An aircraft towing device

Abstract

The application discloses an aircraft towing device and relates to the field of aircraft towing devices, which comprises a towing rod, one end of the towing rod is provided with a towing hook, the towing hook is fixedly provided with a connecting seat, a rotating seat is rotatably connected with a fixing block, the fixing block is slidably connected with a fixing rod, the rotating seat is provided with a fixing hole corresponding to the fixing rod, one end of the fixing block is rotatably connected with a lock catch, a limiting rod is arranged on one side of the lock catch, the limiting rod is fixedly connected with the towing hook, an auxiliary towing mechanism is arranged on the towing rod, and a buffer mechanism is arranged on the auxiliary towing mechanism. The connecting rod between the two wheels is hooked by the towing hook, the auxiliary towing mechanism on the towing rod is used for limiting the front wheels of the airplane, then the other end of the towing rod is connected with a towing vehicle, the auxiliary towing mechanism and the towing hook are used for driving the front wheels of the airplane, so that the pulling force borne by the towing hook is reduced, and the service life of the towing hook is prolonged.

Description

Technical Field

[0001] The present application relates to the field of aircraft towing, and in particular to an aircraft towing device. Background Art

[0002] An aircraft refers to an aircraft that can fly in the atmosphere. An aircraft must overcome various resistances in the air to fly, and the various meteorological conditions and aerodynamic forces in the atmosphere have various effects on the flight of aircraft. Aircraft are divided into two categories based on the different ways of obtaining lift. One category is lighter-than-air aircraft, which float in the air by relying on the buoyancy of the air, such as balloons and airships; the other category is heavier-than-air aircraft, including non-powered and powered types. The most common aircraft are airplanes of various sizes.

[0003] In the application of aircraft, in order to ensure the safe take-off and landing of aircraft, certain areas will be demarcated, and aircraft will be allowed to take off and land in the designated areas. Most aircraft taking off and landing in this area can also be parked in this area. This area is the airport we are familiar with. In order to allow the airport to accommodate more aircraft or to allow the aircraft to be parked neatly, the movement of the aircraft after landing is generally carried out by a traction device. The existing traction device is generally a traction rod, one end of the traction rod is connected to the front wheel of the aircraft, and the other end of the traction rod is connected to the tractor. The driver of the tractor then pulls the traction rod, and the traction rod moves the aircraft.

[0004] One end of the existing towing rod connected to the aircraft wheel is generally a towing hook. A dedicated connecting rod is fixed between the front wheels of the aircraft. When towing, the towing hook on the towing rod is directly hooked on the connecting rod. Then, when the towing rod is pulled, the towing hook pulls the connecting rod on the aircraft wheel to move. The force generated by pulling the aircraft is all applied to the single towing hook and the connecting rod on the aircraft wheel. If a heavy aircraft is driven by a single towing hook for a long time, the towing hook is likely to be damaged. Summary of the Invention

[0005] The purpose of the present application is to solve the problem raised in the above-mentioned background technology that when the towing rod is pulled, the towing hook pulls the connecting rod on the aircraft wheel to move, and the force generated by pulling the aircraft is all applied to the single towing hook and the connecting rod on the aircraft wheel. If a heavy aircraft is driven to move for a long time by only a single towing hook, the towing hook is likely to be damaged. The present application provides an aircraft towing device.

[0006] In order to achieve the above-mentioned purpose, this application specifically adopts the following technical solutions:

[0007] An aircraft towing device comprises a towing rod, a towing hook is provided at one end of the towing rod, a connecting seat is fixed on the towing hook, a fixing block is rotatably connected to the connecting seat, a fixing rod is slidably connected to the fixing block, a fixing hole corresponding to the fixing rod is opened on the connecting seat, one end of the fixing block is rotatably connected to a lock buckle, a limiting rod is provided on one side of the connecting lock buckle, the limiting rod is fixedly connected to the towing hook, an auxiliary towing mechanism is provided on the towing rod, and a buffer mechanism is provided on the auxiliary towing mechanism.

