Dismantling tool for closed rubber plug cap on aircraft skin

Abstract

The utility model discloses a tool for removing a closed rubber plug cap on an aircraft skin, and relates to the technical field of aircraft manufacturing. Comprising an aircraft skin body, a round hole is formed in the surface of the aircraft skin body, a rubber plug cap body is arranged in the round hole, a shell is arranged outside the head of the rubber plug cap body, an ejection hole is formed in the middle of the rubber plug cap body, and an outer core rod is movably arranged in the ejection hole; supporting rods are movably arranged on the two sides of the outer core rod, and the ends, away from the outer core rod, of the supporting rods are hinged to the supporting umbrella. By arranging the shell, the outer core rod, the supporting rod, the supporting umbrella, the pull-out nut, the inner core rod and the fixed self-locking nut, the bottom of the rubber plug cap body can be perfectly clamped, tight connection between the dismounting tool and the rubber plug cap body is ensured through precise clamping, stable support is provided for subsequent dismounting operation, and the dismounting efficiency is improved. And the whole dismantling process is safer and more reliable.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, specifically a tool for removing sealing rubber caps on aircraft skin. Background Technology

[0002] Aircraft skin and other hollow structural components often require circular holes to meet various functional requirements, such as wiring, ventilation, heat dissipation, or equipment installation. To ensure the sealing of these circular holes, prevent foreign object intrusion, and maintain the integrity of the overall structure, sealing rubber caps are usually installed at the holes.

[0003] In actual aircraft production and maintenance, situations often arise where rework of the skin or removal of installed rubber plugs are necessary. Because the contact diameter between the rubber plug and the skin is small and the rubber is too thin, pulling forcefully outwards from the outside of the skin can easily cause the plug to break, leaving some rubber plug inside the skin cavity as foreign matter, threatening flight safety. Currently, the common method for removing these damaged and retained rubber plugs is to dismantle the skin itself. This process is not only complex and tedious, requiring significant time and manpower, but also introduces a series of additional risks.

[0004] In view of the numerous drawbacks of existing technologies in the disassembly of rubber caps, a novel cap removal tool is proposed. This tool employs an innovative umbrella-like structure design. During operation, precise positioning is first achieved through the edge of the cap's head, ensuring the tool's piercing point accurately penetrates the cap's head. Once the piercing point enters the cavity, the umbrella-like structure automatically expands and locks the bottom of the cap. Subsequently, the tight engagement of the threaded nut on the outer pull rod generates a pulling force from inside the cavity to the outside, smoothly pushing the cap out. This novel cap removal tool significantly reduces the risk of cap breakage during disassembly, fundamentally preventing the generation of foreign objects and providing strong protection for flight safety. Simultaneously, since the skin does not need to be removed, it avoids a significant amount of extra work associated with skin disassembly and reassembly, effectively reducing various risks that may arise during rework and improving the efficiency and quality of aircraft maintenance work. Utility Model Content

[0005] This invention provides a tool for removing sealing rubber caps on aircraft skin, in order to solve the problems in the prior art.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a tool for removing sealed rubber caps on aircraft skin, comprising an aircraft skin body, a circular hole on the surface of the aircraft skin body, a rubber cap body disposed within the circular hole, an outer shell disposed on the outer side of the head of the rubber cap body, an ejection hole in the middle of the rubber cap body, an outer core rod movably disposed within the ejection hole, support rods movably disposed on both sides of the outer core rod, the end of the support rod away from the outer core rod being hinged to a support umbrella, a pull-out nut movably disposed on the outer core rod, the pull-out nut being threadedly connected to the outer core rod, and an inner core rod movably disposed inside the outer core rod.

[0007] Furthermore, the material of the rubber plug body is rubber.

[0008] Furthermore, a through hole adapted to the outer core rod is provided in the middle of the outer shell.

[0009] Furthermore, the connection between the support rod and the outer core rod is hinged.

[0010] Furthermore, one end of the inner core rod is fixedly connected to the support umbrella.

[0011] Furthermore, a self-locking nut is movably provided on the outside of the inner core rod, and the connection between the self-locking nut and the inner core rod is a threaded connection.

