A two-way clamping mechanism for aircraft towing rod

Abstract

The present invention provides a bidirectional clamping mechanism for an aircraft towing rod, and belongs to the technical field of aircraft towing equipment. It solves the technical problems such as poor safety of a towing vehicle towing an aircraft through a towing rod. The bidirectional clamping mechanism of the aircraft towing rod comprises two groups of clamping assemblies arranged at the end of the aircraft towing rod, the two groups of clamping assemblies are arranged symmetrically and opposite to each other, the clamping assembly comprises a slide block fixedly connected to the guide rod head and the frame longitudinal beam, a sliding block is slidably arranged on the slide block, a clamping cylinder is arranged between the sliding block and the guide rod head, the shell end of the clamping cylinder is hinged on the side of the sliding block, the output shaft of the clamping cylinder is hinged to one side of the guide rod head, the other side of the guide rod head is provided with a clamping head, and the clamping head has a clamping notch; a guide structure is also provided between the sliding block and the guide rod head. The present invention can reduce one degree of freedom of the towing rod and improve the safety of the towing rod towing the aircraft.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft towing equipment and relates to a bidirectional clamping mechanism of an aircraft towing rod. Background Art

[0002] Existing aircraft tractors are generally connected to the aircraft through a towing rod, so that the aircraft can be towed to a specified location; since there are two hinge points between the towing rod, the tractor and the aircraft, there are two degrees of freedom between the tractor and the towing rod and between the aircraft and the towing rod during the process of the tractor towing the aircraft, which makes the operation difficult and prone to safety accidents.

[0003] A Chinese patent (announcement number: CN106882396A; announcement date: 2017-06-23) discloses a traction buffer device for an aircraft traction rod and an aircraft traction rod, comprising a connecting rod, a safety bolt, a mounting piece, an annular partition, a buffer, a quick docking joint and a shell, wherein a safety bolt is arranged at the first end of the connecting rod, the mounting piece is in the shape of a stepped column and is provided with a circle of protrusions at its small head, the mounting piece is provided with a through hole along its axial direction and is movably mounted on the rod body of the connecting rod near the first end, a retaining ring is fixedly provided on the rod body in the middle of the connecting rod, a plurality of annular partitions are movably mounted on the connecting rod and all the annular partitions are located on the same side of the large head of the mounting piece, a buffer is arranged between the large head of the mounting piece and the adjacent annular partition, a buffer is arranged between the annular retaining ring and the adjacent partition, a buffer is arranged between the adjacent partitions, the shell is in the shape of a tubular column and one end of which is open, and the quick docking joint docks the protrusion of the mounting piece with the open end of the shell.

[0004] The traction buffer device for an aircraft traction rod and the traction buffer device in an aircraft traction rod disclosed in the above patent document can buffer and absorb the impact force between the traction ring and the traction rod, reducing the damage caused during the traction process, but the safety hazard is still very large. Summary of the invention

[0005] The present invention aims at the above problems existing in the prior art and provides a bidirectional clamping mechanism for an aircraft towing rod. The technical problem to be solved by the present invention is: how to improve the safety of a towing vehicle towing an aircraft through a towing rod.

[0006] The purpose of the present invention can be achieved by the following technical solutions:

[0007] A bidirectional clamping mechanism for an aircraft towing rod, comprising two groups of clamping assemblies arranged at the ends of the aircraft towing rod, the two groups of clamping assemblies are arranged symmetrically and opposite to each other, and is characterized in that the clamping assembly comprises a slide block fixedly connected to a guide rod head and a frame longitudinal beam, a sliding block is slidably arranged on the slide block, a clamping cylinder is arranged between the sliding block and the guide rod head, the shell end of the clamping cylinder is hinged on the side of the sliding block, the output shaft of the clamping cylinder is hinged to one side of the guide rod head, the other side of the guide rod head is provided with a clamping head, and the clamping head has a clamping recess; a guide structure is also provided between the sliding block and the guide rod head.

[0008] Its working principle is as follows: In this technical solution, two sets of relative clamping assemblies are used in combination, and the two sets of clamping assemblies have the same structure and are arranged opposite to each other, and are used to clamp the aircraft traction rod, and the diameter of the aircraft traction rod is in the range of 130mm to 200mm. When it is not necessary to work, the clamping cylinder contracts, driving the entire clamping assembly to contract, that is, the clamping heads in the two clamping assemblies are moved away. When it is necessary to clamp the aircraft traction rod, the clamping cylinder extends, pushing the clamping heads to move relative to each other, clamping the aircraft traction rod, and clamping the aircraft traction rod through the clamping assembly reduces one degree of rotational freedom, reduces the driving difficulty of the driver, and avoids unnecessary safety accidents.

