A welding jig for repairing a commercial aircraft component

Abstract

This invention discloses a welding fixture for the maintenance of commercial aircraft parts, including a welding fixture base, positioning components, and clamping components. The welding fixture base has an internal oil reservoir, and the top of the oil reservoir has multiple cylindrical grooves formed within the base. Each positioning component includes a piston cylinder, a connecting support, a support column, and a support rod. A rubber sleeve is sleeved onto the top of the support rod. This invention utilizes hydraulic oil within the oil reservoir to support the multiple positioning components mounted within the cylindrical grooves. When an aircraft part is placed on the top of the support rod on the positioning components, the rubber sleeve on the top of the support rod adheres to the bottom surface of the aircraft part. The aircraft part's own weight applies pressure to the multiple positioning components simultaneously, automatically adjusting the hydraulic oil support to different heights to fit the shape of the aircraft part's bottom. Subsequent simple clamping is sufficient for fixation, eliminating the need for a dedicated welding fixture.

Description

Technical Field

[0001] This invention relates to the field of welding fixtures for aircraft parts, and more particularly to a welding fixture for the maintenance of commercial aircraft parts. Background Technology

[0002] Aircraft components mainly include airframe parts, power systems, avionics, airborne equipment, and other components. The production of these aircraft components widely uses metallic materials (such as titanium alloys, aluminum alloys, stainless steel, structural steel, high-temperature alloys, etc.), and also includes some non-metallic materials and composite materials (such as aerospace ceramics, special rubbers, carbon fibers, etc.).

[0003] For metal materials used to manufacture parts, the conventional connection methods mainly include three types: bolt assembly, riveting assembly, and welding. During the welding process, welding fixtures are needed to fix the parts to be processed to ensure that the parts do not shake during the welding process.

[0004] In the current process of welding aircraft parts, special fixtures are used to match the shape of the parts and ensure the stability of the parts clamping. However, in actual applications, due to the different types and sizes of aircraft parts, a single special fixture is difficult to meet the welding and fixing work of various aircraft parts. At the same time, the use of different fixtures for different aircraft parts results in a large variety of fixtures and a large footprint.

[0005] A welding fixture for processing aircraft parts (publication number CN222370776U) uses a mounting plate and its upper limit assembly to drive the clamping platform to move up and down through the electric cylinder seat on the limit assembly. This places the component to be welded between two sets of clamping platforms and stably clamps the component by moving the height of the two sets of clamping platforms. The fixture has a simple structure, good clamping effect, and can adjust the rotation angle of the component by rotating the limit assembly to ensure welding accuracy. This fixture also addresses the aforementioned issues to some extent.

[0006] Therefore, how to provide a welding fixture for the repair of commercial aircraft parts is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0007] One objective of this invention is to provide a welding fixture for the maintenance of commercial aircraft parts. This fixture supports multiple positioning components mounted inside multiple cylindrical grooves using hydraulic oil within an oil reservoir. When an aircraft part is placed on the top of a support rod on one of the positioning components, the rubber sleeve on the top of the support rod adheres to the bottom surface of the aircraft part. The aircraft part, due to its own weight, simultaneously applies pressure to the multiple positioning components. By sliding a piston cylinder inside the cylindrical grooves, the hydraulic oil automatically adjusts the positioning components to different heights to match the shape of the aircraft part's bottom. Subsequent simple clamping and fixing of the components is sufficient, eliminating the need for a dedicated welding fixture and saving space. Meanwhile, the end of the lap arm away from the clamping support overlaps the top of the aircraft component, and the bottom surface of the clamping head is in contact with the surface of the aircraft component. When an external force forces the aircraft component to tilt from top to bottom, because the clamping head is installed at the end of the lap arm away from the clamping support, the clamping rod at the bottom of the clamping support tends to rotate around the rotating seat, preventing the clamping rod from sliding inside the rotating seat. This helps to keep the aircraft component in a clamped state and can solve the problem that in the actual application of existing special fixtures for aircraft parts, due to the different types and sizes of aircraft parts, a single special fixture is difficult to meet the welding and fixing work of various aircraft parts. At the same time, using corresponding fixtures for different aircraft parts results in a large number of types and a large footprint.