[0008] By adopting the above technical solution, the towing hook is hooked on the connecting rod specially used for towing between the two wheels, and then the auxiliary towing mechanism on the towing rod restricts the front wheel of the aircraft. Then, the other end of the towing rod is connected to the towing vehicle, so that the auxiliary towing mechanism can share the pulling force of the towing hook to move the aircraft, reduce the pulling force on the towing hook, and increase the service life of the towing hook. The buffer mechanism buffers the instantaneous pulling force of the aircraft wheels, which can further protect the towing hook and reduce the excessive pulling force on the towing hook at the moment of pulling. The auxiliary towing mechanism also restricts the front wheel of the aircraft when turning, reducing the wear of the towing hook when turning.

[0009] Furthermore, the auxiliary towing mechanism includes a support seat, which is fixedly connected to the traction rod, and two symmetrical support rods 1 are fixed on the support seat, and support rod 2 is slidably connected to support rod 1, and support block 1 is slidably connected to support rod 2, and two symmetrical support blocks 2 are provided on support block 1, and a dragging roller is rotatably connected to support block 2, an adjustment component 1 is provided between support rod 1 and support rod 2, and an adjustment component 2 is provided between support rod 2 and support block 1.

[0010] By adopting the above technical solution, the adjustment components 1 and 2 cooperate with each other to adjust each other, so that the drag roller on the support block 2 is in contact with the back of the aircraft wheel. When the tractor pulls the towing rod, the towing rod drives the drag roller on the support block 2, and the drag roller contacts the aircraft wheel and pushes the aircraft wheel forward from behind the aircraft wheel, thereby reducing the force applied to the towing hook during pulling and providing a certain degree of protection for the towing hook.

[0011] Furthermore, the adjustment component 1 includes two symmetrical adjustment blocks, the two adjustment blocks are fixedly connected to the corresponding support rod 2, a bidirectional threaded rod is arranged between the two adjustment blocks, the bidirectional threaded rod is threadedly connected to the adjustment block, a turbine is fixed in the middle of the bidirectional threaded rod, a support plate is fixed on the support seat, a worm is rotatably connected to the support plate, the worm corresponds to the turbine, a rocker is rotatably connected to the support plate, the rocker passes through the support plate, and is fixedly connected to the worm.

[0012] By adopting the above technical solution, the two adjustment blocks on the bidirectional threaded rod move relative to each other, and the adjustment blocks drive the support rod 2 to slide on the support rod 1, so that the support rod 2 and the dragging rollers approach each other, thereby making it convenient to move the dragging rollers closer to or away from each other, making it convenient for the aircraft's front wheel to pass between the dragging rollers on the adjacent support rods 2.

[0013] Furthermore, the second adjusting component includes two rotating seats symmetrically fixed on the support rod second, and the two rotating seats are rotatably connected with adjusting gears, an adjusting rack is fixed on the support rod one, and the adjusting rack is meshed with the adjusting gear, and a bevel gear one is provided on the rotating seat, and the bevel gear one passes through the rotating seat and is fixedly connected to the adjusting gear, and an adjusting threaded rod is rotatably connected to the support rod two, and a bevel gear two is fixed on the end of the adjusting threaded rod close to the bevel gear one, and the bevel gear one is meshed with the bevel gear two, and the support block one is threadedly connected to the adjusting threaded rod.

[0014] By adopting the above technical solution, when the adjusting gear moves on the adjusting rack, the adjusting gear transmission drives the bevel gear 1, the bevel gear 1 drives the bevel gear 2, the bevel gear 2 drives the adjusting threaded rod to rotate on the support rod 2, the adjusting threaded rod drives the support block 1 to move on the support rod 2, and the support block 1 brings the dragging roller on the support block 2 closer to the towing hook, so that the dragging rollers can contact the aircraft wheel that needs to be driven after approaching each other.

