Device and method for forming sunken rubber of fuselage structure

Abstract

The invention discloses a fuselage structure sinking glue forming device and method. The device comprises a glue gun, and the glue gun is used for spraying a sealant solution to a target groove area; wherein the target groove area is a groove area to be filled with glue on the fuselage structural component; one end of the glue scraping plate is a plane end, an arc-shaped groove is formed in the other end of the glue scraping plate, and the glue scraping plate is used for scraping a protruding glue solution in the middle area of the sealant glue solution through the arc-shaped groove; the hard plastic film is used for being laid on the surface of the sealant solution with the protruding sealant solution; the heating device comprises a shell, a heating element used for heating the flattened sealant solution is arranged on the shell, an inner groove is formed in the inner bottom of the shell, and the inner groove is located over the target groove area, and the device has the advantages that qualified sunken glue can be formed at a time, and the forming quality and efficiency are improved.

Description

Technical Field

[0001] The present application relates to the technical field of aviation parts processing, and in particular to a device and method for molding a fuselage structure depression rubber. Background Art

[0002] When the frame and beam structures of the aircraft are connected, a groove area will be formed at the connection point, such as Figure 1 As shown in the figure, this structure is common in aircraft assembly. In order to ensure the air tightness and oil tightness between the various structural parts of the aircraft, a special sealant is usually used to fill the groove area, which is called sinking glue filling in the industry. When the sinking glue construction method currently used in the industry is processed, due to the adhesiveness of the glue, the utility knife cannot scrape the glue surface flat, and a depression of about 0.5-1mm will be generated on the glue surface. Figure 2 As shown, the vulcanization of the glue cannot be qualified in one time, and it is necessary to repeatedly fill the glue to eliminate the depression phenomenon until the surface of the sunken glue is flat and the height is 0.1-0.3mm higher than the structure. Since the single vulcanization cycle of the glue is 72h, repeated filling causes the construction cycle of the sunken glue to increase exponentially. Not only that, in the process of repeated filling, the adhesion between the new glue and the old glue is extremely poor, which causes the repeated debonding of the sunken glue, and cannot meet the quality requirements and production rhythm. Summary of the Invention

[0003] The main purpose of this application is to provide a fuselage structure sinking glue molding device and molding method, aiming to solve the technical problem that the existing fuselage structure sinking glue molding method is difficult to mold qualified sinking glue in one time, resulting in poor molding quality.

[0004] To achieve the above-mentioned purpose, the present application provides a fuselage structure sunken glue forming device, including a glue gun, which is used to spray sealant glue liquid into a target groove area; wherein the target groove area is a groove area to be filled with glue on the fuselage structural member; a scraper, one end of the scraper is a flat end, and the other end of the scraper is provided with an arc-shaped groove, and the scraper is used to scrape a raised glue liquid from the middle area of ​​the sealant glue liquid through the arc-shaped groove; a hard plastic film, which is used to be laid on the surface of the sealant glue liquid with the raised glue liquid; a heating device, which includes a shell, and a heating element is provided on the shell for heating the flattened sealant glue liquid, and an inner groove is provided at the bottom of the shell, and the inner groove is located directly above the target groove area.

[0005] Optionally, cross bars are detachably connected to both sides of the shell, and clamping plates are movably sleeved on both cross bars. Limiting nuts are threadedly sleeved on both cross bars, and the limiting nuts are fitted to the side of the clamping plate away from the shell to clamp the two clamping plates on both sides of the fuselage structure.

[0006] Optionally, two support platforms are provided at the bottom of the shell, respectively located on both sides of the inner groove. The support platforms are used to be placed on the fuselage structure. The distance between the support platforms and the shell is adjustable. A strip groove is provided on the clamping plate along the height direction of the clamping plate to cooperate with the cross bar.

[0007] Optionally, two first accommodating grooves are provided in the shell and are respectively located above the support platform. A first airbag component is provided in the first accommodating groove and is used for vertical expansion and stretching. The bottom of the first airbag component is connected to a push plate provided on the top of the support platform and is used to push the support platform to adjust the distance between the support platform and the shell.

[0008] Optionally, the crossbar is a hollow structure, and an inflation component is provided in the crossbar, and the inflation component is used to inflate the first airbag component.

[0009] Optionally, the inflation assembly includes a first fixing plate fixedly arranged in the cross bar, the first fixing plate is connected to the second airbag component on the side away from the first airbag component, and an air inlet hole is opened between the second airbag component and the first fixing plate, and the air inlet hole is used to connect to the first airbag component.

[0010] Optionally, a second fixing plate and a first elastic member are also provided in the cross bar. The first elastic member is located between the second fixing plate and the second airbag member. A traction rope is connected to one end of the second airbag member close to the first elastic member. The traction rope is movable through the second fixing plate and extends out of the cross bar. In the initial state, the first elastic member is in a compressed state.