[0012] Compared with the prior art, this utility model provides a tool for removing sealing rubber caps on aircraft skin, which has the following advantages:

[0013] 1. This tool for removing sealed rubber caps on aircraft skin, by setting up an outer shell, outer core rod, support rod, support umbrella, pull-out nut, inner core rod, and fixing self-locking nut, can perfectly lock the bottom of the rubber cap body. This precise locking not only ensures a tight connection between the removal tool and the rubber cap body, but also provides a stable support for subsequent removal operations, making the entire removal process safer and more reliable.

[0014] 2. This tool for removing sealed rubber caps on aircraft skin features a support rod, a support umbrella, and an inner core rod. Moving the inner core rod causes the support rod to rotate, which in turn drives the support umbrella to open or retract. This flexible opening and closing mechanism allows the removal tool to be easily inserted from the outside of the rubber cap and quickly deploy the support umbrella when in position, making full preparations for subsequent removal work and effectively improving work efficiency.

[0015] 3. This tool for removing sealing rubber caps on aircraft skin changes the force applied to the rubber cap during removal from tension to thrust. This thrust is applied evenly to the rubber cap, allowing it to be smoothly pushed out without tension. This ensures that the rubber cap is always supported and protected during removal, reducing the risk of breakage and debris, and improving the safety and reliability of the removal process.

[0016] 4. This tool for removing the sealing rubber cap on aircraft skin consists of a housing, an outer core rod, and a pull-out nut. With the cooperation of the housing, the nut can be easily pulled out by turning the knob, which in turn moves the outer core rod and generates an outward pulling force to push out the rubber cap body. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of this utility model;

[0018] In the diagram: 101, aircraft skin body; 201, rubber plug body; 202, outer shell; 301, outer core rod; 302, support rod; 303, support umbrella; 401, pull-out nut; 402, inner core rod; 403, fixing self-locking nut. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0020] Please see Figure 1 This utility model discloses a tool for removing sealing rubber caps on aircraft skin, including an aircraft skin body 101. The surface of the aircraft skin body 101 has a circular hole, and a rubber cap body 201 is disposed in the circular hole. The head of the rubber cap body 201 is provided with a shell 202. The middle of the rubber cap body 201 has an ejection hole, and an outer core rod 301 is movably disposed in the ejection hole. Support rods 302 are movably disposed on both sides of the outer core rod 301. The end of the support rod 302 away from the outer core rod 301 is hinged to a support umbrella 303. A pull-out nut 401 is movably disposed on the outside of the outer core rod 301. The pull-out nut 401 is connected to the outer core rod 301 by a threaded connection. An inner core rod 402 is movably disposed inside the outer core rod 301.

[0021] Specifically, the rubber plug body 201 is made of rubber.

[0022] In this embodiment, by setting the rubber plug body 201, the rubber has excellent elasticity and flexibility, which allows the rubber plug body 201 to fit tightly against the edge of the round hole, forming a reliable sealing barrier, effectively preventing foreign objects from entering the cavity and ensuring the normal operation of the aircraft's internal equipment.

[0023] Specifically, the outer shell 202 has a through hole in the middle that is adapted to the outer core rod 301.

[0024] In this embodiment, by setting the outer shell 202 and the outer core rod 301, the opening of the through hole allows the outer core rod 301 to be accurately inserted from the head of the rubber plug body 201 into the inner side of the aircraft skin body 101 and the head of the rubber plug body 201, and to maintain a stable relative position, thereby achieving precise positioning.

[0025] Specifically, the connection between the support rod 302 and the outer core rod 301 is a hinge.

[0026] In this embodiment, by setting the outer core rod 301 and the support rod 302, the hinged connection allows the support rod 302 to automatically adjust its angle according to the force. At the same time, the symmetrically arranged support rods 302 on both sides can form a stable triangular support structure, which further improves the stability and reliability of the tool and ensures that there will be no shaking or displacement during the pulling process.

[0027] Specifically, one end of the inner core rod 402 is fixedly connected to the support umbrella 303.

[0028] In this embodiment, by setting up a support umbrella 303 and an inner core rod 402, when the inner core rod 402 moves inside the outer core rod 301, it will directly drive the support umbrella 303 to perform corresponding movements, so as to ensure that the support umbrella 303 can accurately complete the opening and closing operation according to the design requirements.

