meanwhile, the pose consistency and the positioning accuracy of the joints before and after transferring are effectively ensured;
(4) according to the invention, the profile positioning assemblies are symmetrically arranged on two sides of the middle part of the AGV moving platform, the profile positioning assemblies are used for limiting and clamping two sides of the frame beam of the airplane component, and meanwhile, the cross beam positioning assemblies are matched for limiting the frame beam, so that the pose consistency and the positioning accuracy of the frame beam of the airplane component before and after transferring are effectively ensured;
(5) according to the invention, the lock pin drill jig assembly and the front drill jig assembly are respectively arranged on two sides of the template frame assembly, and the lock pin drill jig assembly and the front drill jig assembly are used for conducting guide drilling on positions, which need to be drilled, on the aircraft component, so that the drilling precision of the front end on the aircraft component is ensured;
(6) according to the invention, the rear drill jig assembly is arranged at the rear end of the AGV moving platform, and the rear end of the aircraft component is effectively supported through the rear drill jig assembly, so that the pose consistency and the positioning accuracy of the rear end of the aircraft component before and after transfer are effectively ensured;
(7) when the aircraft parts need to be transferred, the supporting platform and the AGV moving carrier vehicle are quickly positioned and connected through the butt joint positioning assemblies, the aircraft parts are fixed through the supporting platform and the positioning fixing assemblies on the supporting platform, and the AGV moving carrier vehicle is used for realizing convenient transfer of the aircraft parts; when aircraft parts do not need to be transported, the supporting platform and the AGV are moved to carry the cargo car split, and the positioning fixing assemblies on the supporting platform and the supporting platform are in a standing state, so that the postures and the positions of the aircraft parts cannot be influenced.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic diagram of an AGV moving a cart;
FIG. 3 is a schematic view of the installation of the positioning posts and the zero point positioning contacts;
FIG. 4 is a schematic structural view of a stencil frame assembly;
FIG. 5 is a schematic structural view of an aperture frame beam positioning assembly;
FIG. 6 is a schematic structural view of a frame locator assembly;
FIG. 7 is a schematic structural view of a locking pin jig assembly;
FIG. 8 is a schematic structural view of a front drill jig assembly;
FIG. 9 is a schematic structural view of a swash plate positioning assembly;
FIG. 10 is a schematic view of the seat joint positioning assembly;
FIG. 11 is a schematic structural view of a beam positioning assembly;
FIG. 12 is a schematic view of the construction of the joint positioning assembly;
FIG. 13 is a schematic structural view of a profile positioning assembly;
FIG. 14 is a schematic structural view of a rear jig assembly.
Wherein: 1-AGV moving a platform; 2-a docking positioning assembly; 3-a template frame assembly; 4-a mouth frame beam positioning assembly; 5-a frame locator assembly; 6-a lockpin drill jig assembly; 7-a front drill jig assembly; 8-a sloping plate positioning component; 9-a seat joint positioning assembly; 10-a beam positioning assembly; 11-a joint positioning assembly; 12-a profile positioning assembly; 13-a back jig assembly; 201-fast connecting a master disc; 202-quick connector disc; 203-Mecanum wheels; 204-positioning upright post; 205-zero point positioning contacts; 301-template frame threaded pin; 302-template frame step pin; 303-frame template; 304-a base; 401-a compactor; 402-a first connection support seat; 403-second connecting support seat; 501-component skeleton; 502-upper profile locating block; 503-middle profile positioning block; 504-lower profile locating block; 601-locking pin drill plate; 602-a latch bearing mount; 603-locking pin shaft; 604-a locking bolt; 701-upper drill plate; 702-a front jig support; 703-front jig connections; 704-lower drill plate; 801-sloping plate side positioning piece; 802-fixed wedges; 803-sloping plate middle positioning piece; 901-seat alignment pins; 902-seat joint; 903 — component support post; 111-a positioning head; 112-joint locating pins; 113-joint cylindrical pins; 114-joint positioning struts; 121-positioning a pressure plate; 122-profile positioning posts; 123-butterfly compression nut; 131-a rear mold support; 132-rear die corner seats; 133-back jig drilling template; 01-a support platform; 02-AGV moves the carrier.
