Anti-corrosion paint make-up pen for aircraft fastener

Abstract

The utility model relates to the technical field of aircraft manufacturing, and particularly discloses an anti-corrosion paint make-up pen for an aircraft fastener, which comprises a pen tube with a vacuum effect, a movable sleeve and a pen point with a built-in smearing piece. The vacuum effect is formed in the liquid storage space of the movable sleeve when the movable sleeve is pressed, the vacuum piston in the pen tube is made to move through the atmospheric pressure of the external space, anti-corrosion paint is pushed to be automatically supplemented to the liquid storage space from the pen tube, limitation of the using direction is avoided, the device is suitable for paint repairing of fasteners in various direction scenes on an airplane, operation is easy and convenient, and the practicability is high. And the paint repair effect is greatly improved. And the paint repairing effect is good, a uniform and smooth paint layer can be formed on the surface of the end of the fastener, and the anti-corrosion capacity of the fastener on the airplane is enhanced. And meanwhile, according to the anti-corrosion paint repairing pen for the aircraft fastener, the pen point and the smearing piece of different specifications and different types can be replaced through modular design, and the paint repairing requirements of fasteners of different types and different specifications can be met.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft manufacturing, in particular to an anti-corrosion touch-up paint pen for aircraft fasteners. Background Art

[0002] During the aircraft manufacturing and assembly process, fasteners are often needed to fix parts together. As time goes by, the fasteners will be exposed to the air for a long time and come into contact with water vapor in the air, which will cause them to rust and age, resulting in poor fixing effects and easy danger. In addition, rusted fasteners are difficult to remove and inconvenient to repair.

[0003] For this reason, it is necessary to carry out corrosion protection on the ends of the fasteners, so as to enhance the corrosion resistance and aging resistance of the fasteners. At present, the method commonly used in the prior art is: the staff holds a paint container in one hand and a brush in the other hand and uses the brush to dip some anti-corrosion paint from the paint container, and then uses the brush to manually apply it on the surface of the fastener end. However, during the operation, since the application is completely dependent on the staff's manual work, there are problems such as uneven application and incomplete coverage on the surface of the fastener end, resulting in poor anti-corrosion effect. In addition, for some situations where the operating space is small and the operating position is difficult to reach, the method of applying anti-corrosion paint with a brush is also difficult to operate and the application efficiency is low. Utility Model Content

[0004] The utility model aims to provide an aircraft fastener anti-corrosion touch-up paint pen, which can evenly apply anti-corrosion paint on the surface of the fastener end and fully cover it, has good anti-corrosion quality, can be operated with one hand, is easy to operate, and has high application efficiency.

[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0006] The utility model provides an aircraft fastener anti-corrosion touch-up paint pen, comprising:

[0007] A pen tube having a cavity inside, one end of the pen tube being provided with a first opening, and the other end being a blocking structure;

[0008] a vacuum piston, which passes through the first opening and is installed in the cavity; the vacuum piston can move along the inner wall of the pen tube, and the vacuum piston is in close contact with the inner wall of the pen tube; the vacuum piston divides the cavity into a first space and a second space, the first space is connected to the external space, and the second space is used to store liquid;

[0009] A movable sleeve comprises a plunger shell, a guide shell and an adjusting component, wherein the plunger shell is connected to one end of the pen tube provided with a first opening, the guide shell is connected to the plunger shell, and the guide shell cover is arranged outside the plunger shell, and the guide shell can slide relative to the pen tube; the plunger shell is hollow inside, the adjusting component is arranged in the plunger shell, a liquid storage space is formed between the plunger shell and the adjusting component, and a liquid outlet is arranged at one end of the guide shell away from the pen tube, when the adjusting component is in a first working position, the liquid storage space is connected to the second space, and the liquid storage space is not connected to the liquid outlet; when the adjusting component is in a second working position, the liquid storage space is not connected to the second space, and the liquid storage space is connected to the liquid outlet;

[0010] The pen tip is connected to the end of the guide shell away from the pen tube, and the pen tip is provided with a smearing piece, which can absorb the liquid flowing out of the liquid outlet and smear the liquid onto the target workpiece.

[0011] Optionally, a stopper is provided on the inner wall of the pen tube, and the stopper is used to limit the extreme position of the vacuum piston moving in a direction away from the movable sleeve.

[0012] Optionally, at least one ventilation hole is provided on the pen tube, and the ventilation hole connects the first space with the external space.

[0013] Optionally, the adjustment assembly includes a plunger rod, a two-way plug and a plunger sleeve;

[0014] The plunger shell is provided with a second opening at one end away from the pen tube, and a first flow opening at one end close to the pen tube. The head of the plunger rod is installed in the plunger shell after passing through the second opening, and the head of the plunger rod can block or open the first flow opening. The tail of the plunger rod is provided with a third opening, and the interior of the plunger rod has an injection channel, the third opening is communicated with the injection channel, and the peripheral side wall of the plunger rod is provided with a second flow opening.

[0015] The two-way plug and the plunger sleeve are sequentially sleeved on the plunger rod, a first limiting ridge is provided on the inner wall of the plunger shell, two ends of the two-way plug are respectively abutted against the first limiting ridge and the plunger sleeve, and the two-way plug can block or open the second flow port to selectively connect the liquid storage space and the injection channel.

[0016] Optionally, the movable sleeve further includes an elastic component, and two ends of the elastic component are respectively abutted against the adjustment component and the guide shell.

