Aircraft assembly riveting tool

Abstract

The utility model provides an aircraft assembly riveting tool, which relates to the technical field of riveting tools and comprises a clamp body. The clamp body is provided with a clamping bearing rod in the front-back direction, the whole clamping bearing rod is of an L-shaped rod structure, a reinforcing rib is arranged at the bent position of the clamping bearing rod, and an inner threaded cylinder in the front-back direction is arranged at the left end of a left-right direction rod of the clamping bearing rod. Six insertion blind holes arranged in the front-back direction are formed in the right side of the outer circumference of the clamping bearing rod front-back direction rod, the clamping bearing rod front-back direction rod is sleeved with an adjustable bearing rod in the left-right direction, the adjustable bearing rod is conveniently installed on the clamping bearing rod through a limiting locking column, and the adjustable bearing rod can conveniently move and adjust on the clamping bearing rod front and back.

Description

TECHNICAL FIELD

[0001] The utility model belongs to riveting tool technical field especially relates to a kind of aircraft assembly riveting tools. BACKGROUND

[0002] Aircraft assembly riveting tool refers to special tool used for connecting aircraft components during aircraft assembly, which mainly includes riveting gun, rivet and corresponding auxiliary tools, wherein auxiliary tools include various fixtures and positioning pins, etc., for accurately aligning and fixing workpiece during riveting process, to ensure the quality and accuracy of riveting, and to improve assembly efficiency and accuracy.

[0003] Based on the above, the present inventor found that the existing aircraft assembly riveting fixture has the following disadvantages:

[0004] 1. The maximum opening size of the clamping position is fixed, and cannot be adjusted according to the size of the aircraft assembly parts, which is not convenient to add connection measures on the fixture to adjust the maximum opening size of the clamping position.

[0005] 2. The clamping rod is rotating and moving, and when contacting with the aircraft assembly parts, it is easy to scratch due to rotation, and it is not convenient to add rotation stopping measures on the fixture to make the clamping rod only move and contact with the aircraft assembly parts. INVENTION CONTENTS

[0006] To at least partially solve the above technical problems, the utility model provides an aircraft assembly riveting tool.

[0007] The purpose and effect of the aircraft assembly riveting tool of the utility model are achieved by the following specific technical means:

[0008] An aircraft assembly riveting tool includes a fixture body; the fixture body is provided with a clamping bearing rod in front-rear direction, the clamping bearing rod is overall L-shaped rod structure, the clamping bearing rod is provided with reinforcing ribs at bending position, the clamping bearing rod is provided with internal thread cylinder in front-rear direction at left end in left-right direction, the clamping bearing rod is provided with six insertion blind holes arranged in front-rear direction at right side of outer circumference of front-rear direction rod, the clamping bearing rod is provided with adjustable bearing rod in left-right direction on sleeve, the adjustable bearing rod is provided with sleeve in front-rear direction at right end, the sleeve of the adjustable bearing rod is provided with thread hole penetrating left-right direction at right side wall, the adjustable bearing rod is provided with bearing cylinder in front-rear direction at left end, the bearing cylinder of the adjustable bearing rod is provided with bearing ring groove at inner circumference in front, the bearing cylinder of the adjustable bearing rod is provided with rotation-stopping screw hole penetrating left-right direction at left side wall in rear, the thread hole of the adjustable bearing rod is provided with limiting locking column in left-right direction inside, the limiting locking column is provided with thread at outer circumference, and the right end face of the limiting locking column is provided with regular hexagon groove.

[0009] Further, the rear end surface of the clamping moving rod is provided with a circular plate, a circular groove is formed in the rear end surface of the circular plate of the clamping moving rod, and a rubber protection pad is mounted in the circular groove of the clamping moving rod.

[0010] Further, the clamping rotating cylinder is internally provided with a front-to-back clamping moving rod through screwing, a thread is formed in the outer circumference of the clamping moving rod, and a front-to-back strip-shaped groove is formed in the left side of the outer circumference of the clamping moving rod.

[0011] Further, a bearing ring groove is formed in the outer circumference of the rear end of the clamping rotating cylinder, and a regular hexagonal structure is arranged on the front side of the clamping rotating cylinder.

[0012] Further, the bearing ring groove of the adjustable bearing rod is internally provided with a front-to-back clamping rotating cylinder through a bearing, and a thread is formed in the inner circumference of the clamping rotating cylinder.