Detailed Description
Example 1:
the utility model provides an aircraft part transports guarantor type device of embodiment, as shown in fig. 1 and fig. 2, including AGV moving platform 1, the front end to the rear end at AGV moving platform 1's top have set gradually template frame subassembly 3, the mouth frame roof beam locating component 4 that is used for fixed aircraft part middle part frame roof beam, be used for fixed aircraft part rear end frame locator subassembly 5 that are used for fixed aircraft part front end, it is provided with seat joint locating component 9 still to correspond the seat on the aircraft part on the AGV moving platform 1.
The top of AGV moving platform 1 is for supporting the base, and the top of supporting the base is followed and is pointed the direction of rear end from the front end and has been set gradually template frame subassembly 3, mouthful frame roof beam locating component 4, frame locator subassembly 5, and template frame subassembly 3 sets up at the top front end that supports the base, and frame locator subassembly 5 sets up in the top rear end that supports the base, and mouthful frame roof beam locating component 4 sets up at template frame subassembly 3 between frame locator subassembly 5. The template frame assembly 3 is arranged corresponding to the front end of the airplane component and is used for positioning and fixing an outer frame at the front end of the airplane component; the frame locator component 5 is arranged corresponding to the rear end of the airplane component and is used for locating and fixing an outer frame at the rear end of the airplane component; the opening frame beam positioning assembly 4 is arranged corresponding to the opening frame beam in the middle of the airplane component and used for positioning and fixing the opening frame beam in the middle of the airplane component.
Meanwhile, a seat joint positioning assembly 9 is arranged on one side of the opening frame beam positioning assembly 4 corresponding to a seat on an airplane component, and a positioning fixing end of the seat joint positioning assembly 9 is arranged corresponding to a seat joint on the airplane component and used for positioning and fixing the seat in the middle of the airplane component.
Front end, middle part, rear end frame roof beam to aircraft part are fixed a position respectively through template frame subassembly 3, mouth frame roof beam locating component 4, frame locator subassembly 5 and are fixed a position, fix a position the seat at aircraft part middle part through seat joint locating component 9 simultaneously, and then realize the monolithic stationary to whole aircraft part. Then through the movement of the AGV moving platform 1, the whole stable and convenient transfer of the aircraft parts can be realized, and the form maintenance of the aircraft parts in the transfer process is effectively ensured.
Example 2:
this embodiment is further optimized on the basis of embodiment 1, as shown in fig. 4, the template frame assembly 3 includes a frame template 303 and a base 304, the base 304 is disposed at the front end of the top of the AGV moving platform 1, the top of the base 304 is provided with a frame template 303 for supporting the front end of the aircraft component, and a plurality of connecting members are disposed on one side of the frame template 303 close to the aircraft component corresponding to the connecting pin holes on the aircraft component.
The bottom of a base 304 is fixed at the front end of the top of an AGV moving platform 1 through bolts, a frame template 303 is arranged at the top of the base 304 corresponding to a frame beam at the front end of an aircraft component, one side, close to the frame beam, of the frame template 303 is used as a supporting surface for supporting the frame beam, meanwhile, a template frame threaded pin 301 is arranged on the frame template 303 corresponding to a locking pin hole in the frame beam, a template frame stepped pin 302 is arranged on the frame template 303 corresponding to a positioning pin hole in the frame beam, when the frame beam at the front end of the aircraft component is positioned and fixed on the frame template 303, the template frame stepped pin 302 is aligned with the positioning pin hole in the frame beam, then the aircraft component is moved so that the template frame stepped pin 302 is inserted into the positioning pin hole to achieve guiding positioning of the frame beam, at the moment, the template frame threaded pin 301 on the frame template 303 is synchronously inserted into the locking pin hole in.
By positioning the frame beam by the template frame stepped pin 302 and locking the frame beam by the template frame threaded pin 301, one side of the frame beam is attached and fixed to the supporting surface of the frame template 303, so that the frame beam at the front end of the aircraft component is supported and fixed on the frame template 303.
Further, in order to avoid interference between other structures or components on the frame beam at the front end of the aircraft component and the frame template 303, a plurality of avoidance holes for avoiding the other structures or components on the frame beam are arranged on the frame template 303.
Further, the number of the avoiding holes is four, and the four avoiding holes are circumferentially arranged on the frame template 303.