[0008] According to an embodiment of the present invention, a welding fixture for repairing commercial aircraft parts includes a welding fixture base, a positioning component and a clamping component. Multiple positioning components are provided, and all of them extend from the inside of the welding fixture base to the top. Multiple clamping components are provided, all of which are located at the top edge; The welding fixture base has an oil storage cavity inside, and the top of the oil storage cavity is provided with multiple cylindrical grooves opened inside the welding fixture base. The interior of the oil storage cavity and the interior of the multiple cylindrical grooves are connected. Each of the positioning components includes a piston cylinder, a connecting support is provided inside the piston cylinder, a supporting column is provided on the top of the connecting support, a supporting rod is welded to the top of the supporting column, and a rubber sleeve is sleeved to the top of the supporting rod. The aircraft component is placed on the top of a support rod on multiple positioning components. The aircraft component applies pressure to multiple positioning components simultaneously due to its own weight. With the help of a piston cylinder sliding inside a cylindrical groove, the hydraulic oil is automatically adjusted to support multiple positioning components at different heights.

[0009] Preferably, each of the multiple cylindrical grooves is provided with multiple limiting sleeves, and each of the multiple limiting sleeves is provided with an oil flow groove; the inside of the oil flow groove is connected to the inside of the oil storage cavity, and the piston cylinder is movably connected to the top of the limiting sleeve.

[0010] Preferably, the top of the connecting support is provided with a storage slot, and the inner walls on both sides of the storage slot are machined with first limiting slots. The bottom of the support column is provided with second limiting slots on both sides. The connecting support is internally connected with a limiting pin. The bottom of the support column is interference-fitted into the inside of the storage slot, and the limiting pin is inserted into the storage slot between the first limiting slot and the second limiting slot.

[0011] Preferably, the connecting support has abutment strips welded to both sides of the middle part, and a limit rod is pin-connected inside the connecting support. Both ends of the limit rod are provided with retaining rings. The connecting support is inserted into the piston cylinder, and the retaining rings are engaged with the inside of the piston cylinder.

[0012] Preferably, a second movable groove area is machined at the center of each of the two short sides of the welding fixture base, and two first movable groove areas are machined at each of the two long sides of the welding fixture base; the cross-sections of the first and second movable groove areas are both isosceles trapezoids, and the two first movable groove areas on one long side of the welding fixture base are symmetrical about the center of the welding fixture base.

[0013] Preferably, the two first movable groove areas divide the top of the welding fixture base into a central area located between the two first movable groove areas, a transition area corresponding to the two first movable groove areas, and an edge area located between the first movable groove areas and the positioning component.

[0014] Preferably, each of the plurality of clamping components includes a clamping upright, the top of which is fitted with a clamping support, the inner side of which is provided with an overlapping arm, and the end of the overlapping arm away from the clamping upright is fitted with a clamping head. Outward-extending corner plates are assembled and connected to the four corners of the welding fixture base, and outward-extending side plates are assembled and connected to the two long sides of the welding fixture base; the clamping uprights on the multiple clamping assemblies are respectively inserted into the interior of the outward-extending side plates and outward-extending corner plates, and the overlapping arm supports the clamping head to overlap the top of the aircraft component.

[0015] Preferably, a clamping handle is hinged to one corner of the top of the clamping support, and a transition block is hinged between the middle of the clamping handle and the overlapping arm; one end of the overlapping arm passes through the inside of the clamping handle and is hinged to the other corner of the top of the clamping support.

[0016] Preferably, the clamping upright is externally connected to a rotating seat, and the top and bottom of the rotating seat are both interference-fitted with bearings. The rotating seat is externally connected to a limiting seat. The limiting seat is assembled to the bottom of the outward-extending corner plate or the outward-extending side plate. The bearing at the bottom of the rotating seat is interference-fitted to the inside of the limiting seat, and the bearing at the top of the rotating seat is interference-fitted to the inside of the outward-extending corner plate or the outward-extending side plate.