[0017] Optionally, the elastic component includes a spring and a spring seat, the spring sleeve is arranged on the plunger rod, the outer wall of the plunger sleeve is provided with a second limiting ridge, the inner wall of the plunger shell is provided with a first limiting step, one side of the second limiting ridge abuts against the first limiting step, the other side of the second limiting ridge abuts against one end of the spring, the other end of the spring abuts against the spring seat, and the spring seat is arranged at one end of the guide shell close to the liquid outlet.

[0018] Optionally, the spring seat includes an outer cylinder and an inner cylinder, one side of the outer cylinder is connected to one side of the inner cylinder, and a limiting groove is formed between the outer cylinder and the inner cylinder, the spring is embedded in the limiting groove, and the other side of the inner cylinder extends in the direction of the adjusting assembly, the inner cylinder is inserted into the plunger sleeve, and the inner cylinder is sleeved outside the plunger rod, a third limiting ridge is provided on the inner wall of the inner cylinder, and the tail of the plunger rod abuts against the third limiting ridge.

[0019] Optionally, the pen tip comprises a coaxially arranged cylindrical portion and a horn portion, the cylindrical portion is connected to the horn portion, and a necking opening is formed between the cylindrical portion and the horn portion;

[0020] The smearing member includes a coaxially arranged cylindrical portion and a truncated cone portion, the cylindrical portion is connected to the first bottom wall of the truncated cone portion, a necking portion is provided between the cylindrical portion and the truncated cone portion, the cylindrical portion is embedded in the cylindrical portion, the truncated cone portion is embedded in the flared portion, and the necking portion is clamped in the necking opening.

[0021] Optionally, the second bottom wall of the truncated cone portion is provided with a groove for accommodating the target workpiece, and the area of ​​the second bottom wall is larger than that of the first bottom wall.

[0022] Optionally, the plunger shell is threadedly connected to the pen tube; the guide shell is snap-fitted to the plunger shell by a snap-fit ​​structure; and the guide shell is threadedly connected to the pen tip.

[0023] The beneficial effects of the utility model are:

[0024] The utility model provides an aircraft fastener anti-corrosion touch-up paint pen, comprising a pen tube with a vacuum effect, a movable sleeve, and a pen head with a built-in smearing piece. When anti-corrosion touch-up paint is applied to the fasteners on the aircraft, the smearing piece soaked with the anti-corrosion paint is covered on the fasteners that need to be touched up by pressing the movable sleeve in a "stamp" manner, so as to complete the touch-up paint of the fasteners, thereby realizing one-handed operation, which is efficient and convenient. Specifically, when the movable sleeve is pressed, a vacuum effect is formed inside the liquid storage space of the movable sleeve, and the atmospheric pressure in the external space is used to move the vacuum piston in the pen tube, so as to push the anti-corrosion paint to be automatically replenished from the second space of the pen tube to the liquid storage space. The pen tube is not restricted by the direction of use, and is suitable for fastener touch-up paint in various directional scenes on the aircraft. The operation is simple and convenient. The touch-up paint work of the fasteners can be achieved by pressing the movable sleeve, and the touch-up paint effect is greatly improved. In addition, the touch-up paint effect is good, and a uniform and smooth paint layer can be formed on the end surface of the fasteners, thereby enhancing the anti-corrosion ability of the fasteners on the aircraft. At the same time, the aircraft fastener anti-corrosion touch-up paint pen has a modular design with replaceable pen tips and applicators of different specifications and types, which can meet the touch-up paint needs of fasteners of different types and specifications. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a structural schematic diagram of the aircraft fastener anti-corrosion touch-up paint pen provided in the first embodiment of the utility model;

[0026] Figure 2 This is an exploded view of the aircraft fastener anti-corrosion touch-up paint pen provided in the first embodiment of the utility model;

[0027] Figure 3 This is a cross-sectional view of the aircraft fastener anti-corrosion touch-up paint pen provided in the first embodiment of the utility model;

[0028] Figure 4 for Figure 3 A partial enlarged view of the middle A;

[0029] Figure 5 for Figure 3 A partial enlarged view of point B in the middle;

[0030] Figure 6 for Figure 3 A partial enlarged view of point C in the middle;

[0031] Figure 7 This is a schematic diagram of the structure of the plunger housing provided in the first embodiment of the utility model;

[0032] Figure 8 This is a schematic diagram of the structure of the plunger rod provided in the first embodiment of the utility model;

[0033] Fig. 9 This is a schematic diagram of the structure of the bidirectional plug provided in the first embodiment of the utility model;

[0034] Fig.10 This is a schematic diagram of the structure of the plunger sleeve provided in the first embodiment of the utility model;

[0035] Fig.11 This is a schematic structural diagram of the spring seat provided in the first embodiment of the utility model;

[0036] Fig.12 This is a schematic diagram of the structure of the guide housing provided in the first embodiment of the present utility model;

[0037] Fig.13 This is a structural schematic diagram of the adjustment assembly provided in the first embodiment of the utility model when it is in the first working position;

[0038] Fig.14 This is a schematic diagram of the structure of the adjustment assembly provided in the first embodiment of the utility model when it is in the second working position;

[0039] Fig.15 This is a schematic diagram of the structure of the smear member provided in the first embodiment of the utility model;

[0040] Fig.16 This is a schematic diagram of the structure of the pen tip provided in the first embodiment of the utility model;

[0041] Fig.17 This is a schematic diagram of the structure of the smear member and the pen tip after assembly provided in the second embodiment of the utility model.