Furthermore, a flexible cushion is covered on the supporting surface of the frame template 303, so that the frame beam and the frame template 303 can be effectively prevented from being violently collided through the flexible cushion, and the frame template 303 or the frame beam is effectively prevented from being damaged.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
the present embodiment is further optimized on the basis of the foregoing embodiment 1 or 2, and as shown in fig. 5, the frame beam positioning assembly 4 includes a pressing device 401, a first connection support 402, and a second connection support 403, which are sequentially disposed from the front end to the rear end, the pressing device 401 is configured to press the front end of the middle frame beam of the aircraft component, and a plurality of connecting members are disposed on the first connection support 402 and the second connection support 403 corresponding to the connection pin holes on the middle frame beam of the aircraft component.
The both sides that correspond the front end of aircraft part middle part frame roof beam are provided with collet 401 respectively, collet 401 is including compressing tightly the supporting seat, compress tightly the mount pad, clamp bolt, compress tightly the bottom setting that the supporting seat corresponds aircraft part middle part frame roof beam and be used for supporting the middle part frame roof beam of aircraft part, one side of press supporting seat is provided with compresses tightly the mount pad, the erection end that compresses tightly the mount pad extends to the top that compresses tightly the supporting seat, and the downward through-thread of erection segment that compresses tightly the mount pad installs clamp bolt, place aircraft part middle part frame roof beam behind the top that compresses tightly the supporting seat, middle part frame roof beam is located between the erection end that compresses tightly the supporting seat and compress tightly the mount pad this moment, then rotate clamp bolt, make clamp bolt stretch out downwards and compress tightly middle part frame roof beam, realize.
First connection supporting seat 402 is arranged in the bottom that directly supports middle part frame roof beam or sets up a mouthful frame roof beam ladder round pin through the locating pin hole on the corresponding middle part frame roof beam in the top of first connection supporting seat 402, the locking pinhole on corresponding middle part frame roof beam in the top of second connection supporting seat 403 simultaneously sets up a mouthful frame roof beam screw thread round pin, when transferring middle part frame roof beam fixedly, a mouthful frame roof beam ladder round pin inserts and fixes a position the direction to transferring of middle part frame roof beam in the locating pin hole, a mouthful frame roof beam screw thread round pin inserts in the locking pinhole simultaneously, then rotate a mouthful frame roof beam screw thread round pin and realize the locking to the locking pinhole, and then effectively fix middle part frame roof beam.
The rest of this embodiment is the same as embodiment 1 or 2, and therefore, the description thereof is omitted.
Example 4:
this embodiment is further optimized on the basis of any one of the above embodiments 1-3, as shown in fig. 6, the frame positioner assembly 5 includes an assembly frame 501, an upper shape positioning block 502, a middle shape positioning block 503 and a lower shape positioning block 504, the assembly frame 501 is disposed at the rear end of the top of the AGV moving platform 1, the upper shape positioning block 502 is symmetrically disposed at two ends of the top of the assembly frame 501, the middle position of the top of the assembly frame 501 is disposed with the middle shape positioning block 503, and the lower shape positioning block 504 is symmetrically disposed at two ends of the bottom of the assembly frame 501.
Frame locator subassembly 5 corresponds the interior profile setting of aircraft part rear end frame roof beam, subassembly skeleton 501 sets up the inboard at aircraft part rear end frame roof beam, the top of subassembly skeleton 501 extends to the inboard top of rear end frame roof beam, and the both ends of subassembly skeleton 501 correspond the interior profile of rear end frame roof beam respectively and be provided with upper portion appearance locating piece 502, the locating surface of upper portion appearance locating piece 502 is tightly fixed with the inboard top of rear end frame roof beam, the positioning groove on the profile is provided with middle part appearance locating piece 503 in the central authorities at subassembly skeleton 501's top correspond the rear end frame roof beam simultaneously, positioning groove block on the profile is blocked in middle part appearance locating piece 503 and the rear end frame roof beam, and then realize the convenient location to rear end frame roof beam. Meanwhile, lower contour positioning blocks 504 are arranged at two ends of the bottom of the assembly framework 501 corresponding to the inner contour of the rear end frame beam, and the lower sides of the inner contours of the rear end frame beam are tightly supported and fixed by the positioning surfaces of the lower contour positioning blocks 504.
Other parts of this embodiment are the same as any of embodiments 1 to 3, and thus are not described again.