[0017] Preferably, the surface of the clamping rod is machined with a straight cut surface parallel to its axis, and the interior of the rotating seat is provided with a strip groove; the clamping rod is slidably connected to the interior of the rotating seat, and the clamping rod is adapted to the interior of the rotating seat through the straight cut surface.

[0018] The beneficial effects of this invention are: This invention utilizes hydraulic oil within an oil reservoir to support multiple positioning components mounted within multiple cylindrical slots. When an aircraft component is placed on top of a support rod on one of these positioning components, the rubber sleeve at the top of the support rod adheres to the bottom surface of the aircraft component. Due to its own weight, the aircraft component simultaneously applies pressure to the multiple positioning components. By sliding a piston cylinder within the cylindrical slots, the hydraulic oil automatically adjusts the multiple positioning components to different heights to match the shape of the aircraft component's bottom. Subsequently, only simple clamping and fixing of the components is required, eliminating the need for specialized welding fixtures and saving space occupied by fixtures. This invention involves attaching the end of the overlapping arm away from the clamping support to the top of the aircraft component, with the bottom surface of the clamping head in contact with the surface of the aircraft component. When an external force forces the aircraft component to tilt from top to bottom, because the clamping head is installed at the end of the overlapping arm away from the clamping support, the clamping rod at the bottom of the clamping support tends to rotate around the rotating seat, preventing the clamping rod from sliding inside the rotating seat, thus helping to keep the aircraft component in a clamped state. Attached Figure Description

[0019] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings: Figure 1 This is a schematic diagram of the structure of a welding fixture for repairing commercial aircraft parts proposed in this invention; Figure 2 This is a top view of a welding fixture for repairing commercial aircraft parts proposed in this invention; Figure 3 This is a schematic diagram of the positioning assembly of a welding fixture for the maintenance of commercial aircraft parts proposed in this invention; Figure 4 This is a cross-sectional view of the piston cylinder of a welding fixture for repairing commercial aircraft parts, as proposed in this invention. Figure 5 This is a cross-sectional view of the base of a welding fixture for the maintenance of commercial aircraft parts, as proposed in this invention. Figure 6 This is a schematic diagram of the structure of a welding fixture clamping assembly for repairing commercial aircraft parts, as proposed in this invention. Figure 7 This invention proposes a welding fixture for the repair of commercial aircraft parts. Figure 6 Enlarged diagram of section A in the middle; Figure 8 This invention proposes a welding fixture for the repair of commercial aircraft parts. Figure 6 Enlarged view of section B; Figure 9 This is a front view of a welding fixture clamping assembly for the repair of commercial aircraft parts proposed in this invention.

