CN217515387U

CN217515387U - Integral clamping mechanism of airplane traction rod

Info

Publication number: CN217515387U
Application number: CN202121493494.3U
Authority: CN
Inventors: 文民青; 张振琪; 徐中亚
Original assignee: Hubei Hanggang Technology Co ltd
Current assignee: Hubei Hanggang Technology Co ltd
Priority date: 2021-06-30
Filing date: 2021-06-30
Publication date: 2022-09-30
Anticipated expiration: 2031-06-30

Abstract

The utility model provides an integral clamping mechanism of aircraft traction lever belongs to aircraft traction equipment technical field. The technical problem that the tractor pulls the airplane through the traction rod and the safety is poor is solved. The integrated clamping mechanism of the airplane traction rod comprises a first clamping head, a second clamping head, a first supporting rod and a second supporting rod along the length direction of the traction rod, wherein the first supporting rod and the second supporting rod are arranged on two sides of the traction rod, a first guide rod is arranged between the first supporting rod and the first clamping head, a first guide block and a first return spring positioned between the first guide block and the first clamping head are sleeved on the first guide rod, a second guide rod is arranged between the second supporting rod and the second clamping head, a second guide block and a second return spring positioned between the second guide block and the second clamping head are sleeved on the second guide rod, and a wedge block and a telescopic piece capable of driving the first clamping head and the second clamping head to move to enable the first clamping head and the second clamping head to be close to or far away from each other are arranged between the first supporting rod and the second supporting rod. The utility model discloses can reduce the degree of freedom of traction lever, improve the security that the traction lever pulled the aircraft.

Description

Integral clamping mechanism of airplane traction rod

Technical Field

The utility model belongs to the technical field of the aircraft pulling equipment, a integral clamping mechanism of aircraft traction lever is related to.

Background

The existing aircraft tractor is generally connected with an aircraft through a traction rod, so that the aircraft can be dragged to a specified position; because the tow bar has two pin joints with between tractor and the aircraft, consequently at the in-process that the tractor dragged the aircraft, it is great to have two degrees of freedom between tractor and the tow bar and between aircraft and the tow bar to make the operation degree of difficulty, the incident appears easily.

Chinese patent (publication No. CN 106882396A; published as 2017-06-23) discloses a traction buffer device used on an airplane traction rod and the airplane traction rod, which comprises a connecting rod, a safety bolt, a mounting piece, annular clapboards, buffer pieces, a quick butt joint and a shell, wherein the first end of the connecting rod is provided with the safety bolt, the mounting piece is in a step column shape, a circle of bulge is arranged at the small head part of the mounting piece, the mounting piece is axially provided with a through hole and movably sleeved on the rod body of the connecting rod close to the first end, the rod body at the middle part of the connecting rod is fixedly provided with a check ring, the connecting rod is movably sleeved with a plurality of annular clapboards, all the annular clapboards are positioned at the same side of the large head part of the mounting piece and the adjacent annular clapboards, the buffer pieces are arranged between the annular check rings and the adjacent clapboards, and the buffer pieces are arranged between the adjacent clapboards, the shell is in a tubular column shape, one end of the shell is opened, and the quick butt joint enables the bulge of the installation piece to be in butt joint with the open end of the shell.

The traction buffer device used on the airplane traction rod and the traction buffer device in the airplane traction rod disclosed by the patent documents can buffer and absorb the impact force between the traction ring and the traction rod, reduce the damage caused in the traction process, but the potential safety hazard is still very large.

Disclosure of Invention

The utility model discloses to the above-mentioned problem that prior art exists, provide an integral clamping mechanism of aircraft traction lever, the utility model aims to solve the technical problem that: how to improve the safety of the towing vehicle for towing the airplane through the tow bar.

The purpose of the utility model can be realized by the following technical proposal:

the utility model provides an integral clamping mechanism of aircraft traction lever, is including the tight first and the tight first two of clamp that are used for centre gripping aircraft traction lever, its characterized in that of clamp, it is connected with along traction lever length direction's branch one to press from both sides tight first, it is connected with along traction lever length direction's branch two to press from both sides tight first, branch one with two relative intervals of branch set up the both sides at the traction lever, branch one with it has set firmly guide bar one to press from both sides between the tight first, the cover is equipped with on the guide bar one fixes guide block one on the support and is located guide block one reaches reset spring two between the tight first of clamp, branch two with press from both sides and set firmly guide bar two between the tight first, the cover is equipped with on the guide bar two and fixes guide block two and is located guide block two reaches press from both sides the reset spring two between the tight first, branch one with between the branch two be equipped with the wedge just be connected with on the wedge and can drive its length direction along traction lever And the telescopic piece moves the first clamping head and the second clamping head to be close to or far away from each other.