[0015] Furthermore, both ends of the bidirectional threaded rod are provided with limit blocks, and the limit blocks are fixedly connected to the bidirectional threaded rod.

[0016] By adopting the above technical solution, when the adjusting block moves to the position of the limiting block, it is blocked by the limiting block, thereby reducing the possibility of the adjusting block detaching from the bidirectional threaded rod.

[0017] Furthermore, the buffer mechanism includes a sliding plate fixed on the support block 2, a sliding groove corresponding to the sliding plate is opened on the support block 1, a buffer plate 1 is fixed on the side of the support block 1 away from the traction rod, a buffer plate 2 is fixed on the buffer plate 1, a hydraulic buffer rod 1 is arranged between the sliding plate and the buffer plate 2, one end of the hydraulic buffer rod 1 is fixedly connected to the buffer plate 2, and the other end of the hydraulic buffer rod 1 is fixedly connected to the sliding plate.

[0018] By adopting the above technical solution, when the aircraft wheel is pulled by the dragging roller, at the moment of pulling, the sliding plate on the support block 2 squeezes the hydraulic buffer rod 1 on the buffer plate 2, thereby reducing the possibility of the dragging roller being subjected to excessive pulling force at the moment of pulling.

[0019] Furthermore, a second hydraulic buffer rod is provided between the traction rod and the traction hook, one end of the second hydraulic buffer rod is fixedly connected to the traction hook, and the other end of the second hydraulic buffer rod is fixedly connected to the traction rod.

[0020] By adopting the above technical solution, when the towing hook is pulled, the hydraulic buffer rod 2 is dragged, and the hydraulic buffer rod 2 has a buffering effect on the pulling force between the towing hook and the aircraft wheel, thereby reducing the instantaneous pulling force generated by the towing hook when pulling the front wheel of the aircraft, and better protecting the towing hook.

[0021] Furthermore, the dragging roller is provided with a rubber ring, which is sleeved on the dragging roller and fixedly connected to the dragging roller.

[0022] By adopting the above technical solution, the rubber rings on the dragging rollers are allowed to interfere with each other, thereby reducing the wear between the dragging rollers and the aircraft wheels.

[0023] In summary, the present application includes at least one of the following beneficial effects:

[0024] 1. In the present application, after the towing hook and the connecting rod are fixed, the adjusting assembly 1 and the adjusting assembly 2 cooperate with each other, so that the drag roller on the support block 2 contacts the front wheel of the aircraft. When the tractor pulls the towing rod, the towing rod drives the support rod 1, the support rod 1 drives the support rod 2, and the support rod 2 pulls the aircraft wheel with the drag roller on the support block 2. At the same time, when towing, the buffer mechanism plays a certain role in buffering at the moment of pulling the front wheel of the aircraft, so that the drag roller can share the pulling force of the towing hook to move the aircraft, reduce the pulling force on the towing hook, and increase the service life of the towing hook. At the same time, the buffer mechanism buffers the instantaneous pulling force of driving the aircraft wheel, which can further protect the towing hook and reduce the excessive pulling force on the towing hook at the moment of pulling. The towing roller also restricts the front wheel of the aircraft when turning, thereby reducing the wear of the towing hook caused by deviation when turning.

[0025] 2. In the present application, the worm gear rotates to drive the turbine to rotate, and the turbine drives the bidirectional threaded rod to rotate, so that the adjustment block drives the second support rod to slide on the first support rod, and the adjustment gear on the second support rod moves on the adjustment rack on the first support rod. Then, through the cooperation of the first bevel gear and the second bevel gear, the adjustment threaded rod drives the first support rod to move on the second support rod, and finally the drag roller contacts the aircraft wheel, thereby achieving the purpose of conveniently adjusting the position of the drag roller and making the drag roller contact the aircraft wheel.