[0020] In the picture: 1. Welding fixture base; 2. Cylindrical groove; 3. Positioning assembly; 301. Piston cylinder; 302. Connecting support; 303. Abutment strip; 304. Limiting pin; 305. Support column; 306. Support rod; 307. Rubber sleeve; 308. Snap ring; 309. Limiting rod; 4. First active tank area; 5. Clamping assembly; 501. Clamping upright; 502. Clamping support; 503. Clamping handle; 504. Overlapping arm; 505. Clamping head; 506. Adapter block; 6. Outward-facing side plate; 7. Second movable groove area; 8. Outward-facing corner plate; 9. First limiting groove; 10. Second limiting groove; 11. Receiving groove; 12. Limiting sleeve; 13. Oil channel opening; 14. Oil storage cavity; 15. Strip groove; 16. Bearing; 17. Straight cut surface; 18. Rotary seat; 19. Limiting buckle seat. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0022] Example 1: The technical solution in this application is to address the problem that, in practical applications, a single dedicated jig is insufficient to meet the welding and fixing needs of various aircraft parts due to their different types and sizes. Furthermore, using different jigs for different aircraft parts results in a large variety of jigs and requires significant space. The overall approach is as follows: To address the problems existing in the prior art, this invention provides a schematic diagram of a welding fixture for the maintenance of commercial aircraft parts, with reference to... Figures 1 to 5 As shown, the welding fixture base 1, multiple positioning components 3 and multiple clamping components 5 are provided. The welding fixture base 1 has an oil storage cavity 14 inside. The top of the oil storage cavity 14 is provided with multiple cylindrical grooves 2 opened inside the welding fixture base 1. The inside of the oil storage cavity 14 and the inside of the multiple cylindrical grooves 2 are connected. Multiple positioning components 3 each include a piston cylinder 301. A connecting support 302 is provided inside the piston cylinder 301. A supporting column 305 is provided on the top of the connecting support 302. A supporting rod 306 is welded to the top of the supporting column 305. A rubber sleeve 307 is sleeved to the top of the supporting rod 306. Among them, multiple positioning components 3 extend from the inside of the welding fixture base 1 to the top, and multiple clamping components 5 are set at the top edge. When the aircraft part is placed on the top of the support rod 306 on the multiple positioning components 3, the aircraft part applies pressure to the multiple positioning components 3 simultaneously due to its own weight. With the help of the piston cylinder 301 sliding inside the cylindrical groove 2, the hydraulic oil automatically adjusts to support the multiple positioning components 3 to different heights to adapt to the shape of the bottom of the aircraft part. For large aircraft parts (based on the large passenger capacity and large size of commercial aircraft), it can stably support the aircraft parts. Afterwards, only simple fixation of the clamping components 5 is required, without the need for a special welding and fixing fixture. Meanwhile, for small aircraft parts, multiple positioning components 3 apply pressure simultaneously using their own weight, and the piston cylinder 301 slides inside the cylindrical groove 2 to automatically adjust the hydraulic oil to support multiple positioning components 3 to different heights to adapt to the shape of the bottom of the aircraft parts. In conjunction with the limiting of multiple clamping components 5, the aircraft parts can be fixed. Secondly, in order to fix the support column 305 to the top of the connecting bracket 302 and maintain its characteristics of easy disassembly and few parts, such as Figure 4As shown, the top of the connecting support 302 is provided with a storage slot 11, and the inner walls on both sides of the storage slot 11 are machined with first limiting slots 9. The bottom of the support column 305 is provided with second limiting slots 10 on both sides. The internal pin connection of the connecting support 302 is a limiting pin 304. By making the bottom of the support column 305 interference fit into the inside of the storage slot 11, when the limiting pin 304 is inserted into the storage slot 11 between the first limiting slot 9 and the second limiting slot 10, the limiting pin 304 can be used to restrict the support column 305 from disengaging from the connecting support 302 in the vertical direction. With the bottom of the support column 305 interference fit into the inside of the storage slot 11, the support column 305 can only be disengaged from the connecting support 302 from one direction. The accessories used to connect the support column 305 and the connecting support 302 are few, and it is easy to keep the support column 305 in an easy-to-disassemble state. Furthermore, to ensure the connection stability between the limit rod 309 and the piston cylinder 301, such as Figure 4 As shown, abutment bars 303 are welded to both sides of the middle part