The working principle is as follows: when the first clamping head and the second clamping head need to clamp the traction rod, the telescopic piece can drive the wedge block to move along the length direction of the traction rod, so that the wedge block can drive the first support rod and the second support rod to simultaneously get away from or approach the traction rod, the first support rod and the second support rod can respectively drive the first guide rod and the second guide rod to move so as to enable the first return spring and the second return spring to be in a compressed state, in the process, the first guide rod and the second guide rod can respectively drive the first clamping head and the second clamping head to mutually approach and clamp the traction rod, and the traction rod reduces one degree of freedom when towing an airplane, so that the driving difficulty is reduced, and the safety of the tractor towing the airplane through the traction rod is improved; when the traction rod does not need to be clamped, the telescopic piece drives the wedge block to be far away from the first supporting rod and the second supporting rod, and the first clamping head and the second clamping head can be driven to be far away from each other by the first reset spring and the second reset spring in a compressed state, so that the clamping of the first clamping head and the second clamping head on the traction rod is relieved.

In the integral clamping mechanism of foretell aircraft traction lever, one side of branch one has set firmly the court the actuating lever one that two branches extend, one side of branch two has set firmly the court the actuating lever two that one branch extends, actuating lever one with two relative intervals of actuating lever set up just the wedge is located actuating lever one with between the actuating lever two, the extensible member fix on the support and the output with the one end middle part looks rigid coupling of wedge, the wedge is close to the side of one end of actuating lever is with being close to the side of two one ends of actuating lever is court the inclined plane of wedge other end middle part slope, actuating lever one with two close one end of actuating lever all set firmly with correspond inclined plane matched with swash plate on the wedge. The wedge-shaped block can be driven to move by controlling the telescopic piece, so that the purpose of clamping the traction rod or releasing the clamping is achieved, and the clamping device is very convenient.

In the integrated clamping mechanism of the airplane drawbar, the first guide rod and the second guide rod are both strip-shaped round rods, a first round hole for the first guide rod to penetrate through is formed in the first guide block, and a second round hole for the second guide rod to penetrate through is formed in the second guide block; the driving rod I is sleeved with a limiting block I fixed on the support, and the driving rod II is sleeved with a limiting block II fixed on the support. The first limiting block and the second limiting block are arranged to prevent the first guide rod and the second guide rod from rotating around the axis of the first guide rod and the second guide rod in the moving process, and guarantee is provided for the first clamping head and the second clamping head to normally clamp the traction rod.

In the integrated clamping mechanism of the airplane drawbar, the limiting block one is located at one end of the driving rod one connected with the supporting rod one, and the limiting block two is located at one end of the driving rod two connected with the supporting rod two. The first limiting block and the second limiting block are arranged to provide guarantee for the first supporting rod and the second supporting rod to reset when the wedge-shaped block returns to the initial position.

In the integrated clamping mechanism of the airplane drawbar, the first driving rod and the second driving rod are rectangular rods, the first limiting block is provided with a first rectangular hole through which the first driving rod penetrates, and the second limiting block is provided with a second rectangular hole through which the second driving rod penetrates. The rectangular rod, the first rectangular hole and the second rectangular hole are matched to have a limiting effect, and the first driving rod and the second driving rod can be prevented from rotating around the axial direction when moving.

In the above-mentioned integrated clamping mechanism for an aircraft tow bar, the first strut and the second clamping head are located on one side of the tow bar, and the second strut and the first clamping head are located on the other side of the tow bar. The arrangement of the first support rod, the second support rod, the first clamping head and the second clamping head can reduce the space occupied by the whole clamping mechanism.