[0009] In the above-mentioned two-way clamping mechanism of the aircraft traction rod, the slide block is an I-shaped slide block, the sliding block is an I-shaped sliding block, the left and right sides of the slide block are provided with sliding grooves, the side of the sliding block has two left and right oppositely arranged snap-fitting convex strips, the snap-fitting convex strips on the sliding block are slidably snap-fitted in the corresponding sliding grooves; the two-way clamping mechanism also includes an electric cylinder capable of pushing the sliding block to move up and down on the slide block. The sliding connection matching structure of the above-mentioned sliding block and the slide block is stable and reliable; when the upper and lower position deviation of the clamping head and the aircraft traction rod is large, the electric cylinder pushes the sliding block to move up and down under the guidance of the slide block, adjusts the upper and lower positions of the clamping head, and realizes the action of clamping the aircraft traction rod.

[0010] In the above-mentioned two-way clamping mechanism of the aircraft towing rod, the guide structure includes a guide cylinder fixedly connected to the side of the sliding block and a guide rod fixedly connected to the guide rod head, and the guide rod is slidably inserted in the guide cylinder. The clamping cylinder only bears the clamping force in the horizontal direction, and the forces in other directions are borne by the guide structure. By setting the guide structure, the clamping cylinder is prevented from bearing the forces in the up and down directions, thereby ensuring the smooth and reliable movement of the clamping head.

[0011] In the above-mentioned bidirectional clamping mechanism of the aircraft towing rod, the guide cylinder is coaxially arranged with the guide rod, one end of the guide cylinder is fixedly connected to the side surface of the sliding block by a bolt, and the other end of the guide cylinder has an opening; a threaded mounting seat is provided on the side surface of the guide rod head, one end of the guide rod is screwed on the threaded mounting seat, and the other end is slidably inserted into the guide cylinder through the opening of the guide cylinder.

[0012] In the above-mentioned two-way clamping mechanism of the aircraft towing rod, the guide structures have two groups and are distributed in parallel and side by side on both sides of the clamping cylinder.

[0013] In the above-mentioned bidirectional clamping mechanism of the aircraft traction rod, a mounting bracket 1 is provided on the side surface of the sliding block, a mounting bracket 2 is provided on the inner side surface of the guide rod head, the shell end of the clamping cylinder is hinged to the mounting bracket 1 through a cylinder pin shaft 1, and the output shaft end of the clamping cylinder is hinged to the mounting bracket 2 through a cylinder pin shaft 2.

[0014] In the above-mentioned two-way clamping mechanism of the aircraft traction rod, a connecting seat is provided on the inner and outer sides of the guide rod head, the clamping head is V-shaped, the middle part of the clamping head is connected to the connecting seat through the clamping head pin, and a diaphragm spring is provided between the middle side of the clamping head and the outer side of the guide rod head. In the present technical scheme, an adaptive adjustment structure is particularly provided at the installation connection of the clamping head. When performing the clamping action, if the aircraft traction rod and the V-shaped surface of the clamping head are not in contact, or one of the two V-shaped surfaces of the clamping head is in contact and the other is not in contact, the clamping head will rotate around the clamping head pin, overcome the resistance of the diaphragm spring, and adaptively rotate a suitable small angle (the maximum adjustment angle of the present invention is 10°), so that the two V-shaped surfaces of the clamping head and the aircraft traction rod are completely in contact. When clamping is not required, the clamping head returns to the middle position under the action of the diaphragm spring to prevent the clamping head and the guide rod head from colliding during the driving process of the tractor and generating noise.

[0015] Compared with the prior art, the present invention has the following advantages:

[0016] 1. In the present invention, the aircraft towing rod is clamped by the clamping assembly, which reduces one rotational degree of freedom, reduces the driving difficulty for the driver, and avoids unnecessary safety accidents.

[0017] 2. The present invention provides a guide structure so that the clamping cylinder only bears the clamping force in the horizontal direction, and the forces in other directions are borne by the guide structure, thereby ensuring the smooth and reliable movement of the clamping head.

[0018] 3. The present invention provides an adaptive adjustment structure for the inner clamping head, so that both surfaces of the V-shaped block of the clamping head can contact the aircraft traction rod under any circumstances, avoiding contact with one surface, and ensuring stability and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a three-dimensional structural schematic diagram of the clamping assembly in the bidirectional clamping mechanism.

[0020] Figure 2 It is a schematic cross-sectional structural diagram of the clamping assembly in the bidirectional clamping mechanism.

[0021] Figure 3 It is a three-dimensional structural schematic diagram of the slide block in the bidirectional clamping mechanism.

[0022] Figure 4 It is a three-dimensional structural schematic diagram of the sliding block in the bidirectional clamping mechanism.

[0023] Figure 5 It is a schematic diagram of the partial cross-sectional structure of the bidirectional clamping mechanism.