of the connecting support 302. A limit rod 309 is pin-connected inside the connecting support 302. Both ends of the limit rod 309 are provided with retaining rings 308. By inserting the connecting support 302 into the inside of the piston cylinder 301, the retaining rings 308 are engaged with the inside of the piston cylinder 301. The two retaining rings 308 are used to restrict the movement of the limit rod 309 along its axis. Meanwhile, by inserting the connecting support 302 into the inside of the piston cylinder 301, and after the limiting rod 309 is pinned to the inside of the piston cylinder 301 and the connecting support 302, the connecting support 302 can be fixed to the top of the piston cylinder 301. In some examples, a second movable groove area 7 is machined at the center of the two short sides of the welding fixture base 1, and two first movable groove areas 4 are machined at the two long sides of the welding fixture base 1. By setting a first movable groove area 4 and a second movable groove area 7 with an isosceles trapezoidal cross section, and making the two first movable groove areas 4 on one long side of the welding fixture base 1 symmetrical about the center of the welding fixture base 1, when the two first movable groove areas 4 divide the top of the welding fixture base 1 into a central area between the two first movable groove areas 4, a transition area corresponding to the two first movable groove areas 4, and an edge area between the first movable groove area 4 and the positioning component 3, it is possible for workers or welding equipment to approach the aircraft parts at the second movable groove area 7 or the first movable groove area 4. In some examples, multiple cylindrical grooves 2 are provided with multiple limiting sleeves 12 inside, and multiple limiting sleeves 12 are provided with oil flow grooves 13 inside; The piston cylinder 301 is movably connected to the top of the limiting sleeve 12. By placing the limiting sleeve 12 inside the cylindrical groove 2, when the bottom of the limiting sleeve 12 contacts the bottom inner wall of the oil storage cavity 14, it can support the multiple positioning components 3 placed inside the cylindrical groove 2. Hydraulic oil is injected into the oil storage cavity 14 from the outside, and the positioning components 3 will not be completely submerged inside the oil storage cavity 14 and unable to move inside the cylindrical groove 2. Meanwhile, by connecting the interior of the oil channel 13 with the interior of the oil storage cavity 14, the hydraulic oil injected into the oil storage cavity 14 can flow and transfer between the bottoms of the multiple cylindrical grooves 2. In this embodiment, multiple cylindrical grooves 2 are machined inside the welding fixture base 1, and an oil storage cavity 14 is connected to the inside of the multiple cylindrical grooves 2. Multiple positioning components 3 installed inside the multiple cylindrical grooves 2 are supported by the hydraulic oil inside the oil storage cavity 14. When the aircraft part is placed on the top of the support rod 306 on the multiple positioning components 3, the rubber sleeve 307 on the top of the support rod 306 is in contact with the bottom surface of the aircraft part. The aircraft part applies pressure to the multiple positioning components 3 simultaneously due to its own weight. With the help of the piston cylinder 301 sliding inside the cylindrical grooves 2, the hydraulic oil supports the multiple positioning components 3 to different heights to adapt to the shape of the bottom of the aircraft part. For large aircraft parts, it can stably support the aircraft parts. Afterwards, only the clamping component 5 needs to be simply fixed, without the need for a special welding and fixing fixture. In this process, the top of the welding fixture base 1 is divided into a central area, a transition area and an edge area by the first movable groove area 4 processed to the side of the welding fixture base 1. Generally, multiple positioning components 3 in the central area work independently, and multiple positioning components 3 in the transition area and the edge area work together with multiple positioning components 3 in the central area. It is worth noting that, since the interior of the oil storage cavity 14 is connected to the interior of the multiple cylindrical grooves 2, in the static state, the multiple positioning components 3 are at the same height, while when the top of the local positioning component 3 is pressed, the remaining multiple positioning components 3 move up the same distance in the interior of the corresponding cylindrical groove 2 (the principle of communicating vessels). Meanwhile, the limiting sleeve 12 set inside the cylindrical groove 2 forms a support at the bottom of the positioning component 3, which can prevent the multiple positioning components 3 under pressure from falling into the oil storage cavity 14, while the remaining multiple positioning components 3 are disengaged from the inside of the cylindrical groove 2 at the corresponding position.