[0026] 3. The present application achieves the purpose of reducing the wear between the aircraft wheel and the drag roller by allowing the rubber ring on the drag roller to resist when the drag roller contacts the front wheel of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a first three-dimensional structural diagram of the traction device in this application;

[0028] Figure 2 It is a second three-dimensional structural diagram of the traction device in this application;

[0029] Figure 3 This application Figure 1 A in the middle is an enlarged schematic diagram;

[0030] Figure 4 This application Figure 1 The enlarged schematic diagram of point B in the middle;

[0031] Figure 5 This application Figure 2 Enlarged schematic diagram at point C in the middle;

[0032] Figure 6 It is a partial structural diagram of the towing hook in this application.

[0033] Description of reference numerals:

[0034] 1. Towing rod; 2. Towing hook; 3. Lock; 4. Connecting seat; 5. Fixed rod; 6. Limit rod; 7. Auxiliary towing mechanism; 71. Support seat; 72. Support rod 1; 73. Support rod 2; 74. Support block 1; 75. Support block 2; 76. Towing roller; 77. Adjusting assembly 1; 771. Adjusting block; 772. Bidirectional threaded rod; 773. Turbine; 774. Worm; 775. Support plate; 78. Adjusting assembly 2; 781. Adjusting rack; 782. Adjusting gear; 783. Rotating seat; 784. Bevel gear 1; 785. Bevel gear 2; 786. Adjusting threaded rod; 8. Buffer mechanism; 81. Sliding groove; 82. Sliding plate; 83. Buffer plate 1; 84. Buffer plate 2; 85. Hydraulic buffer rod 1; 86. Hydraulic buffer rod 2; 9. Fixed block; 10. Limit block; 11. Rubber ring. DETAILED DESCRIPTION

[0035] The following is combined with Figure 1 —6 Provide further details of this application.

[0036] An embodiment of the present application discloses an aircraft towing device.

[0037] Reference Figure 1—6. An aircraft towing device comprises a towing rod 1, a towing hook 2 being provided at one end of the towing rod 1, a connecting seat 4 being fixed to the towing hook 2, a fixing block 9 being rotatably connected to the connecting seat 4, a fixing rod 5 being slidably connected to the fixing block 9, a fixing hole corresponding to the fixing rod 5 being provided on the connecting seat 4, one end of the fixing block 9 being rotatably connected to a lock buckle 3, a limiting rod 6 being provided on one side of the connecting lock buckle 3, the limiting rod 6 being fixedly connected to the towing hook 2, an auxiliary towing mechanism 7 being provided on the towing rod 1, and a buffer mechanism 8 being provided on the auxiliary towing mechanism 7. When the towing device needs to be used for towing, first move the towing hook 2 on the towing rod 1 between the two front wheels of the aircraft, then hook the towing hook 2 on the connecting rod specially used for towing between the two wheels, and then let the fixing block 9 rotate on the connecting seat 4 with the lock buckle 3, so that the lock buckle 3 is driven. When the lock buckle 3 is driven to rotate, the lock buckle 3 is buckled on the towing hook 2, and the fixing rod 5 is inserted into the fixing hole on the connecting seat 4 to complete the fixation of the connecting rod between the two front wheels of the aircraft. Then, the auxiliary towing mechanism 7 on the towing rod 1 is restricted to the front wheels of the aircraft, and then the other end of the towing rod 1 is connected to the tractor. Under the pulling of the tractor, the towing rod 1 drives the towing hook 2 and the auxiliary towing mechanism 7 at the same time, and the towing hook 2 and the auxiliary towing mechanism 7 drive the aircraft. When the front wheel of the aircraft is being pulled, the buffer mechanism 8 on the auxiliary towing mechanism 7 plays a certain role in buffering at the moment of pulling the front wheel of the aircraft. When the tractor tows the towing rod 1, the auxiliary towing mechanism 7 and the towing hook 2 drive the front wheel of the aircraft together. At the same time, the buffer mechanism 8 is used to relieve the instantaneous pulling force when towing starts, so that the auxiliary towing mechanism 7 can share the pulling force of the towing hook 2 to move the aircraft, reduce the pulling force on the towing hook 2, and increase the service life of the towing hook 2. The buffer mechanism 8 buffers the instantaneous pulling force of driving the aircraft wheel, which can further protect the towing hook 2 and reduce the excessive pulling force on the towing hook 2 at the moment of pulling. The auxiliary towing mechanism 7 also restricts the front wheel of the aircraft when turning, reducing the wear of the towing hook 2 caused by deviation when turning.