[0011] Optionally, the movable sleeve on the traction rope is provided with a hollow ball located outside the cross bar, the outer diameter of the hollow ball is larger than the inner diameter of the cross bar, and a limit screw is threadedly connected on the hollow ball. The limit screw is used to extend into the hollow ball and press the traction rope into the inside of the hollow ball.

[0012] Optionally, a vertical rod is provided on the shell, which passes through the shell, the first airbag component and the push plate from top to bottom. The vertical rod is threadedly connected to the shell, and the bottom of the vertical rod is movably connected to the support platform. The first airbag component and the push plate are movably mounted on the vertical rod.

[0013] Optionally, a second receiving groove with a top opening is provided in the support platform, and a movable block is slidably arranged at the bottom of the second receiving groove. The sliding direction of the movable block is the opposite direction of the two support platforms, and a blind hole is provided in the movable block to cooperate with the vertical rod.

[0014] Optionally, a sliding groove is provided at the bottom of the second accommodating groove, and a sliding block is connected to the bottom of the movable block and is slidably matched with the sliding groove.

[0015] Optionally, a sphere located in the first airbag component is fixedly sleeved on the vertical rod, and a first channel is provided between the sphere and the vertical rod. One end of the first channel is located on one side of the sphere to communicate with the inflation assembly, and the other end of the first channel passes through the bottom of the vertical rod to communicate with the blind hole. The side wall of the movable block is connected to a third airbag component, and the other end of the third airbag component is connected to the inner side wall of the second accommodating groove. A second channel is provided on the side wall of the movable block, and the second channel is used to connect the third airbag component and the blind hole. The third airbag component is used to expand and stretch laterally to drive the movable block to slide.

[0016] Optionally, a connecting sleeve is provided on one side of the shell and is threadedly connected to the cross bar. The connecting sleeve is movably extended into the first airbag component. A step groove is provided on the inner wall of the connecting sleeve on one side of the first airbag component. A movable tube is movably provided in the step groove. One end of the movable tube is located in the step groove and is connected to the second elastic component. The other end of the second elastic component is connected to the end of the step groove. The inner diameter of the movable tube is smaller than the diameter of the sphere.

[0017] To achieve the above-mentioned purpose, the present application also provides a molding method, based on the above-mentioned fuselage structure sag rubber molding device, comprising the following steps: A layer of pressure-sensitive adhesive tape is attached to both sides and the front and rear ends of the upper surface of the target groove area; Spray the sealant liquid into the target groove area through a glue gun, and finally make the sealant liquid rise above the preset height of the surface of the fuselage structural component; Place the arc-shaped groove of the scraper against one end of the target groove area and tilt the scraper at a preset angle, so that the scraper slowly scrapes the sealant from one end to the other end to scrape out a raised sealant in the middle area of ​​the sealant; Use the flat end of the scraper to remove excess glue from the pressure-sensitive adhesive tape on both sides; Lay the cut transparent hard plastic film on the surface of the raised glue; Use the flat end of the scraper to slowly scrape the hard plastic film from one end to the other, so that the hard plastic film completely fits the surface of the fuselage structure; Place the heating device on top of the hard plastic film and heat it to a preset temperature to vulcanize the sealant liquid; After the preset vulcanization time, remove the heating device; Peel off the hard plastic film and pressure-sensitive adhesive tape on the surface to form a sunken adhesive in the target groove area; Use a knife to cut off the excess glue at both ends of the front and rear sunken glue; Clean the surface of the sunken glue with cleaning fluid.

[0018] The beneficial effects that can be achieved by this application are as follows: The present application first sprays sealant glue liquid onto the target groove area on the fuselage structural component through a glue gun, and then uses a scraper with an arc groove to scrape a raised glue liquid in the middle area of ​​the sealant glue liquid, and the flat end of the scraper is convenient for scraping off the overflow glue. This scraping glue treatment method ensures that while removing excess glue liquid, it also retains the middle glue liquid in a quantitative manner, providing a guarantee for subsequent filling of the entire sunken area. Then, a hard plastic film is laid on the surface of the sealant glue liquid with the raised glue liquid, and then the flat end of the scraper is used to slowly scrape the hard plastic film from one end to the other end to make it completely fit the surface of the fuselage structural component. At this time, the raised glue liquid after scraping the glue can automatically fill the entire sunken area, and the excess glue liquid is discharged from the front and rear ends of the groove area. Finally, a heating device is set on the surface of the sunken area to accelerate the vulcanization of the filled glue liquid. During heating, the heating element is started, and the groove at the bottom of the shell of the heating device forms a heat dissipation space for the surface of the sunken area. After heating for a period of time, the one-time rapid molding of the sunken glue can be completed, and the hard plastic film can be used to have a demolding function for the sunken glue after vulcanization, thereby ensuring the one-time molding quality of the sunken glue, eliminating the need for multiple glue fillings, and improving the molding efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] To more clearly illustrate the specific embodiments of this application or the technical solutions in the prior art, the following briefly describes the drawings required for the specific embodiments or the description of the prior art. Similar elements or parts are generally identified by similar reference numerals throughout the drawings. Elements or parts in the drawings are not necessarily drawn to scale.