[0023] Example 2: Based on Embodiment 1, this embodiment describes the state in which the clamping assembly 5 is connected to the welding fixture base 1, which assists in fixing aircraft components. The overall concept is as follows: like Figure 1 , Figure 2 , Figures 6 to 9 As shown, each of the multiple clamping components 5 includes a clamping pole 501, a clamping support 502 is assembled and connected to the top of the clamping pole 501, an overlapping arm 504 is provided on the inner side of the clamping support 502, and a clamping head 505 is assembled and connected to the end of the overlapping arm 504 away from the clamping pole 501. Outward corner plates 8 are assembled and connected to the sides of the four corners of the welding fixture base 1, and outward side plates 6 are assembled and connected to the sides of the two long sides of the welding fixture base 1. In this process, by inserting the clamping rods 501 on the multiple clamping components 5 into the interior of the outward side plate 6 and the outward corner plate 8 respectively, when the overlapping arm 504 supports the clamping head 505 overlapping the top of the aircraft component, if an external force forces the aircraft component to tilt from the top to the bottom, the positioning component 3 at the pressure point will move to the bottom, while the positioning components 3 at other points will move to the top, causing the aircraft component to apply pressure to the clamping head 505. However, since the clamping head 505 is installed at the end of the overlapping arm 504 away from the clamping support 502, the clamping rods 501 at the bottom of the clamping support 502 tend to rotate around the rotating seat 18, and will not cause the clamping rods 501 to slide inside the rotating seat 18. Secondly, to make the action of clamping component 5 engaging with aircraft parts more operable, such as... Figure 7 As shown, a clamping handle 503 is hinged to one corner of the top of the clamping support 502. A transition block 506 is hinged between the middle of the clamping handle 503 and the overlapping arm 504. By having one end of the overlapping arm 504 pass through the inside of the clamping handle 503 and hinged to the other corner of the top of the clamping support 502, when the transition block 506 is rotated around its hinge point with the clamping support 502, the transition block 506 drives the overlapping arm 504 to rotate around its hinge point with the clamping support 502, which is beneficial to achieving the purpose of clamping aircraft parts. In some examples, the external sleeve connection of the clamping rod 501 is a rotating seat 18, and the top and bottom of the rotating seat 18 are both interference-fitted with bearings 16. The external sleeve connection of the rotating seat 18 is a limit fastener 19. The surface of the clamping pole 501 is machined with a straight cut surface 17 parallel to its axis, and the inside of the rotating seat 18 is provided with a strip groove 15; The limiting buckle 19 is assembled and connected to the bottom of the outward angle plate 8 or the outward side plate 6. The bearing 16 at the bottom of the rotating seat 18 is interference-fitted to the inside of the limiting buckle 19. The bearing 16 at the top of the rotating seat 18 is interference-fitted to the inside of the outward angle plate 8 or the outward side plate 6. The clamping rod 501 is slidably connected to the inside of the rotating seat 18. The clamping rod 501 is adapted to the inside of the rotating seat 18 through the straight cut surface 17. The clamping rod 501 can rotate at the installation position through the rotating seat 18, which is conducive to the quick adjustment of the clamping angle of the support clamping assembly 5.