[0038] Reference Figure 1 、 Figure 2 and Figure 4The auxiliary towing mechanism 7 includes a support seat 71, which is fixedly connected to the traction rod 1. Two symmetrical support rods 72 are fixed on the support seat 71. Support rod 1 72 is slidably connected to support rod 2 73. Support rod 2 73 is slidably connected to support block 1 74. Support block 1 74 is provided with two symmetrical support blocks 2 75. Support block 2 75 is rotatably connected to drag roller 76. An adjusting component 1 77 is provided between support rod 1 72 and support rod 2 73, and an adjusting component 2 78 is provided between support rod 2 73 and support block 1 74. After connecting the towing hook 2 to the connecting rod between the two front wheels of the aircraft, the two support rods 73 are slid on the support rod 1 72 by using the adjusting component 1 77, so that the two symmetrical support rods 73 are close to each other. When the two support rods 73 are close to each other, the adjusting component 2 78 is triggered, and the adjusting component 2 78 drives the support block 1 74 to slide on the support rod 2 73, and the support block 1 74 drives the support block 2 75. The drag roller 76 on the support block 2 75 contacts the back of the aircraft wheel. When the tractor pulls the towing rod 1, the tractor The guide rod 1 drives the towing hook 2 to pull the aircraft wheel to move. When the towing rod 1 pulls the towing hook 2, the towing rod 1 drives the support rod 1 72, the support rod 1 72 drives the support rod 2 73, and the support rod 2 73 drives the drag roller 76 on the support block 2 75. The drag roller 76 contacts the aircraft wheel and pushes the aircraft wheel forward behind the aircraft wheel. By utilizing the support rod 1 72 and the support rod 2 73 on the towing rod 1 to drag the aircraft wheel, the force applied to the towing hook 2 during pulling can be reduced, thereby playing a certain protective role for the towing hook 2.

[0039] Reference Figure 1 and Figure 2The adjustment component 77 includes two symmetrical adjustment blocks 771, and the two adjustment blocks 771 are fixedly connected to the corresponding support rod 2 73. A bidirectional threaded rod 772 is provided between the two adjustment blocks 771, and the bidirectional threaded rod 772 is threadedly connected to the adjustment block 771. A turbine 773 is fixed to the middle part of the bidirectional threaded rod 772, and a support plate 775 is fixed on the support seat 71. A worm 774 is rotatably connected to the support plate 775, and the worm 774 corresponds to the turbine 773. A rocker is rotatably connected to the support plate 775, and the rocker passes through the support plate 775 and is fixedly connected to the worm 774. When the towing hook 2 is hooked on the connecting rod between the two front wheels of the aircraft, the rocker is rotated, and the rocker drives the worm 774 on the support plate 775 to rotate. The rotation of the worm 774 drives the turbine 773 to rotate, and the turbine 773 drives the two-way threaded rod 772 to rotate. The two adjusting blocks 771 on the two-way threaded rod 772 move relative to each other, and the adjusting block 771 drives the support rod 2 73 to slide on the support rod 1 72, so that the support rod 2 73 and the dragging roller 76 approach each other. By using the two-way threaded rod 772 to control the movement of the support rod 2 73 on the support rod 1 72, it is convenient to make the dragging rollers 76 approach or move away from each other, so that the front wheels of the aircraft can pass between the dragging rollers 76 on the adjacent support rods 2 73.

