A device for removing the overflow hole flange of a fighter aircraft structure

Abstract

A device for disassembling a flange plate of a fighter aircraft structure overflow hole belongs to the field of aviation equipment technology. The device for disassembling a flange plate of a fighter aircraft structure overflow hole includes a cover plate, a blade, an intermediate rod, a structural support, a fixing plate, and a spring; wherein the cover plate is mounted on the structural support by screws; the cover presses the blade spring so that the blade can move forward and backward along the track on the structural support; the intermediate rod is screwed into the structural support through a thread, and is driven by a pneumatic trigger to push the blade to extend outward. Compared with the existing violent disassembly method of changing the knife, this device ensures precision and no marks during the disassembly process, ensuring that the body structure does not cause damage, cracks, or excess materials during the disassembly process; compared with the original manual hammering and changing the knife, this device can be directly driven by a pneumatic trigger, which is simple and fast, and improves production efficiency.

Description

Technical Field

[0001] During a fighter aircraft overhaul, a flange was disassembled for repair and replacement. During the disassembly process, the aircraft was violently disassembled at an angle using tools such as a knife, hammer, and flat spatula. This caused scratches and nicks on the aircraft structure and generated a large amount of excess metal shavings. This resulted in deviations from key technical indicators such as structural strength, rigidity, and fuel tank cleanliness, making it difficult to ensure the quality of the aircraft repair.

[0002] The present invention develops a flange disassembly device based on the external dimensions of the overflow hole in the fuselage. By screwing a hexagonal nut and pushing multi-angle blades to squeeze simultaneously, the flange can be efficiently and safely disassembled without damaging the fuselage structure, thereby improving the quality of structural repair. This invention belongs to the field of aviation equipment technology. Background Art

[0003] In order to ensure sufficient structural strength and sufficient fuel carrying capacity, a certain type of fuel tank on a certain fighter aircraft is separated by several bulkheads. Overflow holes are designed on each bulkhead to ensure fuel flow, and a certain type of sealant is used to apply to the fuselage structure to ensure fuel sealing.

[0004] The overflow hole and flange of a certain fighter aircraft are connected by bolts and then coated with sealant to form the internal fuel channel support structure of the fuel tank. The flange is tightly integrated with the body structure and is difficult to disassemble. Figure 8 .

[0005] During repairs on this type of aircraft, the flange must be removed and replaced. Currently, there are no effective disassembly methods available, requiring the use of tools such as knives, hammers, and flat shovels, often performed at oblique angles. This can lead to scratches and nicks on the aircraft structure, and the generation of large amounts of excess metal shavings. This can cause deviations in key technical indicators such as structural strength, rigidity, and fuel tank cleanliness, making it difficult to guarantee aircraft repair quality. Summary of the Invention

[0006] The present invention develops a special overflow hole flange disassembly device, which ensures accuracy and convenience during the disassembly process and ensures that the machine body structure is not damaged, cracked or has no excess materials during the disassembly process.

[0007] The purpose of the present invention is achieved by the following technical solutions:

[0008] A device for removing a flange plate of an overflow hole of a fighter aircraft structure, comprising a cover plate 1, a blade 2, an intermediate rod 3, a structural support 4, a fixing plate 5, and a spring 6;

[0009] The cover plate 1 has a central opening and is mounted on the structural support 4 by screws 7 on all sides; the cover plate 1 can cover and press the blade 2 and the spring 6;

[0010] The bevel of the head of the blade 2 facilitates insertion into the gap between the flange and the body structure. Stoppers are provided on both sides of the middle of the blade 2, and the root of the blade 2 is a curved surface.

[0011] The middle rod 3 is composed of a frustum, a thick cylinder, a thin cylinder and a hexagonal head from the head to the root; the side of the frustum contacts the root curved surface of the blade 2, the frustum and the thick cylinder are located in the thick groove of the structural support 4, and the thick cylinder and the structural support 4 are loosely matched; the thin cylinder is provided with an external thread, which cooperates with the internal thread on the fine groove of the structural support 4.

[0012] The axial direction of the structural support 4 passes through the coarse slot and the fine slot in sequence; the outer dimensions of the structural support 4 are adapted to the overflow hole dimensions and can fit the body structure; a cross-shaped groove is provided on the head end face of the structural support 4, and a spring 6 is placed between the cross-shaped end and the stop block of the blade. The elastic force of the spring 6 ensures that the blade 2 is recovered in time during the retraction of the intermediate rod 3.

[0013] The fixing plate 5 is fixed to the bolt holes around the overflow hole of the body structure by bolts and nuts, and is used to limit the displacement of the structural support 4 and ensure the stability of its forward and backward movement.