[0029] Specifically, a self-locking nut 403 is movably provided on the outside of the inner core rod 402, and the connection between the self-locking nut 403 and the inner core rod 402 is a threaded connection.

[0030] In this embodiment, by setting an inner core rod 402 and a self-locking nut 403, the position of the inner core rod 402 can be adjusted and fixed in the desired position by rotating the self-locking nut 403. This helps to prevent the self-locking nut 403 from loosening and ensures that the position of the inner core rod 402 remains stable.

[0031] In use, the support umbrella 303 and support rod 302 are retracted into the outer core rod 301 and positioned by the outer shell 202, so that they are inserted from the head of the rubber plug body 201 into the inner side of the aircraft skin body 101 and the rubber plug body 201. Then, by pushing the inner core rod 402, the support umbrella 303 and support rod 302 are opened and locked into the bottom of the rubber plug body 201, and the self-locking nut 403 is locked to lock the positions of the inner core rod 402, support umbrella 303 and support rod 302. Then, by turning the knob to pull out the nut 401, the outer core rod 301 and the outer shell 202 generate an outward pulling force, so that the rubber plug body 201 is completely pushed out of the cavity.

[0032] In summary, this tool for removing sealed rubber caps on aircraft skin, through its outer shell 202, outer core rod 301, support rod 302, support umbrella 303, pull-out nut 401, inner core rod 402, and fixing self-locking nut 403, perfectly locks the bottom of the rubber cap body 201. This precise locking not only ensures a tight connection between the removal tool and the rubber cap body 201, but also provides stable support for subsequent removal operations, making the entire removal process safer and more reliable. By setting up the support rod 302, support umbrella 303, and inner core rod 402, moving the inner core rod 402 causes the support rod 302 to rotate, thereby opening or retracting the support umbrella 303. This flexible opening and closing mechanism allows the removal tool to be easily inserted from the outside of the rubber cap body 201. Upon arrival, the support umbrella 303 is quickly deployed to prepare for subsequent dismantling work, effectively improving work efficiency. By changing the force distribution of the original rubber plug body 201 during dismantling from tension to thrust, this thrust is evenly applied to the rubber plug body 201, allowing it to be smoothly pushed out without tension. This ensures that the rubber plug body 201 is always supported and protected during dismantling, reducing the risk of breakage and debris, and improving the safety and reliability of the dismantling process. With the outer shell 202, outer core rod 301, and pull-out nut 401, the nut 401 can be easily pulled out by turning the knob with the cooperation of the outer shell 202, thereby moving the outer core rod 301 and generating an outward pulling force to push out the rubber plug body 201.

[0033] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A tool for removing sealing rubber caps on aircraft skin, comprising an aircraft skin body (101), characterized in that: The surface of the aircraft skin body (101) is provided with a circular hole, and a rubber plug body (201) is provided in the circular hole. The outer shell (202) is provided on the outside of the head of the rubber plug body (201). The rubber plug body (201) is provided with an ejection hole in the middle, and an outer core rod (301) is movably provided in the ejection hole. Support rods (302) are movably provided on both sides of the outer core rod (301). The end of the support rod (302) away from the outer core rod (301) is hinged to the support umbrella (303). A pull-out nut (401) is movably provided on the outside of the outer core rod (301). The connection between the pull-out nut (401) and the outer core rod (301) is a threaded connection. An inner core rod (402) is movably provided inside the outer core rod (301).

2. A tool for removing a closed rubber cap on an aircraft skin as defined in claim 1, characterized in that: The rubber cap body (201) is made of rubber.

3. A tool for removing a closed rubber cap on an aircraft skin as defined in claim 1, wherein: The outer shell (202) has a through hole in the middle that is adapted to the outer core rod (301).

4. A tool for removing a closed rubber cap on an aircraft skin as defined in claim 1, wherein: The connection between the support rod (302) and the outer core rod (301) is a hinge.

5. A tool for removing a closed rubber cap on an aircraft skin as defined in claim 1, wherein: One end of the inner core rod (402) is fixedly connected to the support umbrella (303).

6. A tool for removing a closed rubber cap on an aircraft skin as defined in claim 1, wherein: The inner core rod (402) is externally provided with a self-locking nut (403), and the connection between the self-locking nut (403) and the inner core rod (402) is a threaded connection.

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