[0042] In the figure:

[0043] 100, pen tube; 110, first opening; 120, stopper; 130, vent hole; 1001, first space; 1002, second space;

[0044] 200, vacuum piston;

[0045] 300, movable sleeve;

[0046] 310, plunger housing; 311, second opening; 312, first flow port; 313, first limit rib; 314, first limit step; 315, annular convex; 316, annular fixing edge; 3101, liquid storage space;

[0047] 320, guide shell; 321, liquid outlet; 322, guide column; 3221, third limiting step; 3222, liquid outlet channel; 3223, fourth limiting step; 323, fourth limiting ridge; 324, connecting cylinder; 3241, fifth limiting step; 325, fourth opening;

[0048] 330, adjustment assembly; 331, plunger rod; 3311, head; 3312, tail; 3313, third opening; 3314, injection channel; 3315, second flow port; 3316, second limiting step; 3317, sealing part; 332, two-way plug; 3321, second sealing surface; 333, plunger sleeve; 3331, second limiting ridge;

[0049] 340, spring;

[0050] 350, spring seat; 351, outer cylinder; 352, inner cylinder; 3521, third limiting rib; 3501, limiting groove;

[0051] 400, pen tip; 410, cylindrical portion; 420, flared portion; 430, necking opening;

[0052] 500, smear member; 510, cylindrical portion; 520, truncated cone portion; 521, groove; 530, necked portion;

[0053] 600, first sealing ring; 700, second sealing ring. DETAILED DESCRIPTION

[0054] The technical solution of the utility model will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0055] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions, and the first feature "above", "above" and "above" the second feature include the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. The first feature "below", "below" and "below" the second feature include the first feature being directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0056] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0057] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0058] Anti-corrosion of the ends of fasteners on aircraft is an important means to enhance the anti-corrosion ability of aircraft structural fasteners. At present, there are a large number of fasteners on aircraft that cannot be sprayed for anti-corrosion due to space factors. The fasteners can only be repainted manually using a brush, which is inconvenient and inefficient, and the quality of the repainting is difficult to guarantee.

[0059] Embodiment 1

[0060] The present embodiment provides an aircraft fastener anti-corrosion touch-up paint pen, which can utilize the vacuum effect to selectively supply the anti-corrosion paint stored in its pen tube 100 to the pen head 400, and then the pen head 400 applies the anti-corrosion paint on the surface of the target workpiece.

[0061] Specifically, Figure 1-Figure 3 As shown, the aircraft fastener anti-corrosion touch-up paint pen includes a pen tube 100, a vacuum piston 200, a movable sleeve 300, a pen head 400 and an applicator 500. The interior of the pen tube 100 has a cavity, one end of the pen tube 100 is provided with a first opening 110, and the other end is a blocking structure. The vacuum piston 200 is installed in the cavity through the first opening 110, and the vacuum piston 200 can move along the inner wall of the pen tube 100, and the vacuum piston 200 is in close contact with the inner wall of the pen tube 100. The vacuum piston 200 divides the cavity into a first space 1001 and a second space 1002, the first space 1001 is connected to the external space, and the second space 1002 is used to store liquid. Exemplarily, the liquid can be anti-corrosion paint. The target workpiece can be a fastener set on the aircraft.

[0062] The movable sleeve 300 includes a plunger shell 310, a guide shell 320 and an adjustment assembly 330. One end of the plunger shell 310 is connected to one end of the pen tube 100 provided with the first opening 110, and the other end of the plunger shell 310 is connected to the guide shell 320. The guide shell 320 is covered outside the plunger shell 310, and the guide shell 320 can slide relative to the pen tube 100. The interior of the plunger shell 310 is hollow, and the adjustment assembly 330 is arranged in the plunger shell 310. A liquid storage space 3101 is formed between the plunger shell 310 and the adjustment assembly 330. A liquid outlet 321 is provided at one end of the guide shell 320 away from the pen tube 100. The pen head 400 is connected to one end of the guide shell 320 away from the pen tube 100, and a smearing member 500 is provided on the pen head 400. The smearing member 500 can absorb liquid flowing out of the liquid outlet 321 and smear the liquid on the target workpiece.

[0063] When the adjustment component 330 is in the first working position, the liquid storage space 3101 is connected to the second space 1002. At this time, the liquid stored in the second space 1002 of the pen tube 100 can flow into the liquid storage space 3101. However, since the liquid storage space 3101 is not connected to the liquid outlet 321 at this time, the liquid in the liquid storage space 3101 cannot flow from the liquid outlet 321 to the smear member 500 on the pen head 400. In the first working position, only the function of replenishing liquid to the liquid storage space 3101 is completed. When the adjustment component 330 is in the second working position, the liquid storage space 3101 is not connected to the second space 1002. At this time, the liquid stored in the second space 1002 of the pen tube 100 no longer flows into the liquid storage space 3101. The liquid storage space 3101 is connected to the liquid outlet 321. The liquid in the liquid storage space 3101 flows from the liquid outlet 321 to the smear piece 500 on the pen head 400. In the second working position, the staff can hold the aircraft fastener anti-corrosion touch-up pen with one hand to complete the function of re-applying liquid (anti-corrosion paint) to the target workpiece.

[0064] By controlling the working position of the adjustment component 330, the aircraft fastener anti-corrosion touch-up paint pen in this embodiment can selectively flow liquid out from the pen head 400, and the liquid discharge is uniform, so that the anti-corrosion paint can be evenly applied to the end surface of the fastener. In addition, the smearing piece 500 on the pen head 400 can fully cover the end of the fastener, so that the situation where the anti-corrosion paint is not applied to part of the end surface of the fastener will not occur, the anti-corrosion quality is better, and the aircraft fastener anti-corrosion touch-up paint pen can be operated with one hand, which is convenient to operate and has a high application efficiency.