[0020] Figure 1 A schematic diagram of the structure of a fuselage structural member having a groove area in the prior art; Figure 2 This is a schematic diagram of the structure of a fuselage structural component in the prior art when the glue is sunken; Figure 3 This is a schematic diagram of affixing a pressure-sensitive adhesive tape near a groove area of ​​a fuselage structural member in an embodiment of the present application; Figure 4 This is a schematic diagram of spraying sealant glue liquid into the groove area of ​​the fuselage structural component by using a glue gun in an embodiment of the present application; Figure 5 This is a schematic diagram of spraying sealant into the groove area of ​​the fuselage structural component in an embodiment of the present application; Figure 6 This is a schematic diagram of a process of scraping the sealant liquid by a scraper in an embodiment of the present application; Figure 7 This is a schematic diagram of the raised glue liquid formed after the scraping process in the embodiment of the present application; Figure 8This is a schematic diagram of a hard plastic film laid on a raised adhesive surface in an embodiment of the present application; Figure 9 This is a schematic diagram of heating the sealant liquid by a heating device in an embodiment of the present application; Figure 10 Schematic diagram of the structure of the heating device in the embodiment of the present application; Figure 11 Schematic diagram of the internal structure of the heating device in an embodiment of the present application (heating element omitted); Figure 12 This is a schematic diagram of a partial structure of a heating device in an embodiment of the present application; Figure 13 for Figure 12 Schematic diagram of the locally enlarged structure at point A in the middle.

[0021] Reference numerals: 100-glue gun, 200-squeegee, 210-plane end, 220-arc groove, 300-hard plastic film, 400-heating device, 410-shell, 411-inner groove, 412-first accommodating groove, 420-heating element, 430-cross bar, 440-clamping plate, 441-strip groove, 450-limiting nut, 460-inflatable component, 461-first fixing plate, 462-second airbag component, 463-air inlet, 464-second fixing plate, 465-first Elastic part, 466-traction rope, 467-hollow ball, 468-limiting screw, 469-connecting sleeve, 4691-step groove, 470-vertical rod, 471-sphere, 472-first channel, 480-movable tube, 490-second elastic part, 500-support platform, 510-second accommodating groove, 520-slide groove, 600-first airbag part, 700-push plate, 800-movable block, 810-slider, 820-blind hole, 830-second channel, 900-third airbag part.

[0022] The realization of the objectives, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0024] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0025] In this application, unless otherwise specified or limited, the terms "connection" and "fixed" should be understood in a broad sense. For example, "connection" can mean fixed connection, detachable connection, or integration; it can mean mechanical connection or electrical connection; it can mean direct connection or indirect connection through an intermediate medium; it can mean internal communication between two elements or interaction between two elements, unless otherwise specified. For those skilled in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0026] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or suggesting their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of such features. In addition, the meaning of "and / or" appearing throughout the text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme in which A and B are satisfied at the same time. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement it. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0027] Example 1 Reference Figure 3-Figure 13 The present embodiment provides a fuselage structure sunken glue forming device, including a glue gun 100, which is used to spray sealant glue liquid into a target groove area; wherein the target groove area is a groove area to be filled with glue on the fuselage structural member; a scraper 200, one end of the scraper 200 is a flat end 210, and the other end of the scraper 200 is provided with an arc-shaped groove 220, and the scraper 200 is used to scrape a raised glue liquid from the middle area of ​​the sealant glue liquid through the arc-shaped groove 220; a hard plastic film 300, which is used to be laid on the sealant glue liquid surface with the raised glue liquid; a heating device 400, which includes a shell 410, and a heating element 420 is provided on the shell 410 for heating the flattened sealant glue liquid, and an inner groove 411 is provided at the bottom of the shell 410, and the inner groove 411 is located directly above the target groove area.

[0028] In this embodiment, the sealant is first sprayed onto the target groove area on the fuselage structural member through the glue gun 100, and then a convex glue is scraped out of the middle area of ​​the sealant by the scraper 200 with the arc groove 220, and the flat end 210 of the scraper 200 is convenient for scraping off the overflow glue. This scraping treatment method ensures that the excess glue is removed while quantitatively retaining the middle glue, which provides a guarantee for the subsequent filling of the entire sunken area. Then, a hard plastic film 300 is laid on the surface of the sealant with the convex glue, and then the flat end 210 of the scraper 200 is slowly scraped from one end to the other end to make it completely fit the machine The surface of the body structure, at this time, the raised glue after scraping the glue can automatically fill the entire sunken area, and the excess glue is discharged from the front and rear ends of the groove area, and finally a heating device 400 is set on the surface of the sunken area to accelerate the vulcanization of the filled glue. When heating, the heating element 420 is started, and the groove 411 at the bottom of the shell 410 of the heating device 400 forms a heat dissipation space for the surface of the sunken area. After heating for a period of time, the one-time rapid molding of the sunken glue can be completed, and the hard plastic film 300 can have a demolding function for the sunken glue after vulcanization, thereby ensuring the one-time molding quality of the sunken glue, eliminating the need for multiple glue fillings, and improving the molding efficiency.