In the integral clamping mechanism of the airplane drawbar, the first clamping head comprises a first clamping part connected with the airplane drawbar and a first connecting part integrally formed with the first clamping part, the second clamping head comprises a second connecting part and a second clamping part connected with the airplane drawbar, one end of the first guide rod, which is far away from the first support rod, is fixed on one end side surface of the first connecting part, which is far away from the first support rod, one end of the second guide rod, which is far away from the second support rod, is fixed on one end side surface of the second connecting part, the first clamping part and the second clamping part are oppositely arranged below the first guide rod or the second guide rod, arc-shaped grooves connected with the outer side of the drawbar are formed on one opposite sides of the first clamping part and the second clamping part, a mounting groove for embedding one end of the second connecting part, which is far away from the second guide rod, is formed on the other side of the second clamping part, and a first pin shaft is penetrated through the end of the second connecting part, two ends of the first pin shaft penetrate through the groove wall of the mounting groove and are located on the outer side of the second clamping portion, positioning blocks are fixedly arranged at two ends of the first pin shaft, and limiting grooves for the two positioning blocks to be embedded into are formed in the outer side of the clamping portion. The positioning block and the limiting groove enable the second clamping part to rotate for a certain angle around the first pin shaft, and the arc-shaped groove of the first clamping head and the arc-shaped groove of the second clamping head can be completely attached to the outer side of the traction rod.

In the integral clamping mechanism of the airplane traction rod, the first clamping head comprises a first clamping part connected with the airplane traction rod and a first connecting part integrally formed with the first clamping part, the second clamping head comprises a second connecting part and a second clamping part connected with the airplane traction rod, one end of the first guide rod, far away from the first support rod, is fixed on one end side surface of the first connecting part, far away from the second support rod, is fixed on one end side surface of the second connecting part, the first clamping part and the second clamping part are oppositely arranged below the first guide rod or the second guide rod, one ends, opposite to the first clamping part and the second clamping part, are respectively provided with a V-shaped groove connected with the outer side of the traction rod, the other end of the second connecting part is provided with an open groove penetrating through the upper side and the lower side, one end, far away from the V-shaped groove, of the second clamping part is embedded in the open groove, and a pin shaft is penetrated through the end of the second clamping part Two ends of the second pin shaft penetrate through the groove walls on the two sides of the open groove, and a diaphragm spring is arranged between one end, far away from the V-shaped groove, of the second clamping part and the bottom of the open groove. The arrangement of the diaphragm spring can enable the V-shaped groove of the first clamping part and the V-shaped groove of the second clamping part to be attached to the traction rod, and the diaphragm spring can enable the second clamping part to reset under the action of elastic force when clamping is released.

In the integrated clamping mechanism of the airplane drawbar, the length of the first support rod is smaller than that of the second support rod, and the first driving rod and the first guide rod are parallel to each other and are respectively arranged at two ends of one side of the first support rod; the second driving rod is fixed to one end side face of the second supporting rod, the first supporting rod is provided with one end of the first driving rod and the second supporting rod is provided with one end of the second driving rod, the number of the second guide rods is two, the two guide rods are distributed on the other end side face of the second supporting rod side by side in a spaced mode, the second driving rod is parallel to the two guide rods, and the second guide block and the second reset spring are sleeved on one of the two guide rods. The first supporting rod is shorter than the second supporting rod, so that the clamping mechanism is compact in arrangement, and space is saved.

In the integrated clamping mechanism of the airplane traction rod, the telescopic part is a hydraulic oil cylinder, an air cylinder or an electric push rod. The hydraulic oil cylinder, the air cylinder and the electric push rod can provide enough power for the movement of the wedge block, and the smooth work of the clamping mechanism is ensured.

Compared with the prior art, the utility model has the advantages of it is following:

1. the utility model provides a clamping mechanism can press from both sides tight traction lever, makes the tractor reduce a rotational degree of freedom at the in-process of pulling the aircraft, reduces the driving degree of difficulty, reduces aircraft turning radius, has also improved the security that the tractor passes through the traction lever and pulls the aircraft.

2. The utility model discloses only need control the extensible member just can make press from both sides tight first and press from both sides tight first two and be close to each other and grasp the traction lever, it is very convenient.

3. The utility model discloses well actuating lever one and actuating lever two and stopper one and setting up of stopper two can prevent effectively that guide bar one and guide bar two from rotating around its axial, can grasp the traction lever smoothly for pressing from both sides tight first and press from both sides tight first two and provide the guarantee.

Drawings

Fig. 1 is a schematic perspective view of an integrated clamping mechanism of an airplane tow bar according to one embodiment of the present invention.

Fig. 2 is a top view of the integrated clamping mechanism of the tow bar of the airplane according to the first embodiment.