[0013] Further, the inner screw hole of the clamping bearing rod is internally provided with a left-to-right fixed rotation-stopping column, a threaded column is arranged on the right side of the fixed rotation-stopping column, a limiting ring plate is arranged on the outer circumference of the left end of the threaded column of the fixed rotation-stopping column, and a regular hexagonal prism is arranged on the left end surface of the threaded column of the fixed rotation-stopping column.

[0014] Further, the inner screw hole of the clamping bearing rod is internally provided with a front-to-back clamping contact block, a threaded column is arranged on the rear end of the clamping contact block, a regular hexagonal prism is arranged on the front end surface of the threaded column of the clamping contact block, a circular plate is arranged on the front end surface of the regular hexagonal prism of the clamping contact block, a circular groove is formed in the front end surface of the circular plate of the clamping contact block, and a rubber protection pad is mounted in the circular groove of the clamping contact block.

[0015] Compared with the prior art, the utility model has the advantages of the following:

[0016] The adjustable bearing rod is conveniently installed on the clamping bearing rod through the limiting locking column, the adjustable bearing rod is conveniently adjusted in the front-to-back direction on the clamping bearing rod, the maximum opening size of the clamping position is fixed, the clamping position cannot be adjusted according to the size of the aircraft assembly part, it is inconvenient to add a connecting measure on the clamp to enable the maximum opening size of the clamping position to be adjusted.

[0017] The fixed rotation-stopping column is conveniently installed on the adjustable bearing rod to stop the rotation of the clamping moving rod, the clamping moving rod can only be moved through thread engagement, the clamping rod is rotatably moved, the clamping rod is easily scratched when contacting the aircraft assembly part, it is inconvenient to add a rotation-stopping measure on the clamp to enable the clamping rod to only move and contact the aircraft assembly part. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is a front view structural schematic diagram of the utility model.

[0019] Figure 2 is the rear view structure schematic diagram of the utility model.

[0020] Figure 3 is the section structure schematic diagram of the utility model.

[0021] Figure 4 is the disassembly structure schematic diagram of the utility model.

[0022] Figure 5 is the assembly schematic diagram of adjustable bearing rod and fixed rotation-stopping column of the utility model.

[0023] Figure 6 is the assembly schematic diagram of clamping bearing rod and adjustable bearing rod of the utility model.

[0024] In the figure: 1, clamp body;2, clamping bearing rod;3, adjustable bearing rod;4, limit locking column;5, clamping contact block;6, fixed rotation-stopping column;7, clamping rotary cylinder;8, clamping moving rod. DETAILED DESCRIPTION

[0025] The embodiment of the present application is described in further detail below in combination with the drawings and examples.

[0026] Example one:

[0027] As Figures 1 to 6 shown:

[0028] The aircraft assembly riveting tool provided by the embodiment comprises a clamp body 1; the clamp body 1 is provided with a clamping bearing rod 2 in the front-rear direction, facilitating bearing of various components; the clamping bearing rod 2 is in an overall L-shaped rod structure, facilitating bearing stress; the clamping bearing rod 2 is provided with a reinforcing rib at the bending position, facilitating increase of stress capacity; the left end of the clamping bearing rod 2 in the left-right direction is provided with an inner threaded cylinder in the front-rear direction, facilitating threaded installation of a clamping contact block 5; the outer circumference of the clamping bearing rod 2 in the front-rear direction is provided with six front-rear arranged insertion blind holes on the right side, facilitating insertion of a limiting locking column 4 into the inside; the clamping bearing rod 2 in the front-rear direction is sleeved with an adjustable bearing rod 3 in the left-right direction, facilitating front-rear movement of the adjustable bearing rod 3; the adjustable bearing rod 3 is provided with a sleeve in the front-rear direction at the right end, facilitating insertion of the clamping bearing rod 2 into the inside; a left-right penetrating threaded hole is formed in the right side wall of the sleeve of the adjustable bearing rod 3, facilitating threaded installation of the limiting locking column 4; the adjustable bearing rod 3 is provided with a bearing cylinder in the front-rear direction at the left end, facilitating insertion of a clamping moving rod 8 into the inside; a bearing ring groove is formed in the front inside circumference of the bearing cylinder of the adjustable bearing rod 3, facilitating bearing installation of a clamping rotating cylinder 7; a left-right penetrating rotation stopping screw hole is formed in the left side wall of the rear of the bearing cylinder of the adjustable bearing rod 3, facilitating threaded installation of a fixed rotation stopping column 6; the threaded hole of the adjustable bearing rod 3 is internally installed with a limiting locking column 4 in the left-right direction, facilitating anti-disengagement of the adjustable bearing rod 3; a thread is formed in the outer circumference of the limiting locking column 4, facilitating threaded installation; a regular hexagonal groove is formed in the right end face of the limiting locking column 4, facilitating rotation disassembly by a tool.