[0029] It should be noted that the material of the hard plastic film 300 can be transparent polyethylene material, which is convenient for visual inspection after laying to see whether there are cavities, bubbles, etc. on the surface of the glue. If such phenomena are found, the hard plastic film 300 can be peeled off and the glue can be repaired until the visual inspection is qualified.

[0030] As an optional embodiment, cross bars 430 are detachably connected to both sides of the shell 410, and clamping plates 440 are movably sleeved on both cross bars 430. Limiting nuts 450 are threadedly sleeved on both cross bars 430, and the limiting nuts 450 are fitted to the side of the clamping plate 440 away from the shell 410, so that the two clamping plates 440 are clamped on both sides of the fuselage structure.

[0031] In this embodiment, in order to ensure that the heating device 400 placed on the lower limit area (i.e., the groove area after filling with glue) can stably and continuously heat and vulcanize the sunken glue, a clamping plate 440 is provided. Before using the heating device 400, the heating device 400 is placed above the sunken area on the fuselage structural member, and then the position of the clamping plate 440 on the cross bar 430 is adjusted so that the clamping plate 440 is on both sides of the fuselage structural member. Then, the limiting nut 450 is rotated so that the limiting nut 450 can be pushed to the clamping plate 440 to clamp on both sides of the fuselage workpiece, and finally the heating device 400 is fixed to the fuselage structural member, thereby preventing the heating device 400 from being displaced by external factors during the long-term heating and vulcanization of the fuselage structural member, thereby affecting the vulcanization effect of the fuselage workpiece, further ensuring the molding quality of the sunken glue, and the clamping width of the two clamping plates 440 is adjustable, so that it can adapt to the clamping of fuselage structural members of different specifications, and has strong versatility.

[0032] As an optional embodiment, two support platforms 500 are provided at the bottom of the shell 410, respectively located on both sides of the inner groove 411. The support platforms 500 are used to be placed on the fuselage structure. The distance between the support platforms 500 and the shell 410 is adjustable. A strip groove 441 is opened on the clamping plate 440 along the height direction of the clamping plate 440 to cooperate with the cross bar 430.

[0033] In this embodiment, when processing aircraft parts, when it is necessary to fill the sunken area of ​​the convex part with glue, in order to ensure that the heating device 400 can smoothly heat and vulcanize the glue filling area of ​​the convex part, a support platform 500 is further provided at the bottom of the shell 410. The support platform 500 can be used to lift the height of the heating device 400 to ensure that the concave bottom of the heating device 400 is above the glue filling area of ​​the fuselage structure, so that the sunken glue filling area of ​​the convex part can be effectively heated and vulcanized, and the distance between the support platform 500 and the shell 410 is adjustable, and in conjunction with the adjustment of the cross bar 430 at different height positions of the strip groove 441, it can adapt to the support platform 500 to adjust the height of the heating device 400 and still ensure clamping on both sides of the fuselage structure, and at the same time ensure that sufficient inner groove 411 space can still be formed after adjustment to ensure the vulcanization molding effect of the sunken glue.

[0034] As an optional embodiment, two first accommodating grooves 412 are provided in the shell 410, which are respectively located above the support platform 500. A first airbag component 600 is provided in the first accommodating groove 412. The first airbag component 600 is used for vertical expansion and stretching. The bottom of the first airbag component 600 is connected to a push plate 700 provided on the top of the support platform 500. The push plate 700 is used to push the support platform 500 to adjust the distance between the support platform 500 and the shell 410.

[0035] In this embodiment, during adjustment, the first airbag component 600 can be inflated. After being inflated, the first airbag component 600 can be vertically expanded and stretched, thereby driving the push plate 700 to extend downward from the first accommodating groove 412. When the push plate 700 presses against the top of the support platform 500, the entire shell 410 is pushed upward, thereby changing the distance between the support platform 500 and the shell 410, so as to achieve the ability to heat the glue filling areas at the protrusions of different heights of the fuselage structural parts.

[0036] As an optional embodiment, the crossbar 430 is a hollow structure, and an inflatable assembly 460 is disposed within the crossbar 430. The inflatable assembly 460 is used to inflate the first airbag member 600. Placing the inflatable assembly 460 within the hollow crossbar 430 facilitates inflation while also reducing the overall size of the heating device 400 and achieving a high level of integration.

[0037] As an optional embodiment, the inflation component 460 includes a first fixing plate 461 fixedly arranged in the cross bar 430, and the first fixing plate 461 is connected to the second airbag component 462 on the side away from the first airbag component 600 (the second airbag component can adopt a corrugated tube with closed structures at both ends), and an air inlet hole 463 is opened between the second airbag component 462 and the first fixing plate 461, and the air inlet hole 463 is used to connect to the first airbag component 600.