[0040] Reference Figure 1 and Figure 4The adjustment component 2 78 includes two rotating seats 783 symmetrically fixed on the support rod 2 73, and the two rotating seats 783 are rotatably connected with the adjustment gears 782. An adjustment rack 781 is fixed on the support rod 1 72, and the adjustment rack 781 is engaged with the adjustment gear 782. A bevel gear 1 784 is provided on the rotating seat 783, and the bevel gear 1 784 passes through the rotating seat 783 and is fixedly connected to the adjustment gear 782. An adjustment threaded rod 786 is rotatably connected to the support rod 2 73, and a bevel gear 2 785 is fixed at one end of the adjustment threaded rod 786 close to the bevel gear 1 784. The bevel gear 1 784 is engaged with the bevel gear 2 785, and the support block 1 74 is threadedly connected to the adjustment threaded rod 786. When the second support rod 73 slides on the first support rod 72, the adjusting gear 782 on the second support rod 73 moves on the rack on the first support rod 72. When the adjusting gear 782 moves on the adjusting rack 781, the adjusting gear 782 rotates and drives the bevel gear 1 784. The bevel gear 1 784 drives the bevel gear 2 785. The bevel gear 2 785 drives the adjusting threaded rod 786 to rotate on the second support rod 73. The adjusting threaded rod 786 drives the support block 1 74 to move on the second support rod 73. The support block 1 74 brings the dragging roller 76 on the second support block 75 toward the towing hook 2, so that the dragging roller 76 contacts the rear of the aircraft wheel to be towed. By allowing the dragging roller 76 on the second support block 75 to slide on the support rod 2 73 under the support of the support block 1 74, the dragging roller 76 can contact the aircraft wheel to be driven after approaching each other.

[0041] Reference Figure 1 and Figure 4 Limit blocks 10 are provided at both ends of the bidirectional threaded rod 772, and the limit blocks 10 are fixedly connected to the bidirectional threaded rod 772. When contact traction is required, the bidirectional threaded rod 772 is rotated to move the adjustment block 771 toward the two ends of the bidirectional threaded rod 772. When the adjustment block 771 moves to the position of the limit blocks 10, it is blocked by the limit blocks 10. By using the limit blocks 10 to block the adjustment block 771, the possibility of the adjustment block 771 being separated from the bidirectional threaded rod 772 can be reduced.

[0042] Reference Figure 1 、 Figure 2 and Figure 5The buffer mechanism 8 includes a sliding plate 82 fixed on the support block 2 75, a sliding groove 81 corresponding to the sliding plate 82 is opened on the support block 1 74, a buffer plate 1 83 is fixed on the side of the support block 1 74 away from the traction rod 1, and a buffer plate 2 84 is fixed on the buffer plate 1 83. A hydraulic buffer rod 1 85 is arranged between the sliding plate 82 and the buffer plate 2 84, one end of the hydraulic buffer rod 1 85 is fixedly connected to the buffer plate 2 84, and the other end of the hydraulic buffer rod 1 85 is fixedly connected to the sliding plate 82. When the aircraft wheel is pulled by the drag roller 76, at the moment of pulling, the support block 2 75 slides on the support block 1 74, and the sliding plate 82 on the support block 2 75 squeezes the hydraulic buffer rod 1 85 on the buffer plate 2 84. The hydraulic buffer rod 1 85 is equipped with a return spring, a sliding push rod, and is filled with oil. When the hydraulic buffer rod 1 85 is subjected to pressure, kinetic energy is transmitted to the piston through the plug and the spring. The piston moves to squeeze the oil in the working chamber, and the return spring is compressed. The piston squeezes the oil to do work, consuming a large amount of kinetic energy and playing a buffering role. After the buffer contact, under the action of the return spring, the push rod is pushed back to its original position, and the push rod of the hydraulic buffer rod 1 85 returns to its original position, allowing the sliding plate 82 to return to its original position with the support block 2 75. By allowing the hydraulic buffer rod 1 85 to relieve the instantaneous pulling force generated by the drag roller 76 when pulling the aircraft wheel, the possibility of excessive pulling force on the drag roller 76 at the moment of pulling can be reduced.