[0029] The inner threaded cylinder of the clamping bearing rod 2 is internally provided with a front and rear direction clamping contact block 5, which is convenient for clamping the aircraft assembly parts in cooperation with the clamping moving rod 8, the rear end of the clamping contact block 5 is provided with a threaded column, which is convenient for the clamping contact block 5 to be installed through threads, the front end surface of the threaded column of the clamping contact block 5 is provided with a regular hexagonal prism, which is convenient for the clamping contact block 5 to be disassembled and assembled through tools, the front end surface of the regular hexagonal prism of the clamping contact block 5 is provided with a circular plate, which is convenient for clamping stress, the front end surface of the circular plate of the clamping contact block 5 is provided with a circular groove, which is convenient for the rubber protective pad to be installed, the circular groove of the clamping contact block 5 is internally provided with a rubber protective pad, which is convenient for contacting the aircraft assembly parts, the rotation stopping screw hole of the adjustable bearing rod 3 is internally provided with a left and right direction fixed rotation stopping column 6, which is convenient for the clamping moving rod 8 to be rotationally stopped, the right side of the fixed rotation stopping column 6 is provided with a threaded column, which is convenient for being installed through threads, the left end surface of the threaded column of the fixed rotation stopping column 6 is provided with a regular hexagonal prism, which is convenient for being disassembled and assembled through tools, the bearing ring groove of the adjustable bearing rod 3 is internally provided with a front and rear direction clamping rotating cylinder 7 through a bearing, which is convenient for the clamping rotating cylinder 7 to be rotationally driven through the bearing, the internal circumference of the clamping rotating cylinder 7 is provided with threads, which is convenient for the clamping moving rod 8 to be installed through threads, the rear end external circumference of the clamping rotating cylinder 7 is provided with a bearing ring groove, which is convenient for the clamping rotating cylinder 7 to be installed through the bearing, the front end external circumference of the clamping rotating cylinder 7 is provided with a regular hexagonal structure, which is convenient for being rotated through tools, the clamping moving rod 8 is internally provided with a front and rear direction clamping moving rod 8 through threads, which is convenient for the clamping moving rod 8 to be moved forward and backward through thread engagement, the external circumference of the clamping moving rod 8 is provided with threads, which is convenient for the clamping rotating cylinder 7 to be installed through threads, the left side of the external circumference of the clamping moving rod 8 is provided with a front and rear direction strip-shaped groove, which is convenient for the fixed rotation stopping column 6 to be inserted to rotationally stop the clamping moving rod 8, the rear end surface of the clamping moving rod 8 is provided with a circular plate, which is convenient for clamping stress, the rear end surface of the circular plate of the clamping moving rod 8 is provided with a circular groove, which is convenient for the rubber protective pad to be installed, the circular groove of the clamping moving rod 8 is internally provided with a rubber protective pad, which is convenient for contacting the aircraft assembly parts.

[0030] The specific use mode and effect of the embodiment are as follows:

[0031] In the utility model, Figure 1As shown, the clamp body 1 is in use, at which time the aircraft assembly parts are clamped between the clamping contact block 5 and the clamping moving rod 8, and the aircraft assembly parts are in the intercepted state. When the clamp body 1 is detached from the aircraft assembly parts, the clamping rotating cylinder 7 is rotated by a tool to threadedly engage the clamping moving rod 8, so that the clamping moving rod 8 moves forward by thread engagement, thereby releasing the clamping of the aircraft assembly parts by the clamping contact block 5 and the clamping moving rod 8, and then the clamp body 1 is detached from the aircraft assembly parts, wherein the clamping moving rod 8 is rotated by the fixed rotation stopping column 6 when moving, so that the clamping moving rod 8 can only move and cannot rotate. When the position of the adjustable bearing rod 3 is adjusted, the limiting locking column 4 is rotated by a tool to threadedly engage the adjustable bearing rod 3, so that the limiting locking column 4 moves to the right by thread engagement to be detached from the insertion blind hole of the clamping bearing rod 2, thereby releasing the locking of the adjustable bearing rod 3 by the limiting locking column 4, and moving the adjustable bearing rod 3 forward or backward for adjustment. After the adjustable bearing rod 3 is adjusted, the limiting locking column 4 is rotated by a tool to threadedly engage the adjustable bearing rod 3, so that the limiting locking column 4 moves to the left by thread engagement to be inserted into the insertion blind hole of the clamping bearing rod 2, thereby achieving the locking of the adjustable bearing rod 3 by the limiting locking column 4.