[0065] See also Figure 4In this embodiment, a stopper 120 is provided on the inner wall of the pen tube 100, and the stopper 120 is used to limit the limit position of the vacuum piston 200 moving in the direction away from the movable sleeve 300. Exemplarily, the stopper 120 can be an annular convex ridge provided on the inner wall of the pen tube 100. By providing the stopper 120, it is possible to prevent the vacuum piston 200 from abutting against the end of the pen tube 100 provided with a blocking structure when the vacuum piston 200 is installed in the pen tube 100. On the one hand, the limit position of the vacuum piston 200 moving in the direction away from the movable sleeve 300 can be limited; on the other hand, it can also provide a space for air replenishment and air intake for the first space 1001.

[0066] Specifically, at least one vent hole 130 is provided on the peripheral side wall of the pen tube 100 near the blocking structure, and the vent hole 130 connects the first space 1001 with the external space. As a result, the air pressure in the first space 1001 is the same as the atmospheric pressure in the external space. When the second space 1002 of the pen tube 100 generates negative pressure due to the outflow of liquid, due to the existence of the pressure difference, the atmospheric pressure in the first space 1001 will push the vacuum piston 200 to move toward the direction close to the pen tip 400, and at the same time, the vacuum piston 200 pushes the liquid into the liquid storage space 3101 for liquid replenishment. When the pressure in the second space 1002 is the same as the atmospheric pressure in the external space, the vacuum piston 200 stops moving, and the liquid replenishment in the liquid storage space 3101 is completed.

[0067] More preferably, in order to facilitate observation of the amount of anti-corrosion paint in the pen tube 100 , the pen tube 100 may be made of a transparent material, so that when the anti-corrosion paint in the pen tube 100 is used up, the staff can replenish it in time.

[0068] See also Figure 2 , Figure 3 and Figure 5 In this embodiment, the adjustment assembly 330 includes a plunger rod 331, a two-way plug 332 and a plunger sleeve 333. The plunger housing 310 has a second opening 311 at one end away from the pen tube 100, and a first flow opening 312 at one end close to the pen tube 100. The head 3311 of the plunger rod 331 passes through the second opening 311 and is installed in the plunger housing 310. The head 3311 of the plunger rod 331 can block or open the first flow opening 312. The tail 3312 of the plunger rod 331 has a third opening 3313. The interior of the plunger rod 331 has a liquid injection channel 3314. The third opening 3313 is connected to the liquid injection channel 3314. The side wall of the plunger rod 331 has a second flow opening 3315. The two-way plug 332 and the plunger sleeve 333 are sequentially sleeved on the plunger rod 331. A first limiting rib 313 is provided on the inner wall of the plunger shell 310. Both ends of the two-way plug 332 are respectively abutted against the first limiting rib 313 and the plunger sleeve 333. The two-way plug 332 can block or open the second flow port 3315 to selectively connect the liquid storage space 3101 and the injection channel 3314.

[0069] When the adjustment assembly 330 is in the first working position (see Fig.13 ), the head 3311 of the plunger rod 331 opens the first flow port 312 on the plunger housing 310, the two-way plug 332 is sealed with the plunger rod 331, and the two-way plug 332 blocks the second flow port 3315 on the plunger rod 331. At this time, liquid can be replenished from the second space 1002 of the pen tube 100 into the liquid storage space 3101, but will not pass through the second flow port 3315 into the injection channel 3314. When the adjustment component 330 is in the second working position (see Fig.14 ), the plunger rod 331 moves towards the plunger shell 310 under the push of the guide shell 320 until the head 3311 of the plunger rod 331 blocks the first flow port 312 on the plunger shell 310. At this time, the plunger rod 331 is away from one end of the two-way plug 332, and the seal between the two is released. The second flow port 3315 on the plunger rod 331 is exposed to the liquid storage space 3101. At this time, the liquid can enter the injection channel 3314 from the liquid storage space 3101, and then the liquid flows to the liquid outlet 321 on the guide shell 320 through the injection channel 3314, and then flows from the liquid outlet 321 to the smear member 500 on the pen head 400.

[0070] It should be noted that when the plunger rod 331 moves along the inner wall of the plunger shell 310 toward the pen barrel 100, the plunger rod 331 separates from the two-way plug 332, and the second flow port 3315 on the plunger rod 331 is exposed. At the same time, the head 3311 of the plunger rod 331 blocks the first flow port 312 on the plunger shell 310. Due to the squeezing of the plunger rod 331, the space inside the liquid storage space 3101 becomes smaller. At this time, the liquid can flow out from the injection channel 3314 inside the plunger rod 331 to the liquid outlet 321 on the guide shell 320. When the plunger rod 331 moves along the inner wall of the plunger shell 310 in a direction away from the pen tube 100, the plunger rod 331 is sealed and connected with the two-way plug 332, and the second flow port 3315 on the plunger rod 331 is blocked by the two-way plug 332. At the same time, the head 3311 of the plunger rod 331 leaves the first flow port 312 on the plunger shell 310, and the first flow port 312 is opened. At this time, since part of the liquid in the liquid storage space 3101 has flowed out from the injection channel 3314, the liquid in the liquid storage space 3101 is reduced, but the space is enlarged. Therefore, the pressure in the liquid storage space 3101 becomes smaller and lower than the atmospheric pressure of the external space. At this time, the atmospheric pressure of the external space will push the vacuum piston 200 to move in a direction close to the pen tip 400, and the liquid is squeezed into the liquid storage space 3101, completing the liquid replenishment work in the liquid storage space 3101, which is convenient for subsequent use. The liquid replenishment process is not limited by the use direction and is suitable for fastener touch-up in various directional scenes on aircraft. In addition, when replenishing the liquid, the vacuum piston 200 moves under the thrust of the atmospheric pressure of the external space, pushing all the liquid (anti-corrosion paint) in the second space 1002 to be discharged into the liquid storage space 3101, so that the liquid can be fully used without waste.