Fig. 3 is a schematic structural diagram of a first support rod, a first driving rod and a first clamping head in the first embodiment.

Fig. 4 is a schematic structural diagram of a second strut, a second driving rod and a second clamping head in the first embodiment.

Fig. 5 is a schematic structural diagram of the second clamping portion in the first embodiment.

Fig. 6 is a schematic structural diagram of a first guide block in the first embodiment.

Fig. 7 is a schematic structural diagram of a second limiting block in the first embodiment.

Fig. 8 is a schematic structural view of a second clamping head in the second embodiment.

In the figure, 1, a clamping head I; 1a, a first clamping part; 1b, a first connecting part; 2. a second clamping head; 2a, a connecting part II; 2a1, open slot; 2b, a second clamping part; 2b1, mounting groove; 2b2, a limit groove; 3. a first support rod; 4. a second supporting rod; 5. a first guide rod; 6. a first guide block; 6a, a first round hole; 7. a first return spring; 8. a second guide rod; 9. a second guide block; 9a, a round hole II; 10. a second return spring; 11. a wedge block; 12. a telescoping member; 13. a first driving rod; 14. a second driving rod; 15. a sloping plate; 16. a first limiting block; 16a, a first rectangular hole; 17. a second limiting block; 17a and a rectangular hole II; 18. an arc-shaped slot; 19. a first pin shaft; 20. positioning blocks; 21. a V-shaped groove; 22. a second pin shaft; 23. a diaphragm spring.

Detailed Description

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

The first embodiment is as follows:

as shown in fig. 1 to 4, the integrated clamping mechanism of the airplane tow bar in the embodiment includes a first clamping head 1 and a second clamping head 2 for clamping the airplane tow bar, a first strut 3 and a second strut 4 are arranged on two sides above the airplane tow bar side by side at intervals along the length direction of the tow bar, the first strut 3 and the second strut 4 are parallel to each other, the length of the first strut 3 is smaller than the length of the second strut 4, one end of the first strut is flush with the second strut 4, a first driving rod 13 extending towards the second strut 4 is fixedly arranged on one end side of the first strut 3, a first guide rod 5 parallel to the first driving rod 13 is fixedly arranged on the other end side of the first strut 3, the first driving rod 13 and the first guide rod 5 are positioned on the same side of the first strut 3, the first clamping head 1 is fixed on one end of the first guide rod 5 far away from the first strut 3, a second driving rod 14 extending towards the first strut 3 is fixedly arranged on one end side of the second strut 4 flush with the first strut 3, the other end side of the second support rod 4 is fixedly provided with two guide rods two 8 which are arranged side by side at intervals along the length direction of the second support rod 4, the driving rod two 14 is parallel to any one guide rod two 8 of the two guide rods two 8, the driving rod two 14 and the guide rod two 8 are positioned at the same side of the second support rod 4, the clamping head two 2 is fixed at one end of the two guide rods two 8 far away from the second support rod 4, the middle part of the guide rod one 5 is sleeved with a guide block one 6 fixed on the support, the middle part of one guide rod two 8 is sleeved with a guide block two 9 fixed on the support, the guide rod one 5 is sleeved with a return spring one 7, the return spring one 7 is positioned between the guide block one 6 and the clamping head one 1, the guide rod two 8 provided with the guide block two 9 is sleeved with a return spring two 10, the return spring two 10 is positioned between the guide block two 9 and the clamping head two 2, and the clamping head one 1 and the clamping head two 2 are both positioned below the guide rod one 5 or the two guide rods two 8, the first support rod 3 and the second clamping head 2 are positioned on one side of the traction rod, and the second support rod 4 and the first clamping head 1 are positioned on the other side of the traction rod.

Further, as shown in fig. 1 to 4, the first driving rod 13 and the second driving rod 14 are arranged at an interval and have a space therebetween, a wedge block 11 and an extensible member 12 are arranged between the first driving rod 13 and the second driving rod 14, the extensible member 12 is a hydraulic oil cylinder, an air cylinder or an electric push rod, a housing of the extensible member 12 is fixed on the bracket, an output end of the extensible member 12 is connected with the middle of one end of the wedge block 11, both a side surface of the wedge block 11 close to one end of the first driving rod 13 and a side surface close to one end of the second driving rod 14 are inclined surfaces extending towards the middle of the other end of the wedge block 11, and inclined plates 15 matched with the corresponding inclined surfaces of the wedge block 11 are fixedly arranged at one ends of the first driving rod 13 and the second driving rod 14; the telescopic piece 12 acts to enable the wedge block 11 to move along the length direction of the traction rod, and the wedge block 11 is matched with the inclined plate 15 on the driving rod I13 and the inclined plate 15 on the driving rod II 14 to enable the driving rod I13 and the driving rod II 14 to be close to or far away from the traction rod simultaneously, so that the clamping head I1 and the clamping head II 2 are close to or far away from the traction rod.