[0038] In this embodiment, when it is necessary to transmit gas to the inside of the first airbag component 600 to expand and stretch it, the second airbag component 462 can be compressed toward the first fixed plate 461 so that the gas inside it can be squeezed into the first airbag component 600 through the air inlet hole 463, thereby achieving the purpose of inflating and expanding the first airbag component 600, and ultimately achieving the adjustment of the height of the shell 410. The structural design is ingenious and does not require the aid of an additional inflation device, making it easy to inflate quickly.

[0039] As an optional embodiment, a second fixing plate 464 and a first elastic member 465 (a spring may be used) are also provided in the cross bar 430. The first elastic member 465 is located between the second fixing plate 464 and the second airbag member 462. The end of the second airbag member 462 close to the first elastic member 465 is connected to a traction rope 466. The traction rope 466 is movable through the second fixing plate 464 and extends out of the cross bar 430. In the initial state, the first elastic member 465 is in a compressed state.

[0040] In this embodiment, since the first elastic member 465 is in a compressed state in the initial state, when adjustment is required, the traction rope 466 can be slowly released to allow the first elastic member 465 to gradually release its elastic force. The second fixing plate 464 limits the first elastic member 465 so that it only releases its elastic force to the second airbag member 462, thereby causing the first elastic member 465 to generate an extrusion force on the second airbag member 462 to cause the second airbag member 462 to release the internal gas. By setting the traction rope 466 and the first elastic member 465, the compression amount of the second airbag member 462 can be adjusted, thereby controlling the volume of air squeezed into the first airbag member 600 by the second airbag member 462, and ultimately achieving precise control of the deformation amount of the first airbag member 600, and the operation is convenient and quick.

[0041] As an optional embodiment, a movable sleeve on the traction rope 466 is provided with a hollow ball 467 located on the outside of the cross bar 430. The outer diameter of the hollow ball 467 is larger than the inner diameter of the cross bar 430. A limiting screw 468 is threadedly connected to the hollow ball 467. The limiting screw 468 is used to extend into the hollow ball 467 and press the traction rope 466 into the inside of the hollow ball 467.

[0042] When the second airbag component 462 is compressed, the second airbag component 462 will be compressed, and the traction rope 466 will be pulled along by the traction rope 466. When the deformation adjustment of the second airbag component 462 is completed, the hollow ball 467 is moved to the end of the cross bar 430 and the traction rope 466 is straightened. Finally, the limiting screw 468 is tightened so that the limiting screw 468 fixes the pull rope on the hollow ball 467. Under the action of the first elastic member 465, the hollow ball 467 can be pressed against the end of the cross bar 430, thereby achieving the fixation of the traction rope 466.

[0043] As an optional embodiment, a vertical rod 470 is provided on the shell 410, which passes through the shell 410, the first airbag component 600 and the push plate 700 from top to bottom. The vertical rod 470 is threadedly connected to the shell 410, and the bottom of the vertical rod 470 is movably connected to the support platform 500. The first airbag component 600 and the push plate 700 are both movably mounted on the vertical rod 470.

[0044] In this embodiment, when the first airbag component 600 drives the push plate 700 to move, the vertical rod 470 serves to guide the push plate 700 and simultaneously achieves a detachable connection between the support platform 500 and the housing 410. It should be noted that the connection between the first airbag component 600 and the vertical rod 470 can be sealed by a sealing ring or other sealing structure, thereby preventing air leakage from the first airbag component 600 and simultaneously maintaining the sliding fit between the first airbag component 600 and the vertical rod 470 during inflation.

[0045] As an optional embodiment, a second receiving groove 510 with a top opening is provided in the support platform 500, and a movable block 800 is slidingly arranged at the bottom of the second receiving groove 510. The sliding direction of the movable block 800 is the opposite direction of the two support platforms 500, and a blind hole 820 is provided in the movable block 800 for movably cooperating with the vertical rod 470.

[0046] In this embodiment, in order to adjust the distance between the two support platforms 500 installed at the bottom of the shell 410, thereby meeting the requirements of the groove width of different fuselage structural parts, the movable block 800 is slidably connected to the bottom of the support platform 500, which can directly push the support platform 500 to move left and right, and the movable block 800 will not move therewith under the limiting action of the vertical rod 470, thereby realizing the movement of the support platform 500 relative to the shell 410. The adjustment is convenient and quick, meeting more usage scenarios, and further improving the versatility.

[0047] It should be noted that the support platform 500 and the push plate 700 should be in contact with each other, so that the support platform 500 can translate along the bottom surface of the push plate 700 .

[0048] As an optional embodiment, a slide groove 520 is opened at the bottom of the second receiving groove 510, and a slider 810 is connected to the bottom of the movable block 800 to slide with the slide groove 520, which has a good guiding effect and more stable sliding.