Example 5:
the present embodiment is further optimized on the basis of any one of embodiments 1 to 4, as shown in fig. 10, the seat joint positioning assembly 9 includes a seat positioning pin 901, a seat joint 902, and an assembly supporting column 903, the assembly supporting column 903 is disposed between the frame positioning assembly 4 and the frame positioner assembly 5, the seat joint 902 is disposed on the top and the side of the assembly supporting column 903, one end of the seat joint 902 away from the assembly supporting column 903 is a U-shaped connecting seat, and the seat positioning pin 901 penetrates through the U-shaped connecting seat.
The top and the side of the component support column 903 are provided with a seat joint 902 corresponding to the top joint and the side joint of the seat, respectively, one end of the seat joint 902 is a connecting plate provided with two fixing pin holes, and the other end of the seat joint 902 is a U-shaped connecting seat corresponding to the joint on the seat. The position that corresponds the connecting plate is provided with the connection base on the top and the side of subassembly support column 903, be provided with on one side that the connection base is close to the connecting plate and be parallel to each other and leave gapped connecting plate, it is provided with the mounting hole to correspond the fixed pinhole on the connecting plate to connect the bottom plate, through with connecting plate cartridge to two connecting plate between the clearance, and make the fixed pinhole on the connecting plate align with the mounting hole on the connecting plate, and insert the bolt in a set of fixed pinhole and mounting hole, insert the round pin axle in another group's fixed pinhole and mounting hole, and then realize that the installation of seat joint 902 on the connection base is fixed.
The U-shaped connecting seat is provided with a mounting pin hole corresponding to the connecting pin hole of the upper joint of the seat, the joint of the seat is clamped in the U-shaped cavity of the U-shaped connecting seat, and then a seat positioning pin 901 is inserted into the connecting pin hole and the mounting pin hole, so that the seat is positioned and fixed.
Other parts of this embodiment are the same as any of embodiments 1 to 4, and thus are not described again.
Example 6:
the present embodiment is further optimized on the basis of any one of the above embodiments 1 to 4, and as shown in fig. 1, the present embodiment further includes a swash plate positioning assembly 8 for fixing a plate rib of an aircraft component, a joint positioning assembly 11 for fixing a joint of the aircraft component, and a profile positioning assembly 12 for fixing a profile of the aircraft component, wherein the swash plate positioning assembly 8 is disposed near one side of the template frame assembly 3, the joint positioning assembly 11 is disposed near one side of the seat joint positioning assembly 9, and the profile positioning assembly 12 is disposed near the mouth frame beam positioning assembly 4.
The inclined plate positioning component 8 is arranged corresponding to the inclined plate at the bottom of the front end of the airplane component and is used for positioning and fixing the inclined plate; the joint positioning assembly 11 is arranged corresponding to a joint in the middle of an airplane component and is used for positioning and fixing the joint in the middle of the airplane component; at least two groups of section positioning assemblies 12 are symmetrically arranged on two sides of the center of the top of the AGV moving platform 1 and used for supporting and fixing the middle frame beam of the aircraft component.
Other parts of this embodiment are the same as any of embodiments 1 to 5, and thus are not described again.
Example 7:
this embodiment is further optimized on the basis of any one of the above embodiments 1-4, as shown in fig. 9, the swash plate positioning assembly 8 includes a swash plate side positioning element 801 and a swash plate middle positioning element 803, the swash plate middle positioning element 803 is disposed corresponding to the middle of the front end swash plate of the aircraft component, the swash plate middle positioning element 803 is provided with a fixed wedge block 802 for fixing the middle of the front end swash plate of the aircraft component, the two sides of the swash plate middle positioning element 803 are symmetrically provided with swash plate side positioning elements 801, and the top of the swash plate side positioning element 801 is provided with a connecting element for fixing two sides of the front end swash plate of the aircraft component.
The middle part that corresponds the swash plate is provided with swash plate middle part locating component 803, the middle part that corresponds the swash plate on the location end of swash plate middle part locating component 803 is provided with fixed voussoir 802, one side that fixed voussoir 802 is close to the swash plate middle part is the support fixed surface, the inclination of the support fixed surface of fixed voussoir 802 is the same with the inclination of swash plate, and the connection pinhole that corresponds the swash plate middle part on the support fixed surface of fixed voussoir 802 is provided with the fixed orifices, the both sides that support the fixed surface of fixed voussoir 802 correspond the swash plate middle part bead and are provided. When the inclined plate is fixed, the side face of the inclined plate is in contact with the supporting and fixing face of the fixed wedge block 802, the convex edges in the middle of the inclined plate are correspondingly inserted into the grooves, then the fixing pins are inserted into the aligned connecting pin holes and the fixing holes, and the middle of the inclined plate is fixedly positioned.