[0014] A method for using a fighter aircraft structure overflow hole flange disassembly device:

[0015] 1. Fix the fixing plate 5 to the bolt holes around the overflow hole of the machine body with bolts and nuts;

[0016] 2. Insert the main structure consisting of the cover plate 1, blade 2, intermediate rod 3, and structural support 4 into the fixing plate 5, and slide it back and forth until the blade 2 is aligned with the gap between the flange and the main structure;

[0017] 3. Connect the pneumatic trigger to the hexagonal head at the end of the middle rod 3, hold the structural support 4, open the pneumatic trigger clockwise to drive the middle rod 3 to rotate, and squeeze the flange to fall off;

[0018] 4 After the flange is disassembled, the device can be disassembled in the reverse order of the above steps and stored properly.

[0019] The beneficial effects of the present invention are as follows: the overflow hole flange disassembly device of the present invention positions the device at the center of the overflow hole during the disassembly process, ensuring that the device does not move forward or backward during the entire disassembly process, ensuring its external dimensions, and accurately disassembling the flange. Compared with the existing violent disassembly method using a knife, this device ensures precision and no marks during the disassembly process, ensuring that the body structure is not damaged, cracked, or has excess materials during the disassembly process; compared with the original manual hammering and knife changing method, this device can be directly driven by a pneumatic trigger, which is simple and fast, and improves production efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] FIG1( a ) is a schematic diagram of the external structure of the device of the present invention.

[0021] FIG1( b ) is a cross-sectional view taken along line AA of FIG1( a ).

[0022] FIG1(c) is a left view of FIG1(a).

[0023] Figure 2 Schematic diagram of the cover plate, where (a) is the main view, (b) is the AA cross-sectional view, and (c) is the BB cross-sectional view.

[0024] Figure 3 Schematic diagram of the blade, where (a) is a side view, (b) is a top view, and (c) is a main view.

[0025] Figure 4 Schematic diagram of the middle rod, where (a) is the right view, (b) is the main view, and (c) is the left view;

[0026] Figure 5 Schematic diagram of the structural support, where (a) is the internal schematic diagram, (b) is the left view, (c) is the AA section view, and (d) is the main view.

[0027] Figure 6 Schematic diagram of the fixing plate, where (a) is the main view and (b) is the side view.

[0028] Figure 7 Implementation diagram.

[0029] Figure 8 Overflow hole and flange of a certain type of fighter aircraft fuel tank.

[0030] In the figure: 1 cover plate, 2 blade, 3 middle rod, 4 structural support, 5 fixing plate, 6 spring, 7 screw. DETAILED DESCRIPTION

[0031] Below is a detailed explanation of the following with reference to the accompanying drawings and specific implementation diagrams ( Figure 7 ) to describe the present invention in detail, but not limited thereto.

[0032] like Figure 1(a) to Figure 1(c) As shown in the figure, there is a cover plate 1, four blades 2, an intermediate rod 3, a structural support 4, a fixing plate 5, eight φ5*φ1*L10 springs 6, and four GBT 70.1M4×20 screws 7.

[0033] like Figure 2 As shown, the top of the cover plate 1 is provided with four φ4.2 bolt holes, which can be connected and fixed to the structural support 4 through GBT 70.1M4×20; the middle is provided with a φ30 round hole, which cooperates with the middle rod 3 to move up and down; the guide angles around it are 1×45°, so that the device does not damage the body when passing through the overflow hole of the body structure.

[0034] like Figure 3 As shown, the blade 2 has a 38° bevel angle to facilitate insertion into the gap between the flange and the body structure; the root is an R5 curved surface, which is convenient for fitting with the round table surface of the middle rod 3 to achieve a pushing effect; the two sides are small cube block structures and structural supports 4 to limit the blade displacement trajectory and transmit the φ5*φ1*L10 spring force to the blade as a whole to achieve controllable advance and retreat.

[0035] like Figure 4 As shown, the head of the intermediate rod 3 is designed as a 67° frustum, which cooperates with the structural support 4 during the rotation and propulsion process to push out the blade 2; the middle is an M18×1.5 thread, which cooperates with the internal thread in the structural support 4 to realize the up and down movement of the intermediate rod 3; the root is a hexagonal head, which can cooperate with the pneumatic trigger to provide rotational power;

[0036] like Figure 5 As shown, the structural support 4 can be threadedly matched with the intermediate rod 3 to achieve its fixation and control its movement trajectory; the 4×M4 bolt holes on the upper surface ensure a tight connection with the cover plate 1, pressing the 4 blades 2 and 8 φ5*φ1*L10 springs 6 to limit their displacement; the outer surface has a chamfer angle of 1×45° to ensure that it does not damage the body structure when entering the overflow hole.

[0037] like Figure 6 As shown, the fixing plate 5 is fixed to the body structure by bolts to limit the displacement of the structural support 4 and ensure the stability of its forward and backward movement.

[0038] The cover plate 1 is installed on the structural support 4 by means of GBT 70.1M4×20 screws 7; the cover presses the blade 2 and the φ5*φ1*L10 spring 6, so that the blade 2 can move back and forth along the track on the structural support 4; the intermediate rod 3 is screwed into the structural support 4 through a thread and driven by a pneumatic trigger to push the blade 2 to extend outward.