[0071] Alternatively, see Figure 8 and Fig. 9 , a sealing portion 3317 is provided on the peripheral side wall of the plunger rod 331, and the sealing portion 3317 has a first sealing surface, and a second sealing surface 3321 is provided on the inner wall of the two-way plug 332. When the sealing portion 3317 is in contact with the sealing surface, the two-way plug 332 completely wraps the peripheral side wall of the plunger rod 331 and completely covers the second flow opening 3315 on the peripheral side wall of the plunger rod 331. At this time, the first sealing surface of the plunger rod 331 is sealed and connected with the second sealing surface 3321 of the two-way plug 332. Exemplarily, the sealing portion 3317 can be set to be conical, with an inclined first sealing surface, and the second sealing surface 3321 on the inner wall of the two-way plug 332 is a conical inclined surface matching the first sealing surface.

[0072] Furthermore, the movable sleeve 300 in this embodiment further includes an elastic component, and the two ends of the elastic component are respectively abutted against the adjustment component 330 and the guide shell 320. By setting the elastic component, the automatic reset of the guide shell 320 can be achieved. The automatic reset process of the guide shell 320 is also the process of the adjustment component 330 switching from the second working position to the first working position.

[0073] Specifically, see 5. Figure 7 and Fig.10 The elastic component includes a spring 340 and a spring seat 350. The spring 340 is sleeved on the plunger rod 331. The outer wall of the plunger sleeve 333 is provided with a second limiting rib 3331. The inner wall of the plunger shell 310 is provided with a first limiting step 314. One side of the second limiting rib 3331 abuts against the first limiting step 314. The other side of the second limiting rib 3331 abuts against one end of the spring 340. The other end of the spring 340 abuts against the spring seat 350. The spring seat 350 is arranged at one end of the guide shell 320 near the liquid outlet 321. Therefore, the plunger sleeve 333 can be pressed against the plunger shell 310 by the elastic force of the spring 340, and the spring seat 350 can be pressed against one end of the guide shell 320 provided with the liquid outlet 321. When the spring 340 is compressed, the guide shell 320 can push the spring seat 350 to move, and then the spring seat 350 pushes the plunger rod 331 to move, so that the adjustment assembly 330 is switched from the first working position to the second working position. It should be noted that during this process, the plunger shell 310, the two-way plug 332 and the plunger sleeve 333 all maintain their positions unchanged, and only the position of the plunger rod 331 changes.

[0074] Alternatively, see Figure 5 , Figure 6 and Fig.11 The spring seat 350 includes an outer cylinder 351 and an inner cylinder 352. One side of the outer cylinder 351 is connected to one side of the inner cylinder 352, and a limiting groove 3501 is formed between the outer cylinder 351 and the inner cylinder 352. The spring 340 is embedded in the limiting groove 3501. The other side of the inner cylinder 352 extends in the direction of the adjustment assembly 330. The inner cylinder 352 is inserted into the plunger sleeve 333, and the inner cylinder 352 is sleeved outside the plunger rod 331. The inner wall of the inner cylinder 352 is provided with a third limiting ridge 3521, and the tail 3312 of the plunger rod 331 is provided with a second limiting step 3316 (see Figure 8 ), the third limiting rib 3521 abuts against the second limiting step 3316. Thus, through the arrangement of the third limiting rib 3521, when the guide housing 320 pushes the spring seat 350 to move, the spring seat 350 can continue to push the plunger rod 331 to move synchronously.

[0075] The guide housing 320 is provided with a guide post 322 ( Fig.12), the inner cylinder 352 of the spring seat 350 is sleeved on the guide column 322. The outer wall of the guide column 322 is provided with a third limiting step 3221, and the inner cylinder 352 of the spring seat 350 abuts against the third limiting step 3221, thereby achieving the limiting of the spring seat 350. Further, the end of the guide column 322 away from the pen head 400 is plug-connected with the plunger rod 331, and a liquid outlet channel 3222 is provided in the guide column 322, and the liquid outlet channel 3222 is connected to the injection channel 3314 in the plunger rod 331. Exemplarily, a fourth limiting step 3223 is provided at one end of the guide post 322 connected to the plunger rod 331, the tail 3312 of the plunger rod 331 is inserted into the guide post 322 and abuts against the fourth limiting step 3223, and the third limiting ridge 3521 on the spring seat 350 is clamped between the second limiting step 3316 of the tail 3312 of the plunger rod 331 and the end of the guide post 322 away from the liquid outlet 321. Thus, the spring seat 350 can push the plunger rod 331 to move in the plunger sleeve 333 and the two-way plug 332, and the inner cylinder 352 of the spring seat 350 can move along the inner wall of the plunger sleeve 333. The plunger sleeve 333 can guide the movement of the spring seat 350, ensuring that the plunger rod 331, the spring seat 350 and the guide post 322 are coaxial and move along the axial direction of the pen tube 100. Therefore, through the setting of the elastic component, when the guide shell 320 is pressed and reset under the force of the spring 340, a vacuum effect can be formed in the second space 1002 of the pen tube 100 and the liquid storage space 3101 of the plunger shell 310, so that the vacuum piston 200 in the pen tube 100 moves toward the direction close to the pen tip 400, pushing the liquid to automatically replenish the liquid storage space 3101 of the plunger shell 310. It is not limited by the direction of use and is suitable for fastener touch-up painting in various directional scenes on airplanes, with better adaptability.