The both sides that correspond the swash plate are provided with swash plate side setting element 801 in the bilateral symmetry of middle part locating component 803 respectively, the location end of swash plate side setting element 801 is provided with the support stationary plane with the slope that swash plate inclination is the same, it is provided with the fixed screw round pin to correspond the locking pinhole on the swash plate on the support stationary plane, place the swash plate on the support stationary plane of swash plate side setting element 801, make the side and the support stationary plane contact of swash plate, make simultaneously in the locking pinhole of fixed screw round pin cartridge to the swash plate, then rotate the fixed screw round pin and lock the locking pinhole, and then realize the location fixed to the swash plate both sides.
Other parts of this embodiment are the same as any of embodiments 1 to 6, and thus are not described again.
Example 8:
the present embodiment is further optimized on the basis of any one of embodiments 1 to 4, as shown in fig. 12, the joint positioning assembly 11 includes a positioning head 111, a joint positioning pin 112, a joint cylindrical pin 113, and a joint positioning pillar 114, the joint positioning pillar 114 is disposed near one side of the seat joint positioning assembly 9, the positioning head 111 is disposed on the top of the joint positioning pillar 114, and the joint positioning pin 112 and the joint cylindrical pin 113 are disposed at two ends of the positioning head 111, respectively.
The joint positioning component 11 is arranged corresponding to a joint on a middle frame beam of an aircraft component, the joint positioning strut 114 is arranged at the top of the AGV moving platform 1 and is positioned at one side of the seat joint positioning component 9, the top of the joint positioning strut 114 extends to one side of the joint on the middle frame beam, the top of the joint positioning strut 114 is connected with the positioning head 111 through a connecting seat, one end of the positioning head 111 extends to one side of the joint of the middle frame beam and is provided with a cylindrical pin hole, the other end of the positioning head 111 is provided with a mounting hole corresponding to the positioning pin hole on the middle frame beam, a joint cylindrical pin 113 is inserted in the cylindrical pin hole, one end of the joint cylindrical pin 113 extends into the cylindrical pin hole of the joint of the middle frame beam, positioning and fixing of the joint of the middle frame beam are realized, meanwhile, the joint positioning pin 112 is inserted in the mounting hole at the other end of, the middle frame beam is positioned.
Other parts of this embodiment are the same as any of embodiments 1 to 7, and thus are not described again.
Example 9:
this embodiment is further optimized on the basis of any one of the above embodiments 1-4, as shown in fig. 13, the profile positioning assembly 12 includes a positioning pressing plate 121, profile positioning pillars 122, and butterfly pressing nuts 123, the profile positioning pillars 122 are disposed on two sides of the top of the AGV moving platform 1, the positioning pressing plate 121 is slidably disposed on the top of the profile positioning pillars 122, adjusting chutes are disposed on two sides of the positioning pressing plate 121, and the butterfly pressing nuts 123 are threadedly mounted on the top of the positioning pressing plate 121.
Section bar location pillar 122 includes vertical section and slope section, the bottom setting of vertical section is at AGV moving platform 1 top, the top of vertical section is connected with the one end of slope section, the both sides of slope section are provided with the spout along length direction, the bottom of positioning pressure plate 121 corresponds the spout and is provided with the slider, sliding connection through slider and spout realizes that positioning pressure plate 121 slides at the top of slope section along the length direction of slope section to the realization is to positioning pressure plate 121's position control. Meanwhile, a locking threaded hole is formed in the positioning pressing plate 121, a locking bolt extending into the sliding groove is arranged in the locking threaded hole, and after the position of the positioning pressing plate 121 is adjusted, the locking bolt is screwed down to fix the position of the positioning pressing plate 121.