[0024] In the figure, 1, guide rod head; 2, slide block; 21, sliding groove; 3, sliding block; 31, snap-on convex strip; 4, clamping cylinder; 5, clamping head; 51, clamping notch; 6, guide structure; 61, guide cylinder; 62, guide rod; 63, bolt; 64, threaded mounting seat; 7, mounting bracket 1; 8, mounting bracket 2; 9, cylinder pin shaft 1; 10, cylinder pin shaft 2; 11, connecting seat; 12, clamping head pin shaft; 13, diaphragm spring. DETAILED DESCRIPTION

[0025] The following are specific embodiments of the present invention and the accompanying drawings to further describe the technical solution of the present invention, but the present invention is not limited to these embodiments.

[0026] like Figures 1 to 4 As shown, the bidirectional clamping mechanism of the aircraft traction rod in this embodiment includes two groups of clamping components arranged at the end of the aircraft traction rod, the two groups of clamping components are arranged symmetrically and opposite to each other, the clamping components include a guide rod head 1 and a slide block 2 fixedly connected to the frame longitudinal beam, a sliding block 3 is slidably arranged on the slide block 2, a clamping cylinder 4 is arranged between the sliding block 3 and the guide rod head 1, the shell end of the clamping cylinder 4 is hinged on the side of the sliding block 3, the output shaft of the clamping cylinder 4 is hinged to one side of the guide rod head 1, and a clamping head 5 is arranged on the other side of the guide rod head 1, and a clamping recess 51 is provided on the clamping head 5; a guide structure 6 is also provided between the sliding block 3 and the guide rod head 1.

[0027] In this embodiment, two sets of relative clamping assemblies are used in combination. The two sets of clamping assemblies have the same structure and are arranged opposite to each other. They are used to clamp the aircraft traction rod. The diameter of the aircraft traction rod is in the range of 130mm to 200mm. When it is not necessary to work, the clamping cylinder 4 contracts, driving the entire clamping assembly to contract, that is, the clamping heads 5 in the two clamping assemblies are moved away. When it is necessary to clamp the aircraft traction rod, the clamping cylinder 4 extends, pushing the clamping heads 5 to move relative to each other, clamping the aircraft traction rod. Clamping the aircraft traction rod through the clamping assembly reduces one rotational degree of freedom, reduces the driving difficulty of the driver, and avoids unnecessary safety accidents.

[0028] Combination Figure 3 and Figure 4 As shown, the slide block 2 is an I-shaped slide block 2, and the sliding block 3 is an I-shaped sliding block 3. Sliding grooves 21 are provided on the left and right sides of the slide block 2. The side surface of the sliding block 3 has two left and right relatively arranged snap-fitting convex strips 31, and the snap-fitting convex strips 31 on the sliding block 3 are slidably snap-fitted in the corresponding sliding grooves 21; the bidirectional clamping mechanism also includes an electric cylinder capable of pushing the sliding block 3 to move up and down on the slide block 2; the sliding connection matching structure of the sliding block 3 and the slide block 2 is stable and reliable; when the upper and lower position deviations of the clamping head 5 and the aircraft traction rod are large, the electric cylinder pushes the sliding block 3 to move up and down under the guidance of the slide block 2, adjusts the upper and lower positions of the clamping head 5, and realizes the action of clamping the aircraft traction rod.

[0029] like Figure 1 and Figure 2 As shown, the guide structure 6 includes a guide cylinder 61 fixedly connected to the side of the sliding block 3 and a guide rod 62 fixedly connected to the guide rod head 1, and the guide rod 62 is slidably inserted in the guide cylinder 61; the clamping cylinder 4 only bears the clamping force in the horizontal direction, and the forces in other directions are borne by the guide structure 6. By setting the guide structure 6, the clamping cylinder 4 is prevented from bearing the forces in the up and down directions, and the stability and reliability of the movement of the clamping head 5 are guaranteed. Further, the guide cylinder 61 and the guide rod 62 are coaxially arranged, one end of the guide cylinder 61 is fixedly connected to the side of the sliding block 3 by a bolt 63, and the other end of the guide cylinder 61 has an opening; the side of the guide rod head 1 has a threaded mounting seat 64, one end of the guide rod 62 is screwed on the threaded mounting seat 64, and the other end is slidably inserted in the guide cylinder 61 through the opening of the guide cylinder 61; the guide structure 6 has two groups and is parallel and side by side distributed on both sides of the clamping cylinder 4.

[0030] Furthermore, there is a mounting bracket 7 on the side of the sliding block 3, and a mounting bracket 2 8 on the inner side of the guide rod head 1. The shell end of the clamping cylinder 4 is hinged to the mounting bracket 7 through a cylinder pin 9, and the output shaft end of the clamping cylinder 4 is hinged to the mounting bracket 2 8 through a cylinder pin 2 10.