[0039] When in use, screw the screw of the middle rod 3 into the thread of the structural support 4 until the bottom surface of the thick cylinder fits the inner surface of the structural support 4; place the four blades 2 in the cross-shaped grooves on the upper surface of the structural support 4 respectively, ensuring that the large surface of the blade fits tightly on the structural support 4, and the square stopper of the blade 2 is in the slide rail; compress 8 φ5*φ1*L10 springs 6 and place them between the square stopper of the blade 2 and the end of the cross-shaped groove of the structural support, immediately press the cover plate 1 onto the upper surface of the structural support 4, and fix it with 4 GBT 70.1M4×20 screws. Insert the main structure (comprising the cover plate 1, blade 2, intermediate rod 3, structural support 4, φ5*φ1*L10 spring 6, and GBT 70.1M4×20 screw 7) into the fixing plate 5. Slide the blade 2 back and forth until the tip aligns with the gap between the flange and the main structure. Attach the pneumatic trigger to the hexagonal head at the end of intermediate rod 3. Holding structural support 4, turn the pneumatic trigger clockwise to rotate intermediate rod 3, squeezing the flange to release.

[0040] Use this device to dismantle the overflow flange to prevent damage to the machine body and excess materials during the flange removal process;

[0041] The middle rod 3 of the device uses a chamfer to cooperate with the hemispherical surface at the root of the blade 2, squeezing and pushing the blade to move, achieving efficient transmission between vertical displacements;

[0042] The spring is placed between the blade 2 and the structural support 4, and its elastic force ensures that the blade 2 is retracted in time during the retraction of the intermediate rod 3;

[0043] The outer dimensions of the structural support 4 are adapted to the dimensions of the overflow hole and can fit in with the machine body structure. The blade 2 can be adjusted in telescopic length to ensure the shape and size requirements;

[0044] The fixing plate 5 is designed to match the bolt holes in different positions to ensure coordination with the bolt holes on the outer ring of the overflow hole. In the case of different aircraft sizes, the positioning shape and size requirements can still be met.

[0045] The root of the middle rod 3 adopts a hexagonal head shape, which can be used with the pneumatic trigger, saving time and effort;

[0046] The place where the structural support 4 cooperates with the spring is designed as a semi-cylindrical groove to prevent the blade 2 from getting stuck due to the radius increasing when the spring is compressed and deformed;

[0047] The outer shape of the blade 2 is designed to be a small cube, which ensures that the width is transitionally matched with the structural support 4, while ensuring that the spring force is effectively transmitted to the blade 2 in a positive direction, ensuring that it can be freely retracted and extended along a predetermined trajectory.

Claims

1. A device for disassembling an overflow flange, characterized in that: The overflow hole flange disassembly device comprises a cover plate (1), a blade (2), an intermediate rod (3), a structural support (4), a fixing plate (5) and a spring (6); The cover plate (1) has a central opening and is mounted on the structural support (4) via screws (7) on all sides; the cover plate (1) can cover and press the blade (2) and the spring (6); The bevel of the head of the blade (2) facilitates insertion into the gap between the flange and the body structure, stops are provided on both sides of the middle of the blade (2), and the root of the blade (2) is a curved surface; The middle rod (3) is composed of a frustum, a thick cylinder, a thin cylinder and a hexagonal head from the head to the root; the side surface of the frustum contacts the root curved surface of the blade (2); the frustum and the thick cylinder are located in the thick notch of the structural support (4); the thick cylinder and the structural support (4) are clearance-matched; the thin cylinder is provided with an external thread, which matches the internal thread on the thin notch of the structural support (4); The axial direction of the structural support (4) sequentially passes through the coarse slot and the fine slot; The external dimensions of the structural support (4) are compatible with the dimensions of the overflow hole and can fit in with the machine body structure; A cross-shaped groove is provided on the head end face of the structural support (4), and a spring (6) is placed between the cross-shaped end and the stopper of the blade. The elastic force of the spring (6) ensures that the blade (2) is recovered in time during the retreat of the intermediate rod (3); The fixing plate (5) is fixed to the bolt holes around the overflow hole of the machine body structure by means of bolts and nuts, and is used to limit the displacement of the structural support (4) and ensure the stability of its forward and backward movement.

2. The overflow flange disassembly device according to claim 1, characterized in that: The middle rod (3) uses a chamfer to cooperate with the hemispherical surface at the root of the blade (2), squeezing and pushing the blade (2) to move, thereby achieving efficient transmission between vertical displacements.

3. The overflow flange disassembly device according to claim 1, characterized in that: The fixing plate (5) is designed to match the bolt holes at different positions to ensure coordination with the bolt holes on the outer ring of the overflow hole, and to ensure the positioning shape and size requirements under the conditions of different aircraft with different sizes.

4. The overflow flange disassembly device according to claim 1, characterized in that: The portion where the structural support (4) and the spring (6) cooperate is designed to be a semi-cylindrical groove type, so as to prevent the blade (2) from being stuck due to the radius increasing when the spring (6) is compressed and deformed.

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