A butterfly compression nut 123 is further installed on the positioning pressing plate 121 in a threaded mode, when the butterfly compression nut 123 is not compressed, a gap is reserved between a compression surface of the butterfly compression nut 123 and a top positioning surface of the positioning pressing plate 121 to enable the section on the frame beam to enter, and when the section is placed in place, the butterfly compression nut 123 is rotated, so that the compression surface of the butterfly compression nut 123 and the top positioning surface of the positioning pressing plate 121 clamp and fix the section.
Furthermore, the bilateral symmetry of positioning pressure plate 121 is provided with the regulation constant head tank, and positioning pressure plate 121 is "worker" font structure promptly, and the bead on the section bar slides along adjusting the constant head tank with adjusting the constant head tank joint, realizes finely tuning and location to the section bar fixed position.
Other parts of this embodiment are the same as any of embodiments 1 to 8, and thus are not described again.
Example 10:
this embodiment is further optimized on the basis of any of the above embodiments 1 to 4, wherein a lock pin jig assembly 6 is disposed on one side of the stencil frame assembly 3, and a front jig assembly 7 is disposed on the other side of the stencil frame assembly 3; a rear drill jig assembly 13 is arranged between the frame beam positioning assembly 4 and the frame positioner assembly 5.
As shown in fig. 7, the lock pin jig assembly 6 includes a lock pin jig plate 601, a lock pin support base 602, a lock pin shaft 603, and a lock pin 604, the lock pin support base 602 is fixedly mounted on one side of the template frame assembly 3 through a bolt, one end of the lock pin support base 602, which is away from the template frame assembly 3, is provided with a U-shaped groove, one end of the lock pin jig plate 601 is provided with an insert plate corresponding to the U-shaped groove, the insert plate is provided with a lock pin shaft hole and a lock pin hole, the side wall of the U-shaped groove is provided with a lock pin shaft through hole and a lock pin through hole corresponding to the lock pin shaft hole and the lock pin hole, the lock pin 603 is inserted in the lock pin shaft hole and the lock pin through hole, and the lock pin 604 is inserted in the lock.
One end of the lock pin drill plate 601, which is far away from the lock pin support seat 602, is provided with a drill hole guide sleeve corresponding to the drill hole position at the front end of the aircraft component, and after the position of the lock pin drill plate 601 is fixed, a drill bit can be guided through the drill hole guide sleeve, so that the aircraft component can be guided to drill holes.
As shown in fig. 8, the front drill jig assembly 7 includes an upper drill jig plate 701, a front drill jig support 702, a front drill jig connecting member 703, and a lower drill jig plate 704, the front drill jig support 702 is symmetrically disposed at two ends of the top of the side of the template frame assembly 3, one end of the front drill jig support 702 close to the aircraft component is fixedly connected with the upper drill jig plate 701, and one end of the upper drill jig plate 701, which is far away from the front drill jig support 702, is provided with a drilling guide sleeve corresponding to a frame beam, a rib plate, and other positions of the aircraft component, which need to be drilled.
The front drill jig connecting pieces 703 are symmetrically arranged at two ends of the bottom of the side face of the template frame component 3, one end of each front drill jig connecting piece 703 close to the aircraft component is fixedly connected with a lower drill jig plate 704, and one end, far away from the front drill jig connecting pieces 703, of the lower drill jig plate 704 is provided with a drilling guide sleeve corresponding to the positions, needing drilling, of frame beams, rib plates and the like of the aircraft component.
As shown in fig. 14, the rear jig assembly 13 includes a rear jig support 131, a rear jig angle seat 132, a rear jig drilling plate 133, the bottom of the rear jig support 131 is fixedly connected with the top of the AGV moving platform 1, the top of the rear jig support 131 is fixedly provided with the rear jig angle seat 132, the rear jig drilling plate 133 is installed at the end of the rear jig support 132 far away from the rear jig support 131, the end of the rear jig drilling plate 133 far away from the rear jig angle seat 132 is a U-shaped positioning groove corresponding to the rear frame beam mold, a locking threaded hole is formed in the side wall of the U-shaped positioning groove, and after the rear frame beam mold is installed in the U-shaped positioning groove, a locking bolt is screwed into the locking threaded hole in the side wall of the U-shaped positioning groove, so that the threaded end of the locking bolt tightly pushes up the side surface of the rear frame beam mold, and the positioning and fixing of the.
The drill bit is guided through the drill hole guide sleeve, and then guide drilling is carried out in the areas of frame beams, rib plates and the like of the airplane parts.