Further, as shown in fig. 1 to 7, the first guide rod 5 and the second guide rod 8 are bar-shaped round rods, the first guide block 6 is sleeved in the middle of the first guide rod 5, a first round hole 6a for the first guide rod 5 to penetrate through is formed in the first guide block 6, a second guide block 9 is sleeved in the middle of the second guide rod 8, a second round hole 9a for the second guide rod 8 to penetrate through is formed in the second guide block 9, the first drive rod 13 and the second drive rod 14 are rectangular rods, a first limit block 16 is sleeved at one end, connected with the first support rod 3, of the first drive rod 13, a first rectangular hole 16a for the first drive rod 13 to penetrate through is formed in the first rectangular block, a second limit block 17 is sleeved at one end, connected with the second support rod 4, of the second drive rod 14, and a second rectangular hole 17a for the second drive rod 14 to penetrate through is formed in the second rectangular block.

Further, as shown in fig. 1, 4 and 5, the first clamping head 1 includes a first connecting portion 1b and a first clamping portion 1a integrally formed with the first connecting portion 1b, the second clamping head 2 includes a second connecting portion 2a and a second clamping portion 2b, one end of the first guide rod 5, which is far away from the first support rod 3, is fixed on one end side of the first connecting portion 1b, one end of the second guide rod 8, which is far away from the second support rod 4, is fixed on one end side of the second connecting portion 2a, the first clamping portion 1a and the second clamping portion 2b are oppositely arranged, and arc-shaped grooves 18 connected with opposite side surfaces of the traction rod are formed on opposite sides of the first clamping portion 1a and the second clamping portion 2b, an installation groove 2b1 for embedding the other end of the second connecting portion 2a is formed in one side of the second clamping portion 2b, which is located in the installation groove 2b1, a first pin 19 is penetrated through two ends of the first pin 19 respectively through two side walls of the installation groove 2b and located on two sides of the second connecting portion 1 and located on the outer side of the second clamping portion 2a, the two ends of the first pin shaft 19 are fixedly provided with positioning blocks 20, and the outer side of the second connecting part 2a is provided with two limiting grooves 2b2 for the corresponding positioning blocks 20 to be embedded into.

When the traction rod needs to be clamped, the expansion piece 12 pushes the wedge block 11 to move along the length direction of the traction rod, the driving rod I13 and the driving rod II 14 are pushed towards two sides, the supporting rod I3 and the supporting rod II 4 also move towards two sides of the traction rod simultaneously, and then the guiding rod I5 and the guiding rod II 8 are driven to move, so that the clamping head I1 and the clamping head II 2 are close to each other to clamp the traction rod, the clamping head II 2 can swing around the pin shaft I19, so that the arc-shaped grooves 18 of the clamping head I1 and the clamping head II 2 can be completely attached to the outer side of the traction rod, in the process, the return spring I7 and the return spring II 10 are compressed, when the traction rod does not need to be clamped, the expansion piece 12 drives the wedge block 11 to be far away from the inclined plate 15, and the return spring I7 and the return spring II 10 can drive the guiding rod I5 and the guiding rod II 8 to move, so that the clamping head I1 and the clamping head II 2 are far away from each other; here, the diameters of the longitudinal sections of the first guide rod 5, the first circular hole 6a, the second guide rod 8 and the second circular hole 9a are all 60mm, and the lengths and widths of the longitudinal sections of the first drive rod 13, the first rectangular hole 16a, the second drive rod 14 and the second rectangular hole 17a are all 60mmX60 mm.