[0031] Combination Figure 5As described, a connection seat 11 is provided on the inner and outer sides of the guide rod head 1, the clamping head 5 is V-shaped, the middle part of the clamping head 5 is connected to the connection seat 11 through the clamping head pin 12, and a diaphragm spring 13 is provided between the middle side of the clamping head 5 and the outer side of the guide rod head 1. In this embodiment, an adaptive adjustment structure is particularly provided at the installation connection of the clamping head 5. When performing the clamping action, if the aircraft traction rod and the V-shaped surface of the clamping head 5 are not in contact, or one of the two V-shaped surfaces of the clamping head 5 is in contact and the other is not in contact, the clamping head 5 will rotate around the clamping head pin 12, overcome the resistance of the diaphragm spring 13, and adaptively rotate to a suitable small angle. The maximum adjustment angle of the present invention is 10°, so that the two V-shaped surfaces of the clamping head 5 and the aircraft traction rod are completely in contact. When clamping is not required, the clamping head 5 returns to the middle position under the action of the diaphragm spring 13 to prevent the clamping head 5 and the guide rod head 1 from colliding during the driving of the tractor and generating noise.

[0032] The specific embodiments described herein are merely examples of the spirit of the present invention. Those skilled in the art may make various modifications or additions to the specific embodiments described or replace them in similar ways, but they will not deviate from the spirit of the present invention or exceed the scope defined by the appended claims.

Claims

1. A bidirectional clamping mechanism for an aircraft towing rod, comprising two sets of clamping assemblies arranged at the ends of the aircraft towing rod, the two sets of clamping assemblies being arranged symmetrically and facing each other, characterized in that: The clamping assembly comprises a guide rod head (1) and a slide block (2) fixedly connected to the longitudinal beam of the frame, a sliding block (3) is slidably arranged on the slide block (2), a clamping cylinder (4) is arranged between the sliding block (3) and the guide rod head (1), the shell end of the clamping cylinder (4) is hinged on the side of the sliding block (3), the output shaft of the clamping cylinder (4) is hinged to one side of the guide rod head (1), and a clamping head (5) is arranged on the other side of the guide rod head (1), and the clamping head (5) has a clamping recess (51); a guide structure (6) is also arranged between the sliding block (3) and the guide rod head (1); The clamping oil cylinder (4) only bears the clamping force in the horizontal direction, and the forces in other directions are borne by the guide structure (6); The slide block (2) is an I-shaped slide block (2), the sliding block (3) is an I-shaped sliding block (3), the slide block (2) is provided with sliding grooves (21) on the left and right sides, the side surface of the sliding block (3) is provided with two left and right oppositely arranged snap-fitting convex strips (31), the snap-fitting convex strips (31) on the sliding block (3) are slidably snap-fitted into the corresponding sliding grooves (21); the bidirectional clamping mechanism also includes an electric cylinder capable of pushing the sliding block (3) to reciprocate up and down on the slide block (2); A connecting seat (11) is provided on the outer side of the guide rod head (1); the clamping head (5) is V-shaped; the middle part of the clamping head (5) is connected to the connecting seat (11) via a clamping head pin (12); and a diaphragm spring (13) is provided between the side surface of the middle part of the clamping head (5) and the outer side surface of the guide rod head (1).

2. The two-way clamping mechanism of an aircraft towing rod according to claim 1, characterized in that: The guide structure (6) comprises a guide cylinder (61) fixedly connected to the side of the sliding block (3) and a guide rod (62) fixedly connected to the guide rod head (1); the guide rod (62) is slidably inserted in the guide cylinder (61).

3. The two-way clamping mechanism of an aircraft towing rod according to claim 2, characterized in that: The guide cylinder (61) and the guide rod (62) are coaxially arranged, one end of the guide cylinder (61) is fixedly connected to the side surface of the sliding block (3) by a bolt (63), and the other end of the guide cylinder (61) has an opening; a threaded mounting seat (64) is provided on the side surface of the guide rod head (1), one end of the guide rod (62) is screwed to the threaded mounting seat (64), and the other end is slidably inserted into the guide cylinder (61) through the opening of the guide cylinder (61).

4. The two-way clamping mechanism of an aircraft towing rod according to claim 3, characterized in that: The guide structures (6) have two groups and are distributed in parallel and side by side on both sides of the clamping cylinder (4).

5. The two-way clamping mechanism of an aircraft towing rod according to claim 1, characterized in that: The side surface of the sliding block (3) is provided with a mounting bracket 1 (7), the inner side surface of the guide rod head (1) is provided with a mounting bracket 2 (8), the shell end of the clamping cylinder (4) is hinged to the mounting bracket 1 (7) through a cylinder pin shaft 1 (9), and the output shaft end of the clamping cylinder (4) is hinged to the mounting bracket 2 (8) through a cylinder pin shaft 2 (10).

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