[0032] Example Two:

[0033] The difference from Example One is that the regular hexagonal prism of the clamping contact block 5 can also be set as a regular heptagonal prism, thereby making the clamping contact block 5 need to be rotated by a special tool matched with the regular heptagonal prism, preventing non-workers from rotating and detaching the clamping contact block 5.

[0034] Example Three:

[0035] The difference from Example One is that the regular hexagonal prism of the fixed rotation stopping column 6 can also be set as a regular heptagonal prism, thereby making the fixed rotation stopping column 6 need to be rotated by a special tool matched with the regular heptagonal prism, preventing non-workers from rotating and detaching the fixed rotation stopping column 6.

Claims

1. An aircraft assembly riveting tool characterized by: The utility model provides a kind of clamp, including clamp body (1);The clamp body (1) is provided with clamping carrier rod (2), clamping carrier rod (2) is overall L-shaped rod structure, clamping carrier rod (2) is provided with reinforcing rib at bending place, clamping carrier rod (2) left end of left and right direction rod is provided with inside thread cylinder of front and back direction, clamping carrier rod (2) is provided with six front and back insertion blind holes of arrangement in front and back direction on the right side of outer periphery of front and back direction rod, clamping carrier rod (2) is provided with adjustable carrier rod (3) on front and back direction rod, adjustable carrier rod (3) right end is provided with sleeve of front and back direction, the sleeve right side wall of adjustable carrier rod (3) is provided with left and right through thread hole, adjustable carrier rod (3) left end is provided with the carrier cylinder of front and back direction, the carrier cylinder of adjustable carrier rod (3) is provided with bearing ring groove on the inside circumference of front, the left side wall of carrier cylinder of adjustable carrier rod (3) is provided with left and right through stop screw hole, the inside of thread hole of adjustable carrier rod (3) is mounted with limit locking column (4), limit locking column (4) is provided with thread on the outside circumference, limit locking column (4) right end surface is provided with regular hexagon slot.

2. The aircraft assembly rivet tool of Claim 1, wherein: The inside of inside thread cylinder of the clamping carrier rod (2) is mounted with clamping contact block (5) in front, the clamping contact block (5) rear end is provided with threaded column, the clamping contact block (5) threaded column front end surface is provided with regular hexagonal prism, the clamping contact block (5) regular hexagonal prism front end surface is provided with circular plate, the clamping contact block (5) circular plate front end surface is provided with circular groove, the clamping contact block (5) circular groove is mounted with rubber protective pad.

3. Aircraft assembly riveting tool according to claim 1 or 2, characterized in that: The inside of stop screw hole of the adjustable carrier rod (3) is mounted with fixed stop column (6), the fixed stop column (6) right side is provided with threaded column, the fixed stop column (6) threaded column left end outside circumference is provided with limit ring plate, the fixed stop column (6) threaded column left end surface is provided with regular hexagonal prism.

4. The aircraft assembly rivet tool of Claim 3, wherein: The inside of bearing ring groove of the adjustable carrier rod (3) is mounted with clamping rotating cylinder (7) by bearing, the inside circumference of clamping rotating cylinder (7) is provided with thread.

5. The aircraft assembly rivet tool of Claim 4, wherein: The outside circumference of clamping rotating cylinder (7) rear end is provided with bearing ring groove, and the outside circumference of clamping rotating cylinder (7) front is provided with regular hexagonal structure.

6. The aircraft assembly rivet tool of Claim 5, wherein: The inside of clamping moving rod (8) is mounted by thread, and the outside circumference of clamping moving rod (8) is provided with thread.

7. The aircraft assembly rivet tool of Claim 6, wherein: The rear end surface of clamping moving rod (8) is provided with circular plate, and the rear end surface of the circular plate of clamping moving rod (8) is provided with circular groove, and the inside of the circular groove of clamping moving rod (8) is mounted with rubber protective pad.

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