[0076] Further, the guide shell 320 is provided with a fourth opening 325 at one end close to the pen tube 100, and the plunger shell 310 is inserted into the guide shell 320 through the fourth opening 325. The inner wall of the guide shell 320 and the outer wall of the plunger shell 310 are connected by a snap-fit ​​structure. Exemplarily, a fourth limiting rib 323 is provided on the inner wall surface of the guide shell 320, and an annular clamping protrusion 315 is provided at the end of the plunger shell 310 provided with the second opening 311, and the annular clamping protrusion 315 and the fourth limiting rib 323 form a snap-fit ​​structure, and the annular clamping protrusion 315 and the fourth limiting rib 323 are snap-fitted.

[0077] Continue to see Figure 3 , Fig.15 and Fig.16, the pen tip 400 in this embodiment is detachably connected to the guide shell 320. Exemplarily, one end of the guide shell 320 having the liquid outlet 321 is provided with a connecting cylinder 324, the pen tip 400 is detachably connected to the connecting cylinder 324, and the diameter of the connecting cylinder 324 is smaller than the diameter of the main part of the guide shell 320, and a fifth limiting step 3241 is formed between the connecting cylinder 324 and the main part of the guide shell 320. The pen tip 400 and the smear member 500 can be combined into a modular whole, and the pen tips 400 and the smear member 500 of different specifications can be replaced in different usage scenarios to meet the requirements of touch-up paint of fasteners of different types and specifications. Optionally, the smear member 500 can be set as a sponge.

[0078] Exemplarily, the pen tip 400 in this embodiment includes a coaxially arranged cylindrical portion 410 and a trumpet portion 420, the cylindrical portion 410 is connected to the trumpet portion 420, and a necking opening 430 is formed between the cylindrical portion 410 and the trumpet portion 420. The smearing member 500 includes a coaxially arranged cylindrical portion 510 and a truncated cone portion 520, the cylindrical portion 510 is connected to the first bottom wall of the truncated cone portion 520, a necking portion 530 is provided between the cylindrical portion 510 and the truncated cone portion 520, the cylindrical portion 410 is embedded in the cylindrical portion 410, the truncated cone portion 520 is embedded in the trumpet portion 420, and the necking portion 530 is clamped in the necking opening 430. By providing the necking portion 530 and the necking opening 430 that cooperate with each other, the smearing member 500 can be well fixed on the pen tip 400, and the smearing member 500 is prevented from falling off from the pen tip 400, and the fixing effect is good.

[0079] As an optional technical solution, there is a gap between the cylindrical portion 410 of the pen tip 400 and the cylindrical portion 510 of the smear member 500, and the gap can be used to accommodate the connecting cylinder 324. Exemplarily, the outer wall of the connecting cylinder 324 is provided with an external thread, the inner wall of the cylindrical portion 410 is provided with an internal thread, and the connecting cylinder 324 and the cylindrical portion 410 are connected by threaded matching. Of course, in other embodiments, the cylindrical portion 410 of the pen tip 400 and the cylindrical portion 510 of the smear member 500 may not be provided with a gap, and the connecting cylinder 324 is sleeved on the outer side of the pen tip 400. Exemplarily, the inner wall of the connecting cylinder 324 is provided with an external thread, the inner wall of the cylindrical portion 410 is provided with an internal thread, and the connecting cylinder 324 and the cylindrical portion 410 are connected by threaded matching.

[0080] Continue to see Fig.13, the second bottom wall of the truncated cone portion 520 is provided with a groove 521 for accommodating the target workpiece, and the area of ​​the second bottom wall is larger than the area of ​​the first bottom wall. As a result, the smearing member 500 can completely cover the end of the fastener, and the smearing member 500 evenly applies the anti-corrosion paint to the end of the fastener, and the anti-corrosion paint can completely cover all parts of the end of the fastener, and the anti-corrosion effect is good. For example, for some shorter fasteners, such as rivets, nail heads, pier heads, etc., the groove 521 provided on the truncated cone portion 520 of the smearing member 500 is conical.

[0081] Continue to see Figure 2 and Figure 5 The plunger housing 310 and the pen tube 100 can also be connected by threaded fitting. Specifically, an external thread is provided on the outer wall surface of the plunger housing 310, and an internal thread is provided on one end of the pen tube 100 having the first opening 110, and the plunger housing 310 and the pen tube 100 are connected by threaded fitting.

[0082] Furthermore, the aircraft fastener anti-corrosion touch-up paint pen in this embodiment includes a first sealing ring 600. An annular fixing edge 316 is provided on the outer wall of the plunger shell 310, and the annular fixing edge 316 extends in the radial direction of the plunger shell 310. The first sealing ring 600 is sandwiched between the annular fixing edge 316 and the end of the pen tube 100 provided with the first opening 110. The first sealing ring 600 can ensure a good sealing effect between the plunger shell 310 and the pen tube 100, and the external thread on the outer wall of the plunger shell 310 is provided on one side of the annular fixing edge 316 near the first flow port 312.

[0083] In this embodiment, the aircraft fastener anti-corrosion touch-up paint pen further includes a second sealing ring 700, which is sandwiched between the cylindrical portion 410 of the pen head 400 and the fifth limiting step 3241 of the guide shell 320. The second sealing ring 700 can ensure a good sealing effect between the guide shell 320 and the pen head 400 to prevent leakage of liquid (anti-corrosion paint).

[0084] Embodiment 2

[0085] This embodiment also provides an aircraft fastener anti-corrosion paint touch-up pen, which is different from the aircraft fastener anti-corrosion paint touch-up pen in the first embodiment in that the arrangement scheme of the pen head 400 and the groove 521 on the smear member 500 is different in this embodiment.

