Auxiliary tool for disassembling and assembling plug pin of airplane hatch cover

Abstract

The invention relates to a bolt on a hatch cover hinge convenient to disassemble and assemble. The bolt is used when a certain type of airplane hatch cover is disassembled and assembled. The invention discloses an auxiliary tool for disassembling and assembling a bolt of an airplane hatch cover. The auxiliary tool comprises a guide pin and an auxiliary device for disassembling and assembling, the guide pin is T-shaped, is used for replacing the installation plug pin and comprises an end face and a guide pin shaft, the outer diameter of the guide pin shaft is matched with the inner diameter of the plug pin through hole, and the end, away from the end face, of the guide pin shaft is in conical transition; the dismounting auxiliary device comprises a bolt mounting part and a bolt dismounting part which are arranged left and right, the bolt mounting part is used for auxiliary mounting of the bolt, the bolt dismounting part is used for dismounting of the bolt and comprises a dismounting bolt fixing groove, the inner diameter of the dismounting bolt fixing groove is matched with the outer diameter of the guide pin shaft and the outer diameter of the mounting bolt, and a notch of the dismounting bolt fixing groove is located at the end of the dismounting auxiliary device. The hatch cover dismounting device has the following advantages that operation which is prone to injuring personnel and structures becomes safe and reliable, and the hatch cover dismounting efficiency is improved.

Description

Technical Field

[0001] The invention relates to a latch pin used for disassembling and assembling a cabin cover of a certain type of aircraft and convenient for disassembling and assembling a cabin cover hinge. Background Art

[0002] The hatch hinge of a certain type of aircraft is half-embedded inside the structure. There are no special tools for disassembling and installing the latch. The latch needs to be held by hand during installation. Affected by the aircraft structure, the end face of the latch is about half covered by the structure. When using a tool to hit the half-exposed end face of the latch into the aircraft structure, the hitting tool cannot exert vertical force on the end face of the latch. At the same time, the installation latch part is a flat end. During installation, the latch with a flat end face is not easy to insert due to the eccentricity between the hatch and the structural hole. This makes installation difficult and easily injures the aircraft structure and the installer's hands. Summary of the invention

[0003] The purpose of the present invention is to provide an aircraft cabin cover latch disassembly and assembly auxiliary tool, which simplifies the disassembly and assembly of the cabin cover hinge latch of a certain type of aircraft and improves safety and quality.

[0004] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an aircraft cabin cover latch disassembly and assembly auxiliary tool, the disassembly and assembly auxiliary tool includes a guide pin and a disassembly and assembly auxiliary device; the guide pin is T-shaped and is used to replace the installation latch, and it includes an end face and a guide pin shaft, the outer diameter of the guide pin shaft is adapted to the inner diameter of the latch through hole, and its end away from the end face has a conical transition; the disassembly and assembly auxiliary device includes an installation latch part and a removal latch part arranged on the left and right, the installation latch part is used for auxiliary installation of the latch, and the removal latch part is used for removal of the latch, and it includes a removal latch fixing groove, the inner diameter of the removal latch fixing groove is adapted to the outer diameter of the guide pin shaft and the outer diameter of the installation latch, and its notch is located at the end of the disassembly and assembly auxiliary device.

[0005] Preferably, the connecting portion between the installation latch portion and the removal latch portion is a hand-held portion.

[0006] Preferably, the mounting pin portion includes a mounting pin striking surface and an end face positioning groove; the mounting pin striking surface and the end face positioning groove are alternately arranged on opposite sides of the mounting pin portion, the mounting pin striking surface is a boss extending radially outward along the mounting pin portion, the end face positioning groove is close to the end of the mounting pin portion, its depth is not greater than the end face height of the guide pin and the installation pin, and its radial dimension is not less than the end face outer diameter of the guide pin and the installation pin.

[0007] Preferably, the end surface positioning groove is a groove extending radially inward along the installation pin portion.

[0008] Preferably, the disassembly latch portion further includes a disassembly latch striking surface, and the disassembly latch striking surface is a boss extending radially outwardly along the disassembly latch portion.

[0009] Preferably, one side of the disassembly pin fixing groove near the notch is a sloped transition, and the other side is a flat surface.

[0010] Compared with the prior art, the present invention has the following advantages: operations that are likely to cause damage to personnel and structures are made safe and reliable, and the efficiency of disassembly and assembly of the hatch cover is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a schematic diagram of the structure of an embodiment of the present invention; Figure 2 yes Figure 1 Bottom view of the (excluding process guide pins); Figure 3 is a schematic diagram of the structure of the installation latch used in the embodiment of the present invention; Figure 1-2 1. Install the strike surface of the bolt; 2. Hand-held part; 3. Guide pin cap fixing groove; 4. Remove the strike surface of the bolt; 5. Remove the bolt fixing groove; 6. Process guide pin; Figure 3 7. Installation latch. DETAILED DESCRIPTION

[0012] It should be noted that the terms “left”, “right”, “upper”, “lower”, etc. are described according to the drawings and do not constitute limitations to the present invention.