[0024] In this embodiment, based on the sliding of the clamping rod 501 inside the rotating seat 18 and the rotation of the rotating seat 18 inside the limiting buckle 19, the clamping assembly 5 is supported to adjust its working orientation. When the end of the overlapping arm 504 away from the clamping support 502 overlaps with the top of the aircraft component, and the bottom surface of the clamping head 505 is in contact with the surface of the aircraft component, and an external force forces the aircraft component to tilt from top to bottom, the positioning component 3 at the pressure application position moves to the bottom, while the positioning component 3 at other positions moves to the top, causing the aircraft component to apply pressure to the clamping head 505. However, since the clamping head 505 is installed at the end of the overlapping arm 504 away from the clamping support 502, the clamping rod 501 at the bottom of the clamping support 502 tends to rotate around the rotating seat 18, and will not cause the clamping rod 501 to slide inside the rotating seat 18, thus ensuring the fixed posture of the aircraft component in the clamped state.

[0025] Specifically, when using this device to perform operations: First, hydraulic oil is injected into the oil storage cavity 14 and then the hydraulic oil enters the cylindrical groove 2. Then, multiple limiting sleeves 12 with oil flow slots 13 are installed into the cylindrical groove 2. Then, multiple positioning components 3 are installed into the cylindrical groove 2. The limiting sleeves 12 are used to support the bottom of the positioning components 3, restricting the positioning components 3 from being completely submerged in the oil storage cavity 14. Then, the aircraft component is placed on top of the support rod 306 on multiple positioning components 3. The rubber sleeve 307 on the top of the support rod 306 fits against the bottom surface of the aircraft component. The aircraft component applies pressure to multiple positioning components 3 simultaneously due to its own weight. With the help of the piston cylinder 301 sliding inside the cylindrical groove 2, the hydraulic oil is automatically adjusted to support multiple positioning components 3 to different heights to adapt to the shape of the bottom of the aircraft component. Next, the control clamping rod 501 slides inside the rotating seat 18, and the control rotating seat 18 rotates inside the limiting buckle 19, adjusting the orientation of the clamping assembly 5, and causing the end of the overlapping arm 504 away from the clamping support 502 to overlap the top of the aircraft component, while the bottom surface of the clamping head 505 is in contact with the surface of the aircraft component. During this process, the adapter block 506 can also be controlled to rotate around its hinge point with the clamping support 502. The adapter block 506 drives the overlapping arm 504 to rotate around its hinge point with the clamping support 502 to clamp the aircraft parts and improve the stability of the aircraft parts when they are fixed.

[0026] Meanwhile, when the end of the overlapping arm 504 away from the clamping support 502 is overlapped on the top of the aircraft component, and the bottom surface of the clamping head 505 is in contact with the surface of the aircraft component, if an external force forces the aircraft component to tilt from top to bottom, the positioning component 3 at the pressure point may move to the bottom, while the positioning components 3 at other points move to the top, causing the aircraft component to apply pressure to the clamping head 505. However, since the clamping head 505 is installed at the end of the overlapping arm 504 away from the clamping support 502, the clamping rod 501 at the bottom of the clamping support 502 tends to rotate around the rotating seat 18, limiting the sliding of the clamping rod 501 inside the rotating seat 18. It is worth noting that for aircraft parts with smaller dimensions, traditional welding fixtures are still required. However, these fixtures are small in size, take up little space, and are not easy to clamp and fix using a uniform fixture (such as the strut outer cylinder joint of the aircraft landing gear, the connection between the crossbeam and the strut, the piston rod and the lug / joint, the retraction mechanism linkage joint, etc.).

[0027] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A welding fixture for repairing commercial aircraft parts, characterized in that, include: Welding fixture base (1); Positioning components (3) are provided in multiples, and all of them extend from the inside of the welding fixture base (1) to the top; Clamping components (5) are provided in multiples, and all of them are located at the top edge; The welding fixture base (1) has an oil storage cavity (14) inside. The top of the oil storage cavity (14) is provided with multiple cylindrical grooves (2) opened inside the welding fixture base (1). The interior of the oil storage cavity (14) and the interior of the multiple cylindrical grooves (2) are connected. Each of the positioning components (3) includes a piston cylinder (301), a connecting support (302) is provided inside the piston cylinder (301), a supporting column (305) is provided on the top of the connecting support (302), a supporting rod (306) is welded to the top of the supporting column (305), and a rubber sleeve (307) is sleeved to the top of the supporting rod (306). The aircraft component is placed on the top of the support rod (306) on multiple positioning components (3). The aircraft component applies pressure to multiple positioning components (3) simultaneously due to its own weight. With the help of the piston cylinder (301) sliding inside the cylindrical groove (2), the hydraulic oil is automatically adjusted to support multiple positioning components (3) to different heights.

2. The welding fixture for repairing commercial aircraft parts according to claim 1, characterized in that, Multiple limiting sleeves (12) are provided inside the multiple cylindrical grooves (2), and oil flow grooves (13) are opened inside the multiple limiting sleeves (12). The interior of the oil channel (13) is connected to the interior of the oil storage cavity (14), and the piston cylinder (301) is movably connected to the top of the limiting sleeve (12).