[0086] Specifically, see Fig.17In this embodiment, the height of the trumpet portion 420 of the pen tip 400 is higher, and the height of the truncated cone portion 520 of the smear piece 500 is equal to the height of the trumpet portion 420 of the pen tip 400. The groove 521 provided on the truncated cone portion 520 of the smear piece 500 is cylindrical, so that the pen tip 400 and the smear piece 500 can be applied to fasteners with higher end heights. For example, high locking nail sleeves, nuts, etc. Through modular design, the replaceable pen tips 400 and the smear piece 500 of different specifications and types make it possible for the utility model to be used for repainting the ends of various types of fasteners in the aircraft manufacturing and assembly process, with good adaptability, and easy and quick disassembly and assembly.

[0087] The remaining structures in this embodiment are the same as those in the first embodiment and will not be described again here.

[0088] The operation process of installing the aircraft fastener anti-corrosion touch-up paint pen is as follows:

[0089] 1) First, select a pen tip 400 and an smear member 500 that match the target workpiece, and assemble the pen tip 400, the smear member 500, the second sealing ring 700 and the guide housing 320;

[0090] 2) Then, the second space 1002 of the pen tube 100 is filled with anti-corrosion paint, and the plunger housing 310 is assembled with the pen tube 100 to ensure that the second space 1002 is filled with anti-corrosion paint and to prevent air from entering the second space 1002;

[0091] 3) The plunger rod 331, the two-way plug 332, the plunger sleeve 333, the spring 340 and the spring seat 350 are sequentially installed into the plunger shell 310, and then the guide shell 320 is sleeved outside the plunger shell 310 and the pen tube 100, and the guide shell 320 is pushed in the direction close to the pen tube 100 until the annular protrusion 315 is engaged with the fourth limiting ridge 323. At this time, the two ends of the spring 340 will respectively abut against the plunger sleeve 333 and the spring seat 350, and then the elastic restoring force of the spring 340 will push the guide shell 320 in the direction away from the pen tube 100, so that a preset gap is maintained between the guide shell 320 and the plunger shell 310. At this time, the adjustment assembly 330 is located in the first working position;

[0092] At this point, the assembly process of the aircraft fastener anti-corrosion touch-up paint pen is completed.

[0093] Furthermore, the operation process of using the aircraft fastener anti-corrosion touch-up paint pen is as follows:

[0094] 1) First, complete the preparation for the wetting of the smear member 500. Hold the pen tube 100 and make the pen tip 400 stand against any test block. By pressing the pen tip 400 several times, the spring 340 in the guide shell 320 is compressed, and the adjustment component 330 is switched to the second working position. The smear member 500 is completely wetted with the anti-corrosion paint, and a "stamping" experiment is performed on the test block to ensure that the smear member 500 can perform a complete touch-up operation on the test block when the pen tip 400 is pressed, so that the subsequent aircraft fastener anti-corrosion touch-up paint pen can form a complete, uniform, and smooth paint layer on the end surface of the fastener;

[0095] 2) The staff member holds the pen tube 100, aligns the groove 521 of the soaked smearing member 500 with the target workpiece (i.e., the fastener) and buckles it on the end of the fastener, and presses the pen tip 400 to make the smearing member 500 "stamp" to quickly complete the paint touch-up operation.

[0096] It should be noted that when the anti-corrosion paint adsorbed in the smear member 500 continues to gradually decrease with the increase in the number of touch-ups, through the action of pressing the pen tip 400, the anti-corrosion paint in the second space 1002 of the pen tube 100 can be synchronously replenished to the liquid storage space 3101 in real time, and then flow from the liquid storage space 3101, the injection channel 3314, the liquid outlet channel 3222 and the liquid outlet 321 to the smear member 500, keeping the smear member 500 in a moist state, thereby ensuring the continuity of the touch-up operation.

[0097] This aircraft fastener anti-corrosion touch-up paint pen can be operated with one hand when touch-up painting, which is convenient and quick. The touch-up work of the fastener end can be completed with just one "cap", greatly improving work efficiency. And because this aircraft fastener anti-corrosion touch-up paint pen utilizes the vacuum effect, by pressing the spring 340 with the help of the thrust of atmospheric pressure to push the vacuum piston 200 to push the anti-corrosion paint to automatically replenish the liquid storage space 3101, it is clean, waste-free, and not limited by space. It is suitable for fastener touch-up painting in various directions on the aircraft. In addition, the end of the fastener painted with the aircraft fastener anti-corrosion touch-up paint pen has a uniform, smooth and beautiful surface paint layer, which greatly improves the anti-corrosion effect and aesthetics of the fastener, and improves the aircraft quality and customer satisfaction.

[0098] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all implementation methods here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. An aircraft fastener anti-corrosion touch-up paint pen, characterized in that: include: A pen tube (100) having a cavity therein, one end of the pen tube (100) being provided with a first opening (110) and the other end being a blocking structure; a vacuum piston (200) which passes through the first opening (110) and is installed in the cavity; the vacuum piston (200) is capable of moving along the inner wall of the pen tube (100), and the vacuum piston (200) is in close contact with the inner wall of the pen tube (100); the vacuum piston (200) divides the cavity into a first space (1001) and a second space (1002); the first space (1001) is in communication with an external space, and the second space (1002) is used to store liquid; The movable sleeve (300) comprises a plunger shell (310), a guide shell (320) and an adjustment assembly (330); the plunger shell (310) is connected to one end of the pen tube (100) provided with a first opening (110); the guide shell (320) is connected to the plunger shell (310), and the guide shell (320) is arranged outside the plunger shell (310); the guide shell (320) can slide relative to the pen tube (100); the plunger shell (310) is hollow inside, the adjustment assembly (330) is arranged inside the plunger shell (310), and the plunger shell (310) and the adjustment assembly (330) are connected to each other. A liquid storage space (3101) is formed between the adjusting component (330), and a liquid outlet (321) is provided at one end of the guide shell (320) away from the pen tube (100); when the adjusting component (330) is in the first working position, the liquid storage space (3101) is communicated with the second space (1002), and the liquid storage space (3101) is not communicated with the liquid outlet (321); when the adjusting component (330) is in the second working position, the liquid storage space (3101) is not communicated with the second space (1002), and the liquid storage space (3101) is communicated with the liquid outlet (321); A pen tip (400), the pen tip (400) is connected to an end of the guide shell (320) away from the pen tube (100), and a smearing piece (500) is provided on the pen tip (400), and the smearing piece (500) can absorb liquid flowing out of the liquid outlet (321) and smear the liquid onto a target workpiece.