[0049] As an optional embodiment, a sphere 471 located in the first airbag component 600 is fixedly sleeved on the vertical rod 470, and a first channel 472 is provided between the sphere 471 and the vertical rod 470. One end of the first channel 472 is located on one side of the sphere 471 to communicate with the inflation component 460, and the other end of the first channel 472 passes through the bottom of the vertical rod 470 to communicate with the blind hole 820. The side wall of the movable block 800 is connected to the third airbag component 900, and the other end of the third airbag component 900 is connected to the inner wall of the second accommodating groove 510. The side wall of the movable block 800 is provided with a second channel 830, and the second channel 830 is used to connect the third airbag component 900 and the blind hole 820. The third airbag component 900 is used to perform lateral expansion and stretching to drive the movable block 800 to slide.

[0050] In this embodiment, when the distance between the two support platforms 500 needs to be adjusted, the connection between the second airbag component 462 and the first airbag component 600 can be connected through the provided sphere 471, so that the gas generated by the extrusion of the second airbag component 462 can enter the first channel 472 of the sphere 471, and then the gas enters the blind hole 820 of the movable block 800 along the first channel 472, and finally enters the third airbag component 900 through the second channel 830. The provided third airbag component 900 can be a bellows, which can be stretched along its axial direction (i.e., expanded and stretched laterally) after being inflated to change the length of the third airbag component 900. When After the length of the third airbag component 900 is changed, since the vertical rod 470 can only move in the vertical direction and cannot move in the horizontal direction, under the reaction force of the movable block 800, the support platform 500 is relatively displaced with the shell 410 under the action of the slider 810, and finally the adjustment of the distance between the two support platforms 500 at the bottom of the shell 410 is achieved to meet the use of groove areas of different widths of the fuselage structural parts. Therefore, the first airbag component 600 can be fully utilized here, and it has the functions of adjusting the height of the shell 410 and the distance between the support platforms 500. There is no need to set up an inflatable airbag separately, which saves internal space and makes the structure more compact.

[0051] It should also be noted that by adjusting the depth of the vertical rod 470 extending into the blind hole 820 in the movable block 800, it is possible to control whether the gas transferred by the second airbag component 462 enters the third airbag component 900. That is, when the bottom of the vertical rod 470 is inserted below the connection between the third airbag component 900 and the inner wall of the blind hole 820, the second channel 830 is blocked. At this time, the third airbag component 900 and the first channel 472 are in a disconnected state. At this time, the gas generated by the extrusion of the second airbag component 462 will not be able to be transferred to the third airbag component 900, and the operation is flexible.

[0052] As an optional embodiment, a connecting sleeve 469 is provided on one side of the shell 410 and is threadedly connected to the cross bar 430. The connecting sleeve 469 is movably extended into the first airbag component 600. A step groove 4691 is provided on the inner wall of the connecting sleeve 469 and on one side of the first airbag component 600. A movable tube 480 is movably provided in the step groove 4691. One end of the movable tube 480 located in the step groove 4691 is connected to the second elastic component 490 (a spring can be used), and the other end of the second elastic component 490 is connected to the end of the step groove 4691. The inner diameter of the movable tube 480 is smaller than the diameter of the sphere 471.

[0053] In this embodiment, when it is necessary to inflate the interior of the third airbag component 900, the vertical rod 470 is rotated forward to move the vertical rod 470 upward. In the process of moving upward, the vertical rod 470 drives the ball 471 to move along with it. In the process of moving upward, the ball 471 acts on the end of the movable tube 480, causing the movable tube 480 to compress the second elastic member 490 and retract into the connecting sleeve 469. When the ball 471 moves to be coaxially aligned with the movable tube 480, the movable tube 480 is sealed with the ball 471 under the action of the second elastic member 490. At this time, the first channel 472 and the second channel 83 are connected. 0, the third airbag component 900 is connected to the second airbag component 462; and when the first airbag component 600 needs to be connected to the second airbag component 462 again, the vertical rod 470 is reversed so that the bottom of the vertical rod 470 extends into the blind hole 820 of the movable tube 480, and finally the bottom of the vertical rod 470 blocks the second channel 830. At this time, the third airbag component 900 is disconnected from the blind hole 820. At this time, the gas generated by the squeezing of the second airbag component 462 can only enter the first airbag component 600, causing the first airbag component 600 to stretch and lengthen. Therefore, the air path can be switched by only rotating the vertical rod 470 in different directions, which is convenient and quick to operate.