3. The welding fixture for repairing commercial aircraft parts according to claim 1, characterized in that, The top of the connecting support (302) is provided with a storage slot (11), and the inner walls on both sides of the storage slot (11) are provided with first limiting slots (9). The bottom of the support column (305) is provided with two side limiting slots (10). The internal pin connection of the connecting support (302) is a limiting pin (304). The bottom of the support column (305) is interference-fitted into the inside of the storage slot (11), and the limiting pin (304) is inserted into the inside of the storage slot (11) between the first limiting slot (9) and the second limiting slot (10).

4. A welding fixture for repairing commercial aircraft parts according to claim 1, characterized in that, The connecting support (302) has a stop bar (303) welded to both sides of the middle part. The connecting support (302) has a limit rod (309) pin-connected inside. Both ends of the limit rod (309) are provided with retaining rings (308). The connecting support (302) is inserted into the inside of the piston cylinder (301), and the retaining ring (308) is engaged with the inside of the piston cylinder (301).

5. A welding fixture for repairing commercial aircraft parts according to claim 1, characterized in that, The welding fixture base (1) has a second movable groove area (7) at the center of each of the two short sides, and two first movable groove areas (4) at each of the two long sides. The cross sections of the first movable groove area (4) and the second movable groove area (7) are both isosceles trapezoids, and the two first movable groove areas (4) at one long side of the welding fixture base (1) are symmetrical about the center of the welding fixture base (1).

6. A welding fixture for repairing commercial aircraft parts according to claim 5, characterized in that, The two first movable groove areas (4) divide the top of the welding fixture base (1) into a central area between the two first movable groove areas (4), a transition area corresponding to the two first movable groove areas (4), and an edge area between the first movable groove area (4) and the positioning component (3).

7. A welding fixture for repairing commercial aircraft parts according to claim 1, characterized in that, Each of the clamping assemblies (5) includes a clamping rod (501), the top of which is fitted with a clamping support (502), and the inner side of the clamping support (502) is provided with an overlapping arm (504). The end of the overlapping arm (504) away from the clamping rod (501) is fitted with a clamping head (505). The welding fixture base (1) has outward corner plates (8) assembled and connected to the sides of the four corners, and outward side plates (6) assembled and connected to the sides of the two long sides. Among them, the clamping uprights (501) on the multiple clamping components (5) are respectively inserted into the interior of the outward side plate (6) and the outward corner plate (8), and the overlapping arm (504) supports the clamping head (505) to overlap on the top of the aircraft component.

8. A welding fixture for repairing commercial aircraft parts according to claim 7, characterized in that, A clamping handle (503) is hinged to one corner of the top of the clamping support (502), and a transition block (506) is hinged between the middle of the clamping handle (503) and the overlapping arm (504). One end of the overlapping arm (504) passes through the inside of the clamping handle (503) and is hinged to the other corner of the top of the clamping support (502).

9. A welding fixture for repairing commercial aircraft parts according to claim 7, characterized in that, The clamping upright (501) is externally connected to a rotating seat (18), and the top and bottom of the rotating seat (18) are both interference-fitted with bearings (16), and the rotating seat (18) is externally connected to a limit fastener (19). The limiting buckle (19) is assembled and connected to the bottom of the outward corner plate (8) or the outward side plate (6). The bearing (16) at the bottom of the rotating seat (18) is interference-fitted to the inside of the limiting buckle (19). The bearing (16) at the top of the rotating seat (18) is interference-fitted to the inside of the outward corner plate (8) or the outward side plate (6).

10. A welding fixture for repairing commercial aircraft parts according to claim 9, characterized in that, The surface of the clamping rod (501) is machined with a straight cut surface (17) parallel to its axis, and the inside of the rotating seat (18) is provided with a strip groove (15). The clamping rod (501) is slidably connected inside the rotating seat (18), and the clamping rod (501) is adapted to be connected inside the rotating seat (18) through a straight cut surface (17).

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