2. The aircraft fastener anti-corrosion touch-up paint pen according to claim 1, characterized in that: A stopper (120) is provided on the inner wall of the pen tube (100), and the stopper (120) is used to limit the extreme position of the vacuum piston (200) moving in a direction away from the movable sleeve (300).

3. The aircraft fastener anti-corrosion touch-up paint pen according to claim 1, characterized in that: At least one vent hole (130) is provided on the pen tube (100), and the vent hole (130) connects the first space (1001) with the external space.

4. The aircraft fastener anti-corrosion touch-up paint pen according to claim 1, characterized in that: The adjustment assembly (330) comprises a plunger rod (331), a two-way plug (332) and a plunger sleeve (333); The plunger shell (310) is provided with a second opening (311) at one end away from the pen tube (100), and a first flow opening (312) at one end close to the pen tube (100); the head (3311) of the plunger rod (331) is installed in the plunger shell (310) after passing through the second opening (311); the head (3311) of the plunger rod (331) can block or open the first flow opening (312); the tail (3312) of the plunger rod (331) is provided with a third opening (3313); the interior of the plunger rod (331) is provided with a liquid injection channel (3314); the third opening (3313) is communicated with the liquid injection channel (3314); and a second flow opening (3315) is provided on the peripheral side wall of the plunger rod (331); The two-way plug (332) and the plunger sleeve (333) are sequentially sleeved on the plunger rod (331); a first limiting ridge (313) is provided on the inner wall of the plunger shell (310); two ends of the two-way plug (332) are respectively abutted against the first limiting ridge (313) and the plunger sleeve (333); the two-way plug (332) can block or open the second flow port (3315) to selectively connect the liquid storage space (3101) and the injection channel (3314).

5. The aircraft fastener anti-corrosion touch-up paint pen according to claim 4, characterized in that: The movable sleeve (300) further comprises an elastic component, two ends of which are respectively in contact with the adjustment component (330) and the guide shell (320).

6. The aircraft fastener anti-corrosion touch-up paint pen according to claim 5, characterized in that: The elastic component comprises a spring (340) and a spring seat (350), wherein the spring (340) is sleeved on the plunger rod (331), the outer wall of the plunger sleeve (333) is provided with a second limiting rib (3331), the inner wall of the plunger shell (310) is provided with a first limiting step (314), one side of the second limiting rib (3331) abuts against the first limiting step (314), the other side of the second limiting rib (3331) abuts against one end of the spring (340), the other end of the spring (340) abuts against the spring seat (350), and the spring seat (350) is arranged in the guide shell (320) at one end close to the liquid outlet (321).

7. The aircraft fastener anti-corrosion touch-up paint pen according to claim 6, characterized in that: The spring seat (350) comprises an outer cylinder (351) and an inner cylinder (352), one side of the outer cylinder (351) is connected to one side of the inner cylinder (352), and a limiting groove (3501) is formed between the outer cylinder (351) and the inner cylinder (352), the spring (340) is embedded in the limiting groove (3501), the other side of the inner cylinder (352) extends in the direction of the adjusting assembly (330), the inner cylinder (352) is inserted into the plunger sleeve (333), and the inner cylinder (352) is sleeved outside the plunger rod (331), and a third limiting rib (3521) is provided on the inner wall of the inner cylinder (352), and the tail (3312) of the plunger rod (331) abuts against the third limiting rib (3521).

8. The aircraft fastener anti-corrosion touch-up paint pen according to claim 1, characterized in that: The pen tip (400) comprises a coaxially arranged cylindrical portion (410) and a horn portion (420), wherein the cylindrical portion (410) is connected to the horn portion (420), and a necking opening (430) is formed between the cylindrical portion (410) and the horn portion (420); The smear member (500) comprises a coaxially arranged cylindrical portion (510) and a truncated cone portion (520), wherein the cylindrical portion (510) is connected to a first bottom wall of the truncated cone portion (520), a necking portion (530) is provided between the cylindrical portion (510) and the truncated cone portion (520), the cylindrical portion (410) is embedded in the cylindrical portion (410), the truncated cone portion (520) is embedded in the flared portion (420), and the necking portion (530) is clamped in the necking opening (430).

9. The aircraft fastener anti-corrosion touch-up paint pen according to claim 8, characterized in that: The second bottom wall of the truncated cone portion (520) is provided with a groove (521) for accommodating the target workpiece, and the area of ​​the second bottom wall is greater than that of the first bottom wall.

10. The aircraft fastener anti-corrosion touch-up paint pen according to claim 1, characterized in that: The plunger shell (310) is threadedly connected to the pen tube (100); the guide shell (320) is snap-fitted to the plunger shell (310) using a snap-fit ​​structure; and the guide shell (320) is threadedly connected to the pen tip (400).

Images