[0054] Example 2 Reference Figure 3-Figure 13 This embodiment further provides a molding method, based on a fuselage structure sag rubber molding device in the above embodiment, comprising the following steps: Step S1: affixing a layer of pressure-sensitive adhesive tape on both sides and the front and rear ends of the upper surface of the target groove area; Step S2: spraying the sealant liquid into the target groove area using the glue gun 100, and finally making the sealant liquid higher than a preset height on the surface of the fuselage structural component; Step S3: Using the arc groove 220 of the scraper 200 to lean against one end of the target groove area, and tilting the scraper 200 at a preset angle, the scraper 200 is slowly scraped from one end of the sealant liquid to the other end, so as to scrape out a raised glue line in the middle area of ​​the sealant liquid; Step S4: using the flat end 210 of the scraper 200 to remove excess adhesive on both sides of the pressure-sensitive adhesive tape; Step S5: laying the cut transparent hard plastic film 300 on the raised glue surface; Step S6: Slowly scrape the hard plastic film 300 from one end to the other end using the flat end 210 of the scraper 200 so that the hard plastic film 300 completely adheres to the surface of the fuselage structure; Step S7: placing the heating device 400 above the rigid plastic film 300 and heating it to a preset temperature to vulcanize the sealant glue; Step S8: After the preset curing time, the heating device 400 is removed; Step S9: peeling off the hard plastic film 300 and the pressure-sensitive adhesive tape on the surface to form a sunken adhesive in the target groove area; Step S10: using a cutter to cut off excess glue at both ends of the front and rear sunken glue; Step S11: Cleaning the surface of the sunken glue with a cleaning solution. In this embodiment, before applying glue, a layer of pressure-sensitive adhesive tape (the thickness can be about 0.2mm) is first pasted on both sides of the upper surface and the front and rear ends of the target groove area to prevent the glue from contaminating the surface of the fuselage structure. At the same time, it is also convenient to tear off the pressure-sensitive adhesive tape after the subsequent sunken glue is formed; then, the glue gun 100 is used to apply glue. When applying glue, the mixed special sealant glue is filled into the glue gun 100, and a small hole is cut in the front end glue nozzle with a utility knife. Press the switch to slowly fill the glue from one direction to the other. Into the target groove area, and ensure that the final glue is 2~3mm higher than the surface of the structure; then use the arc groove 220 of the scraper 200 to lean against one end of the target groove area, tilt 30°~45°, and slowly scrape the glue from one end to the other end, so as to ensure that the excess glue is removed while quantitatively retaining the intermediate glue, which provides a guarantee for the subsequent filling of the entire sunken area; then use the flat end 210 of the scraper 200 to clean the excess glue on the pressure-sensitive adhesive tapes on both sides, and lay the cut transparent polyethylene hard plastic film 300 on Then use the flat end 210 of the scraper 200 to slowly scrape the plastic film from one end to the other end to make it completely fit the surface of the structure. At this time, the glue that protruded from the surface of the structure after scraping will automatically fill the entire sunken area, and the excess glue will be discharged from the front and back ends of the structure. Here, the transparent hard plastic film 300 can be used to visually check whether there are cavities, bubbles, etc. on the surface of the glue. If there are such phenomena, the hard plastic film 300 will be peeled off and steps S2-S6 will be repeated until the visual inspection is qualified. Then the glue can be checked according to the fuselage. The width of the groove of the structural part adjusts the spacing of the bottom support platform 500 of the heating device 400, and then the heating device 400 is placed above the sunken area, and the power is turned on to heat it to 60°C, and the stability of the heating device 400 is ensured by the clamping plate 440 provided on the heating device 400; after heating and vulcanizing for 6 hours, the heating device 400 is removed; the plastic film and pressure-sensitive adhesive tape on the surface are peeled off; the excess glue at the front and back ends is cut off with a tool such as a utility knife; the surface of the sunken glue is cleaned with a cleaning fluid such as acetone, and finally a high-quality sunken glue is formed in one go.

[0055] The above are only preferred embodiments of the present application and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A device for forming a sag rubber for a fuselage structure, characterized in that: include: A glue gun is used to spray sealant glue liquid into the target groove area; wherein the target groove area is the groove area to be filled with glue on the fuselage structural part; A scraper, one end of which is a flat surface, and the other end of which is provided with an arc-shaped groove. The scraper is used to scrape a raised line of sealant from the middle area of ​​the sealant through the arc-shaped groove. Hard plastic film, hard plastic film is used to lay on the surface of the sealant glue with raised glue; The heating device includes a shell, on which a heating element is provided for heating the flattened sealant liquid. An inner groove is provided at the bottom of the shell, and the inner groove is located directly above the target groove area.

2. The fuselage structure sag rubber molding device according to claim 1, characterized in that: The shell is detachably connected with cross bars, and clamping plates are movably sleeved on both cross bars. Limiting nuts are threadedly sleeved on both cross bars, and the limiting nuts are fitted to the side of the clamping plate away from the shell to clamp the two clamping plates on both sides of the fuselage structure.

3. The fuselage structure sag rubber molding device according to claim 2, characterized in that: Two support platforms are provided at the bottom of the shell, one on each side of the inner groove. The support platforms are used to be placed on the fuselage structure. The distance between the support platforms and the shell is adjustable. A strip groove is provided on the clamping plate along the height direction of the clamping plate to cooperate with the cross bar.