[0043] Reference Figure 1 and Figure 2 A hydraulic buffer rod 86 is provided between the towing rod 1 and the towing hook 2. One end of the hydraulic buffer rod 86 is fixedly connected to the towing hook 2, and the other end of the hydraulic buffer rod 86 is fixedly connected to the towing rod 1. While the towing roller 76 is sliding due to the hydraulic buffer rod 85, the towing hook 2 is subjected to the tension of the aircraft wheel. The towing hook 2 is pulled, and when the towing hook 2 is pulled, the hydraulic buffer rod 86 is dragged. The hydraulic buffer rod 86 buffers the tension between the towing hook 2 and the aircraft wheel. By allowing the towing hook 2 to move with the aircraft wheel under the buffering effect of the hydraulic buffer rod 86, the instantaneous tension generated by the towing hook 2 when pulling the aircraft's front wheel can be reduced, thereby better protecting the towing hook 2.

[0044] Reference Figure 1 and Figure 2 The drag roller 76 is provided with a rubber ring 11, which is sleeved on the drag roller 76 and fixedly connected to the drag roller 76. When the drag roller 76 contacts the front wheel of the aircraft, the rubber ring 11 on the drag roller 76 contacts the front wheel of the aircraft. By positioning the rubber ring 11 between the aircraft wheel and the drag roller 76, wear between the drag roller 76 and the aircraft wheel can be reduced.

[0045] Working principle: When the traction device needs to be used for towing, first move the traction hook 2 on the traction rod 1 between the two front wheels of the aircraft, and then hook the traction hook 2 on the connecting rod specially used for towing between the two wheels, and then let the fixing block 9 rotate with the lock buckle 3 on the connecting seat 4, so that the lock buckle 3 is driven. When the lock buckle 3 is driven to rotate, the lock buckle 3 is buckled on the traction hook 2, and the fixing rod 5 is inserted into the fixing hole on the connecting seat 4 to complete the fixation of the connecting rod between the two front wheels of the aircraft, and then rotate the rocker, and the rocker drives the worm 774 on the support plate 775 to rotate, and the rotation of the worm 774 drives the turbine 773 to rotate, and the turbine 773 drives the two-way threaded rod 772 to rotate, and the two adjusting blocks 771 on the two-way threaded rod 772 move relative to each other, and the adjusting block 771 drives the support rod 2 73 to slide on the support rod 1 72, and the adjusting gear 782 on the support rod 2 73 moves on the rack on the support rod 1 72. When the adjusting gear 782 moves on the adjusting rack 781, the adjusting gear The rotation of 782 drives bevel gear 1 784, bevel gear 1 784 drives bevel gear 2 785, bevel gear 2 785 drives adjusting threaded rod 786 to rotate on support rod 2 73, adjusting threaded rod 786 drives support block 1 74 to move on support rod 2 73, support block 1 74 brings the drag roller 76 on support block 2 75 toward the direction of towing hook 2, while approaching each other, finally making the drag roller 76 hit the wheel of the aircraft, and then connecting the other end of the towing rod 1 to the towing vehicle. The tractor pulls the towing rod 1, and the towing rod 1 drives the towing hook 2 and the two towing rollers 76 to move the aircraft wheels. At the moment of pulling, the towing hook 2 pulls the hydraulic buffer rod 2 86. At the same time, the support block 2 75 slides on the support block 1 74, and the sliding plate 82 on the support block 2 75 squeezes the hydraulic buffer rod 1 85 on the buffer plate 2 84, so that the towing hook 2 and the towing roller 76 are buffered at the moment of pulling, protecting the towing hook 2 and the towing roller 76, and then the aircraft is pulled until it moves to the appropriate position.