Example two:

as shown in fig. 8, the present embodiment has substantially the same contents as the first embodiment, except that the opposite ends of the first clamping portion 1a and the second clamping portion 2b are both provided with a V-shaped groove 21 connected to the outer side of the drawbar, the ends of the two guide rods 8 far away from the second support rod 4 are fixed to the side surface of the end of the second connecting portion 2a, the other end of the second connecting portion 2a is provided with an open groove 2a1 penetrating through the upper and lower sides, the end of the second clamping portion 2b far away from the V-shaped groove 21 is embedded in the open groove 2a1, the end of the second clamping portion 2b located in the open groove 2a1 is provided with a second pin 22, the two ends of the second pin 22 are embedded in the groove walls of the open groove 2a1, and the end of the second clamping portion 2b located in the open groove 2a1 is provided with a diaphragm spring 23 connected to the bottom of the open groove 2a 1.

When the clamping action is carried out, if the traction rod is not jointed with the V-shaped groove 21 of the first clamping head 1 and the V-shaped groove 21 of the second clamping head 2 or the traction rod is jointed with the V-shaped groove 21 of one of the clamping heads and is not contacted with the other one of the clamping heads, the second clamping part 2b can rotate around the second pin shaft 22 against the resistance of the diaphragm spring 23, so that the second clamping part can rotate by a proper small angle, wherein the maximum angle is 10 degrees, the V-shaped groove 21 of the first clamping head 1 and the V-shaped groove 21 of the second clamping head 2 are completely jointed with the traction rod, when the clamping is not needed, the first clamping head 1 and the second clamping head 2 are far away from each other, and the second clamping part 2b returns to the original position under the action of the diaphragm spring 23.

The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications or additions may be made to the described embodiments or alternatives may be employed by those skilled in the art without departing from the spirit or ambit of the invention as defined in the appended claims.

Claims

1. An integral clamping mechanism of an airplane traction rod comprises a first clamping head (1) and a second clamping head (2) which are used for clamping the airplane traction rod, and is characterized in that the first clamping head (1) is connected with a first support rod (3) along the length direction of the traction rod, the second clamping head (2) is connected with a second support rod (4) along the length direction of the traction rod, the first support rod (3) and the second support rod (4) are arranged on two sides of the traction rod at intervals, a first guide rod (5) is fixedly arranged between the first support rod (3) and the first clamping head (1), a first guide block (6) fixed on a support and a first return spring (7) positioned between the first guide block (6) and the first clamping head (1) are sleeved on the first guide rod (5), a second guide rod (8) is fixedly arranged between the second support rod (4) and the second clamping head (2), the cover is equipped with guide block two (9) of fixing on the support and is located on guide bar two (8) guide block two (9) reach press from both sides reset spring two (10) between tight head two (2), branch one (3) with be equipped with wedge (11) just between branch two (4) be connected with on wedge (11) and drive its length direction removal messenger along the traction lever it is first (1) to press from both sides tight head two (2) and be close to each other or the extensible member (12) of keeping away from each other.

2. The integrated clamping mechanism of the aircraft drawbar according to claim 1, characterized in that a first driving rod (13) extending towards the second supporting rod (4) is fixedly arranged at one side of the first supporting rod (3), a second driving rod (14) extending towards the first supporting rod (3) is fixedly arranged at one side of the second supporting rod (4), the first driving rod (13) and the second driving rod (14) are arranged at intervals relatively, the wedge block (11) is positioned between the first driving rod (13) and the second driving rod (14), the telescopic member (12) is fixed on a bracket, the output end of the telescopic member is fixedly connected with the middle part of one end of the wedge block (11), the side surface of the wedge block (11) close to one end of the first driving rod (13) and the side surface of one end of the second driving rod (14) are inclined surfaces inclining towards the middle part of the other end of the wedge block (11), and the inclined plate (15) matched with the corresponding inclined plane on the wedge-shaped block (11) is fixedly arranged at one end of the driving rod I (13) close to one end of the driving rod II (14).

3. The integrated clamping mechanism for the aircraft drawbar according to claim 2, characterized in that the first guide bar (5) and the second guide bar (8) are both bar-shaped round bars, the first guide block (6) is provided with a first round hole (6a) for the first guide bar (5) to pass through, and the second guide block (9) is provided with a second round hole (9a) for the second guide bar (8) to pass through; the driving rod I (13) is sleeved with a limiting block I (16) fixed on the support, and the driving rod II (14) is sleeved with a limiting block II (17) fixed on the support.

4. The integrated clamping mechanism of the aircraft drawbar according to claim 3, characterized in that the first stopper (16) is located at the end where the first driving rod (13) is connected with the first strut (3), and the second stopper (17) is located at the end where the second driving rod (14) is connected with the second strut (4).