4. The fuselage structure sag rubber molding device according to claim 3, characterized in that: Two first accommodating grooves are provided in the shell and are respectively located above the support platform. A first airbag component is provided in the first accommodating groove. The first airbag component is used for vertical expansion and stretching. The bottom of the first airbag component is connected to a push plate provided on the top of the support platform. The push plate is used to push the support platform to adjust the distance between the support platform and the shell.

5. The fuselage structure sag rubber molding device according to claim 4, characterized in that: The crossbar is a hollow structure, and an inflation component is arranged inside the crossbar. The inflation component is used to inflate the first airbag component.

6. The fuselage structure sag rubber molding device according to claim 5, characterized in that: The inflation component includes a first fixing plate fixedly arranged in the crossbar. The second airbag component is connected to the side of the first fixing plate away from the first airbag component. An air inlet is opened between the second airbag component and the first fixing plate, and the air inlet is used to connect to the first airbag component.

7. The fuselage structure sag rubber molding device according to claim 6, characterized in that: A second fixing plate and a first elastic member are also provided in the cross bar. The first elastic member is located between the second fixing plate and the second airbag member. A traction rope is connected to one end of the second airbag member close to the first elastic member. The traction rope movably passes through the second fixing plate and extends out of the cross bar. In the initial state, the first elastic member is in a compressed state.

8. The fuselage structure sag rubber molding device according to claim 7, characterized in that: The movable sleeve on the traction rope is provided with a hollow ball located outside the cross bar. The outer diameter of the hollow ball is larger than the inner diameter of the cross bar. The hollow ball is threadedly connected with a limit screw, which is used to extend into the hollow ball and press the traction rope into the inside of the hollow ball.

9. A fuselage structure sag rubber molding device according to any one of claims 5 to 8, characterized in that: The shell is provided with a vertical rod which passes through the shell, the first airbag component and the push plate from top to bottom. The vertical rod is threadedly connected to the shell, and the bottom of the vertical rod is movably connected to the support platform. The first airbag component and the push plate are movably mounted on the vertical rod.

10. The fuselage structure sag rubber molding device according to claim 9, characterized in that: A second receiving groove with a top opening is provided in the support platform, and a movable block is slidably provided at the bottom of the second receiving groove. The sliding direction of the movable block is the opposite direction of the two support platforms, and a blind hole is provided in the movable block to cooperate with the vertical rod.

11. The fuselage structure sag rubber molding device according to claim 10, characterized in that: A sliding groove is provided at the bottom of the second accommodating groove, and a sliding block is connected to the bottom of the movable block and is slidably matched with the sliding groove.

12. The fuselage structure sag rubber molding device according to claim 10, characterized in that: A sphere located in the first airbag component is fixedly sleeved on the vertical rod, and a first channel is provided between the sphere and the vertical rod. One end of the first channel is located on one side of the sphere to communicate with the inflation component, and the other end of the first channel passes through the bottom of the vertical rod to communicate with the blind hole. The side wall of the movable block is connected to the third airbag component, and the other end of the third airbag component is connected to the inner side wall of the second accommodating groove. A second channel is provided on the side wall of the movable block, and the second channel is used to connect the third airbag component and the blind hole. The third airbag component is used to expand and stretch laterally to drive the movable block to slide.

13. The fuselage structure sag rubber molding device according to claim 12, characterized in that: A connecting sleeve is provided on one side of the shell and is threadedly connected to the cross bar. The connecting sleeve is movably extended into the first airbag component. A step groove is provided on the inner wall of the connecting sleeve on one side of the first airbag component. A movable tube is movably provided in the step groove. One end of the movable tube is located in the step groove and is connected to the second elastic component. The other end of the second elastic component is connected to the end of the step groove. The inner diameter of the movable tube is smaller than the diameter of the sphere.

14. A molding method, characterized in that: A fuselage structure sag rubber molding device according to any one of claims 1 to 13 comprises the following steps: A layer of pressure-sensitive adhesive tape is attached to both sides and the front and rear ends of the upper surface of the target groove area; Spray the sealant liquid into the target groove area through a glue gun, and finally make the sealant liquid rise above the preset height of the surface of the fuselage structural component; Place the arc-shaped groove of the scraper against one end of the target groove area and tilt the scraper at a preset angle, so that the scraper slowly scrapes the sealant from one end to the other end to scrape out a raised sealant in the middle area of ​​the sealant; Use the flat end of the scraper to remove excess glue from the pressure-sensitive adhesive tape on both sides; Lay the cut transparent hard plastic film on the surface of the raised glue; Use the flat end of the scraper to slowly scrape the hard plastic film from one end to the other, so that the hard plastic film completely fits the surface of the fuselage structure; Place the heating device on top of the hard plastic film and heat it to a preset temperature to vulcanize the sealant liquid; After the preset vulcanization time, remove the heating device; Peel off the hard plastic film and pressure-sensitive adhesive tape on the surface to form a sunken adhesive in the target groove area; Use a knife to cut off the excess glue at both ends of the front and rear sunken glue; Clean the surface of the sunken glue with cleaning fluid.

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