Claims

1. An aircraft towing device, comprising a towing rod (1), characterized in that: A traction hook (2) is provided at one end of the traction rod (1), a connecting seat (4) is fixed on the traction hook (2), a fixing block (9) is rotatably connected to the connecting seat (4), a fixing rod (5) is slidably connected to the fixing block (9), a fixing hole corresponding to the fixing rod (5) is provided on the connecting seat (4), a lock buckle (3) is rotatably connected to one end of the fixing block (9), a limiting rod (6) is provided on one side of the lock buckle (3), and the limiting rod (6) is fixedly connected to the traction hook (2), an auxiliary dragging mechanism (7) is provided on the traction rod (1), and a buffer mechanism (8) is provided on the auxiliary dragging mechanism (7); The auxiliary dragging mechanism (7) includes a support seat (71), the support seat (71) is fixedly connected to the traction rod (1), two symmetrical support rods (72) are fixed on the support seat (71), the support rod (72) is slidably connected to the support rod (73), the support rod (73) is slidably connected to the support block (74), the support block (74) is provided with two symmetrical support blocks (75), the support block (75) is rotatably connected to the drag roller (76), an adjustment component (77) is provided between the support rod (72) and the support rod (73), and an adjustment component (78) is provided between the support rod (73) and the support block (74); The adjustment component 1 (77) includes two symmetrical adjustment blocks (771), the two adjustment blocks (771) are fixedly connected to the corresponding support rod 2 (73), a bidirectional threaded rod (772) is provided between the two adjustment blocks (771), the bidirectional threaded rod (772) is threadedly connected to the adjustment block (771), a worm gear (773) is fixed to the middle of the bidirectional threaded rod (772), a support plate (775) is fixed on the support seat (71), a worm (774) is rotatably connected to the support plate (775), the worm (774) corresponds to the worm gear (773), a rocker is rotatably connected to the support plate (775), the rocker passes through the support plate (775), and is fixedly connected to the worm gear (774); The adjustment component 2 (78) includes two rotating seats (783) symmetrically fixed on the support rod 2 (73), the two rotating seats (783) are rotatably connected with an adjustment gear (782), the support rod 1 (72) is fixed with an adjustment rack (781), the adjustment rack (781) and the adjustment gear (782) are meshed, the rotating seat (783) is provided with a bevel gear 1 (784), the bevel gear 1 (784) passes through the rotating seat (783) and is fixedly connected to the adjustment gear (782), the support rod 2 (73) is rotatably connected with an adjustment threaded rod (786), the adjustment threaded rod (786) is fixed with a bevel gear 2 (785) at one end close to the bevel gear 1 (784), the bevel gear 1 (784) and the bevel gear 2 (785) are meshed, and the support block 1 (74) is threadedly connected to the adjustment threaded rod (786); The buffer mechanism (8) includes a sliding plate (82) fixed on the support block 2 (75), a sliding groove (81) corresponding to the sliding plate (82) is provided on the support block 1 (74), a buffer plate 1 (83) is fixed on the side of the support block 1 (74) away from the traction rod (1), a buffer plate 2 (84) is fixed on the buffer plate 1 (83), a hydraulic buffer rod 1 (85) is provided between the sliding plate (82) and the buffer plate 2 (84), one end of the hydraulic buffer rod 1 (85) is fixedly connected to the buffer plate 2 (84), and the other end of the hydraulic buffer rod 1 (85) is fixedly connected to the sliding plate (82).

2. The aircraft towing device according to claim 1, characterized in that: Limit blocks (10) are provided at both ends of the bidirectional threaded rod (772), and the limit blocks (10) are fixedly connected to the bidirectional threaded rod (772).

3. The aircraft towing device according to claim 1, characterized in that: A second hydraulic buffer rod (86) is provided between the traction rod (1) and the traction hook (2), one end of the second hydraulic buffer rod (86) is fixedly connected to the traction hook (2), and the other end of the second hydraulic buffer rod (86) is fixedly connected to the traction rod (1).

4. The aircraft towing device according to claim 1, characterized in that: The dragging roller (76) is provided with a rubber ring (11), and the rubber ring (11) is sleeved on the dragging roller (76) and fixedly connected to the dragging roller (76).

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