[0013] The following is combined with Figure 1-3 The present invention is further described in detail: an auxiliary tool for disassembling and assembling a latch of an aircraft canopy, comprising two parts: a process guide pin 6 and a disassembling and assembling auxiliary device; the guide pin is made into a tapered transition at the front section according to the size of the assembly part, which is easy to install; the two ends of the disassembling and assembling auxiliary device are made for both installation and disassembly according to the requirements of the disassembly and assembly work; the installation end is made into a groove with a certain depth according to the size of the latch end face, which is used to fix the process guide pin 6 and the end face of the assembly latch 7, and at the same time, a boss is extended to the outside of the aircraft structure as the installation latch striking surface 1. During installation, the force is transmitted to the end face of the assembly latch 7 by hitting the boss according to the principle of force conduction, and the assembly latch 7 is guided into the aircraft installation position. The disassembling end face is a fork-shaped face, and the fork-shaped mouth (disassembling latch fixing groove 5) is made according to the diameter of the process guide pin 6. During disassembly, a part of the process guide pin 6 is first knocked out with an auxiliary tool, and then the fork-shaped part is inserted into the gap between the process guide pin 6 and the structure, and the disassembling end boss (disassembling latch striking surface 4) extending out of the structure is hit to take out the process guide pin 6.

[0014] As a preferred implementation manner of this embodiment, the boss heights of the installation pin striking surface 1 and the removal pin striking surface 4 are both higher than the radial dimension of the hand-holding part 2 .

[0015] As a preferred implementation mode of this embodiment, the depth of the guide pin cap fixing groove 3 is not greater than the end face height of the process guide pin 6 and the installation plug pin 7, and its radial dimension is not less than the end face outer diameter of the process guide pin 6 and the installation plug pin 7.

[0016] As a preferred implementation scheme of this embodiment, the installation pin striking surface 1 and the guide pin cap fixing groove 3 are respectively located on both sides of the radial direction of the disassembly and assembly auxiliary device, and are staggered, that is, the guide pin cap fixing groove 3 is close to the left end of the disassembly and assembly auxiliary device, and the installation pin striking surface 1 is close to the hand-holding part 2; the disassembly pin fixing groove 5 is located at the right end of the disassembly and assembly auxiliary device, and its notch is located at the right end of the disassembly and assembly auxiliary device, and the disassembly pin striking surface 4 is close to the hand-holding part 2, and on the same side as the sloped transition end face of the disassembly pin fixing groove 5.

[0017] The specific usage process is as follows: When installing the installation latch 7, first use the process guide pin 6 in the disassembly and assembly tool to replace the installation latch 7 and insert it into the installation hole, grasp the hand-held part 2 of the disassembly and assembly auxiliary tool, insert the guide pin cap fixing groove 3 at the installation end of the disassembly and assembly auxiliary tool into the end face of the process guide pin 6, and hit the installation latch striking surface 1 extending from the aircraft structure with a hammer, which can effectively install the process guide pin 6 in place. After installing two process guide pins 6 in the same way, the latch through holes of the aircraft cabin cover and the structure are basically aligned, and the remaining latch through holes are directly installed with the installation latch 7. After the installation is completed, the two process guide pins 6 are removed and replaced with the installation latch 7; During disassembly, first use the flat end of the disassembly pin fixing groove 5 at the other end of the disassembly and assembly auxiliary tool to knock the protruding part of the installation pin 7 until it is flush with the structure, then insert the disassembly pin fixing groove 5 of the disassembly and assembly auxiliary tool into the gap between the pin and the structure, and use a hammer to hit the disassembly pin striking surface 4 of the disassembly and assembly auxiliary tool extending out of the aircraft structure to push the installation pin 7 out of the installation position.

[0018] The above embodiments are only preferred implementations of the present invention and do not constitute a limitation of the present invention. Any extension, deformation, equivalent substitution, etc. made by ordinary technicians in this field without departing from the principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An auxiliary tool for disassembling and assembling a latch of an aircraft cabin cover, characterized in that: The disassembly and assembly auxiliary tool includes a guide pin and a disassembly and assembly auxiliary device; the guide pin is T-shaped and is used to replace the installation pin; the disassembly and assembly auxiliary device includes an installation pin part and a removal pin part arranged on the left and right, the installation pin part is used for auxiliary installation of the pin, and the removal pin part is used for removal of the pin, which includes a removal pin fixing groove, the inner diameter of the removal pin fixing groove is adapted to the outer diameter of the guide pin shaft and the outer diameter of the installation pin, and the groove is located at the end of the disassembly and assembly auxiliary device.

2. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 1, characterized in that: The connection portion between the installation latch portion and the removal latch portion is a hand-held portion.

3. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 1, characterized in that: The mounting pin portion includes a mounting pin striking surface and an end face positioning groove; the mounting pin striking surface and the end face positioning groove are staggered and arranged on opposite sides of the mounting pin portion, and the end face positioning groove is close to the end of the mounting pin portion, and its depth is not greater than the end face height of the guide pin and the installation pin, and its radial dimension is not less than the end face outer diameter of the guide pin and the installation pin.

4. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 3, characterized in that: The mounting pin striking surface is a boss extending radially outwardly along the mounting pin portion.

5. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 1, characterized in that: The end surface positioning groove is a groove extending radially inwardly along the installation latch portion.

6. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 1, characterized in that: The disassembly latch portion further comprises a disassembly latch striking surface, which is a boss extending radially outwardly along the disassembly latch portion.

7. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 1 or 6, characterized in that: One side of the disassembly pin fixing groove near the notch is sloped, and the other side is flat.

8. The aircraft cabin cover latch disassembly and assembly auxiliary tool according to claim 1, characterized in that: The guide pin comprises an end face and a guide pin shaft, the outer diameter of the guide pin shaft is matched with the inner diameter of the plug through hole, and the end portion thereof away from the end face is in a conical transition.

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