Other parts of this embodiment are the same as any of embodiments 1 to 9, and thus are not described again.
Example 11:
the present embodiment is further optimized on the basis of any one of the foregoing embodiments 1 to 10, as shown in fig. 1 to 3, the AGV moving platform 1 includes a supporting platform 01, an AGV moving carrier 02, and a docking positioning assembly 2, the docking positioning assembly 2 includes a fast-joint mother disc 201 disposed at four corners of the top of the AGV moving carrier 02, a fast-joint sub disc 202 is disposed at a position, corresponding to the fast-joint mother disc 201, of the top of the supporting platform 01, a female slot is disposed on the fast-joint mother disc 201, a sub plug-in block inserted into the female slot is disposed on the fast-joint sub disc 202, and by inserting the sub plug-in block into the female slot, convenient installation of the supporting platform 01 at the top of the AGV moving carrier 02 is further achieved. Meanwhile, Mecanum wheels 203 are arranged at four corners of the bottom of the AGV moving loading vehicle 02, so that the AGV moving loading vehicle 02 can move conveniently.
Furthermore, the four corners of the top of the AGV 02 are provided with positioning columns 204, the top of the positioning column 204 is provided with zero point positioning contacts 205, the four corners of the bottom of the supporting platform 01 are provided with positioning holes corresponding to the positioning columns 204 and the zero point positioning contacts 205, and the supporting platform 01 is inserted into the positioning holes through the positioning columns 204 and the zero point positioning contacts 205, so that the supporting platform 01 can be conveniently positioned in the AGV 02.
Other parts of this embodiment are the same as any of embodiments 1 to 10 described above, and thus are not described again.
Example 12:
the embodiment is further optimized on the basis of any one of the above embodiments 1 to 11, and as shown in fig. 11, the AGV moving platform further includes beam positioning assemblies 10 disposed on two sides of the top of the AGV moving platform 1, each beam positioning assembly 10 includes beam limiting seats symmetrically disposed on two sides of the top of the AGV moving platform 1, a limiting vertical plate is disposed at the top of each beam limiting seat corresponding to the outer contour of a beam of an aircraft component, and after the beam is placed between two adjacent beam limiting seats, the side surface of the beam contacts with one side of the limiting vertical plate or has a small gap, and the beam is limited by the limiting vertical plate.
Furthermore, the width between the adjacent beam limiting seats is larger than or equal to the width of the cross beam of the aircraft component.
Other parts of this embodiment are the same as any of embodiments 1 to 11, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (10)
1. The utility model provides an aircraft parts transports guarantor type device, includes AGV moving platform (1), its characterized in that, AGV moving platform (1)'s the top the front end to the rear end set gradually template frame subassembly (3), the mouth frame roof beam locating component (4) that are used for fixed aircraft parts middle part frame roof beam, be used for fixed aircraft parts rear end frame locator subassembly (5), still correspond the seat on the aircraft parts on AGV moving platform (1) and be provided with seat joint locating component (9).
2. The aircraft component transportation shape keeping device of claim 1, wherein the template frame assembly (3) comprises a frame template (303) and a base (304), the base (304) is arranged at the front end of the top of the AGV moving platform (1), the top of the base (304) is provided with the frame template (303) used for supporting the front end of the aircraft component, and a plurality of connecting pieces are arranged on one side, close to the aircraft component, of the frame template (303) corresponding to connecting pin holes in the aircraft component.
3. The aircraft component transportation shape-keeping device according to claim 1, wherein the frame beam positioning assembly (4) comprises a pressing device (401), a first connection support (402) and a second connection support (403) which are sequentially arranged from the front end to the rear end, the pressing device (401) is used for pressing the front end of the middle frame beam of the aircraft component, and a plurality of connecting pieces are arranged on the first connection support (402) and the second connection support (403) corresponding to the connecting pin holes on the middle frame beam of the aircraft component.
4. The aircraft component transportation shape-keeping device of claim 1, wherein the frame positioner assembly (5) comprises an assembly framework (501), an upper shape positioning block (502), a middle shape positioning block (503) and a lower shape positioning block (504), the assembly framework (501) is arranged at the rear end of the top of the AGV moving platform (1), the upper shape positioning block (502) is symmetrically arranged at two ends of the top of the assembly framework (501), the middle position of the top of the assembly framework (501) is provided with the middle shape positioning block (503), and the lower shape positioning block (504) is symmetrically arranged at two ends of the bottom of the assembly framework (501).