5. The integrated clamping mechanism of the airplane drawbar according to claim 4, characterized in that the first driving rod (13) and the second driving rod (14) are rectangular rods, the first limiting block (16) is provided with a first rectangular hole (16a) for the first driving rod (13) to pass through, and the second limiting block (17) is provided with a second rectangular hole (17a) for the second driving rod (14) to pass through.

6. The integrated clamping mechanism for the aircraft tow bar according to claim 1 or 2, characterized in that the first strut (3) and the second clamping head (2) are located on one side of the tow bar, and the second strut (4) and the first clamping head (1) are located on the other side of the tow bar.

7. The integrated clamping mechanism of the aircraft drawbar according to claim 1 or 2, characterized in that the first clamping head (1) comprises a first clamping portion (1a) connected with the aircraft drawbar and a first connecting portion (1b) integrally formed with the first clamping portion (1a), the second clamping head (2) comprises a second connecting portion (2a) and a second clamping portion (2b) connected with the aircraft drawbar, one end of the first guide rod (5) away from the first strut (3) is fixed on one end side of the first connecting portion (1b) away from the first clamping portion (1a), one end of the second guide rod (8) away from the second strut (4) is fixed on one end side of the second connecting portion (2a), and the first clamping portion (1a) and the second clamping portion (2b) are oppositely arranged below the first guide rod (5) or the second guide rod (8), clamping part one (1a) with arc wall (18) that meet outside the traction lever have all been opened to the relative one side of clamping part two (2b), the opposite side of clamping part two (2b) is opened and is supplied connecting part two (2a) are kept away from mounting groove (2b1) of guide bar two (8) one end embedding just round pin axle one (19) are worn to be equipped with by this end of connecting part two (2a), the both ends of round pin axle one (19) are passed respectively the cell wall of mounting groove (2b1) just all are located the outside of clamping part two (2b), round pin axle one (19) both ends all set firmly locating piece (20), open in the clamping part two (2b) outside has supplied two spacing groove (2b2) of locating piece (20) embedding.

8. The integrated clamping mechanism of the aircraft drawbar according to claim 1 or 2, characterized in that the first clamping head (1) comprises a first clamping portion (1a) connected with the aircraft drawbar and a first connecting portion (1b) integrally formed with the first clamping portion (1a), the second clamping head (2) comprises a second connecting portion (2a) and a second clamping portion (2b) connected with the aircraft drawbar, one end of the first guide rod (5) away from the first strut (3) is fixed on one end side of the first connecting portion (1b) away from the first clamping portion (1a), one end of the second guide rod (8) away from the second strut (4) is fixed on one end side of the second connecting portion (2a), and the first clamping portion (1a) and the second clamping portion (2b) are oppositely arranged below the first guide rod (5) or the second guide rod (8), clamping part (1a) one end relative with clamping part two (2b) all opens V-arrangement groove (21) that meet with the traction lever outside, open slot (2a1) of both sides about running through is opened to the other end of connecting portion two (2a), clamping part two (2b) are kept away from the one end of V-arrangement groove (21) is inlayed and is established in open slot (2a1) just this end of clamping part two (2b) is worn to be equipped with round pin axle two (22), the both ends of round pin axle two (22) are worn to establish on the both sides cell wall of open slot (2a1), clamping part two (2b) are kept away from the one end of V-arrangement groove (21) with be equipped with diaphragm spring (23) between open slot (2a1) the tank bottom.

9. The integrated clamping mechanism of the aircraft tow bar according to claim 2, wherein the length of the first strut (3) is smaller than the length of the second strut (4), and the first driving rod (13) and the first guide rod (5) are parallel to each other and are respectively arranged at two ends of one side of the first strut (3); fixed in actuating lever two (14) on the one end side of branch two (4), branch one (3) are equipped with the one end of actuating lever one (13) with branch two (4) are equipped with the one end of actuating lever two (14) is leveled mutually, the quantity of guide bar two (8) is two, two guide bar two (8) are in side by side interval distribution just on the other end side of branch two (4) actuating lever two (14) and arbitrary guide bar two (8) are parallel to each other, guide block two (9) with reset spring two (10) are all established and are established at one of them on guide bar two (8).

10. An integral clamping mechanism for an aircraft tow bar according to claim 1 or claim 2 wherein the telescopic member (12) is a hydraulic ram, an air cylinder or an electric push rod.