5. The aircraft component transportation shape keeping device of claim 1, wherein the seat joint positioning assembly (9) comprises a seat positioning pin (901), a seat joint (902) and an assembly supporting column (903), the assembly supporting column (903) is arranged between the mouth frame beam positioning assembly (4) and the frame positioner assembly (5), the seat joint (902) is arranged on the top and the side of the assembly supporting column (903), one end of the seat joint (902), which is far away from the assembly supporting column (903), is a U-shaped connecting seat, and the seat positioning pin (901) is arranged on the U-shaped connecting seat in a penetrating manner.
6. The aircraft component transfer shape keeping device according to any one of claims 1-5, further comprising a sloping plate positioning component (8) for fixing the aircraft component plate rib, a joint positioning component (11) for fixing the aircraft component joint, and a profile positioning component (12) for fixing the aircraft component profile, wherein the sloping plate positioning component (8) is arranged near one side of the template frame component (3), the joint positioning component (11) is arranged near one side of the seat joint positioning component (9), and the profile positioning component (12) is arranged near the mouth frame beam positioning component (4).
7. The transportation shape-preserving device for aircraft components as claimed in claim 6, wherein the swash plate positioning assembly (8) comprises a swash plate side positioning element (801) and a swash plate middle positioning element (803), the swash plate middle positioning element (803) is arranged corresponding to the middle of the front end swash plate of the aircraft component, a fixed wedge block for fixing the middle of the front end swash plate of the aircraft component is arranged on the swash plate middle positioning element (803), swash plate side positioning elements (801) are symmetrically arranged on two sides of the swash plate middle positioning element (803), and connecting elements for fixing two sides of the front end swash plate of the aircraft component are arranged on the top of the swash plate side positioning element (801).
8. The aircraft component transportation shape-keeping device according to claim 6, wherein the joint positioning assembly (11) comprises a positioning head (111), a joint positioning pin (112), a joint cylindrical pin (113) and a joint positioning strut (114), the joint positioning strut (114) is arranged close to one side of the seat joint positioning assembly (9), the positioning head (111) is arranged at the top of the joint positioning strut (114), and the joint positioning pin (112) and the joint cylindrical pin (113) are respectively arranged at two ends of the positioning head (111).
9. The aircraft component transportation shape-keeping device of claim 6, wherein the profile positioning assembly (12) comprises a positioning pressing plate (121), profile positioning pillars (122) and butterfly pressing nuts (123), the profile positioning pillars (122) are arranged on two sides of the top of the AGV moving platform (1), the positioning pressing plate (121) is arranged on the top of the profile positioning pillars (122) in a sliding mode, adjusting sliding grooves are arranged on two sides of the positioning pressing plate (121), and the butterfly pressing nuts (123) are installed on the top of the positioning pressing plate (121) in a threaded mode.
10. The aircraft component transfer shape keeping device of any one of claims 1-5, wherein a lockpin jig assembly (6) is provided on one side of the template frame assembly (3), and a front jig assembly (7) is provided on the other side of the template frame assembly (3); and a rear drill jig component (13) is arranged between the frame beam positioning component (4) and the frame positioner component (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010577602.9A CN111824451B (en) | 2020-06-23 | 2020-06-23 | Aircraft part transports guarantor type device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010577602.9A CN111824451B (en) | 2020-06-23 | 2020-06-23 | Aircraft part transports guarantor type device |
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| Publication Number | Publication Date |
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| CN111824451A true CN111824451A (en) | 2020-10-27 |
| CN111824451B CN111824451B (en) | 2021-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010577602.9A Active CN111824451B (en) | 2020-06-23 | 2020-06-23 | Aircraft part transports guarantor type device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114253290A (en) * | 2021-12-15 | 2022-03-29 | 成都飞机工业（集团）有限责任公司 | Method and system for automatic tracking and accurate positioning of airplane component transport vehicle |
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| CN114253290B (en) * | 2021-12-15 | 2024-03-19 | 成都飞机工业（集团）有限责任公司 | Method and system for automatic tracking and accurate positioning of airplane component transport vehicle |
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|---|---|
| CN111824451B (en) | 2021-09-07 |
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