CN110001992B - Aircraft connection device for an aircraft tractor and aircraft tractor - Google Patents
Aircraft connection device for an aircraft tractor and aircraft tractor Download PDFInfo
- Publication number
- CN110001992B CN110001992B CN201810008491.2A CN201810008491A CN110001992B CN 110001992 B CN110001992 B CN 110001992B CN 201810008491 A CN201810008491 A CN 201810008491A CN 110001992 B CN110001992 B CN 110001992B
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- aircraft
- lifting frame
- frame
- driving mechanism
- pushing
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- 230000007246 mechanism Effects 0.000 claims abstract description 135
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 230000009975 flexible effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/22—Ground or aircraft-carrier-deck installations for handling aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to an aircraft connection device for an aircraft tractor and the aircraft tractor. The aircraft tractor comprises a vehicle body, the rear end of the vehicle body is rotatably provided with a lifting frame along a horizontal axis, the lifting frame is provided with a collet for supporting the front of an aircraft, the lifting frame is also provided with a main pulling mechanism, the main pulling mechanism comprises a driving mechanism and a guy cable for connecting the driving mechanism with the main of the aircraft, and the lifting frame is also provided with a pressing mechanism for pressing the front wheel on the collet. When the aircraft traction operation is carried out, the aircraft is moved to the collet from the front, the pressing mechanism presses the front wheels, the guy cable is connected with the aircraft main crane and pulls the main crane to move forward under the action of the driving mechanism, and the aircraft can be carried to move on the ground when the tractor moves, so that the pulling force is fully applied to the aircraft main crane, and the front crane cannot be subjected to forward force, so that the rodless traction of the aircraft of some special models is realized.
Description
Technical Field
The invention relates to an aircraft connection device for an aircraft tractor and the aircraft tractor.
Background
Aircraft retractors are important devices that secure the movement of the aircraft ground. The existing aircraft tractor can be divided into two types of traction with a rod and traction without a rod according to different traction modes. The traction with the rod means that a traction rod is arranged on the aircraft tractor and is connected with the front part of the aircraft through the traction rod so as to realize the traction of the aircraft; rodless towing refers to the aircraft tractor lifting the front of the aircraft, the aircraft tractor forming an integral with the aircraft to effect aircraft towing. Compared with the rod traction mode, the rodless traction mode has various advantages such as small turning radius, light weight of the vehicle body, flexible operation, high operation efficiency, good universality and the like. For some special types of aircrafts, due to the characteristics of the aircrafts, an important problem needs to be considered when the aircrafts are towed, namely the aircrafts cannot bear pulling force when being towed, the pulling force can only act on the main aircraft, and when the aircrafts are towed, the existing wheel-holding type rodless towing mode is not suitable, and the ground moving operation can only be completed through the mode of rod towing.
Disclosure of Invention
The invention aims to provide an aircraft connecting device for an aircraft tractor, which is used for solving the problem that an aircraft which can not bear pulling force when being lifted forward can not be pulled in a rodless way; the invention also aims to provide an aircraft tractor.
In order to achieve the above object, the aircraft connection device for an aircraft tractor of the present invention adopts the following scheme:
scheme 1: the utility model provides an aircraft connecting device for aircraft tractor, includes the lifting frame, be equipped with the collet that is used for bearing aircraft to rise before the lifting frame, still be equipped with on the lifting frame and play pulling mechanism, play pulling mechanism includes actuating mechanism and connects actuating mechanism and aircraft and play the cable, still be equipped with the hold-down mechanism that is used for compressing tightly the front wheel on the collet on the lifting frame, actuating mechanism is the straight line actuating mechanism of the straight line action in the direction around the output, and the cable walks straight line actuating mechanism's output and pulls to play the antedisplacement when straight line actuating mechanism stretches out forward, lifting frame rear end has by the front and back downward sloping inclined plane.
The beneficial effects are that: when the aircraft traction operation is carried out, the aircraft is moved to the collet from the front, the pressing mechanism presses the front wheels, the guy cable is connected with the aircraft main crane and pulls the main crane to move forward under the action of the driving mechanism, and the aircraft can be carried to move on the ground when the tractor moves, so that the pulling force is fully applied to the aircraft main crane, and the front crane cannot be subjected to forward force, so that the rodless traction of the aircraft of some special models is realized. And the total length of the inhaul cable is not influenced when the aircraft turns leftwards or rightwards in the traction process of the aircraft, and additional moment is not brought to forward-lifting steering, so that the normal forward-lifting steering of the aircraft is ensured.
Scheme 2: on the basis of scheme 1, the linear driving mechanism comprises two telescopic cylinders which are arranged in parallel, and the two telescopic cylinders are respectively arranged on the left side and the right side of the lifting frame. The two telescopic cylinders act on different parts of the same inhaul cable, the inhaul cable is tensioned when the two telescopic cylinders stretch out simultaneously, and the inhaul cable is loosened when the two telescopic cylinders retract simultaneously, so that the inhaul cable is more stable and convenient to tighten and loosen.
Scheme 3: on the basis of scheme 2, the left and right sides of collet is equipped with the guide rail that extends back and forth, and telescopic cylinder's output slidable mounting is on the guide rail, and is equipped with the switching-over pulley that supplies the cable to walk around on it. When the telescopic cylinder stretches out and draws back the action, the output of telescopic cylinder can slide along the guide rail back and forth to realize tightening up and loosening of cable, the switching-over pulley makes the cable take place the switching-over at the output of telescopic cylinder, and a cable can realize being connected with the aircraft owner like this.
Scheme 4: on the basis of the scheme 3, a guide pulley for the stay cable to bypass and guide the stay cable to a reversing pulley arranged at the output end of the stay cable is arranged on the telescopic cylinder. The guide pulley guides the inhaul cable, so that the inhaul cable is prevented from winding.
Scheme 5: on the basis of any one of the schemes 1-4, a pushing mechanism for pushing the front part from the bottom support is further arranged on the lifting frame. When the traction is completed, the forward lifting is pushed down from the bottom support through the pushing mechanism, so that the airplane is separated from the lifting frame.
Scheme 6: on the basis of the scheme 5, the pushing mechanism comprises a pushing driving mechanism and a pushing plate connected to the output end of the pushing driving mechanism.
Scheme 7: on the basis of the scheme 6, the output end of the pushing driving mechanism is connected with a pushing frame, the pushing plate is arranged at the rear end of the pushing frame, and the compressing mechanism is arranged on the pushing frame.
Scheme 8: on the basis of any one of the schemes 1-4, the pressing mechanism is a pitching pressing mechanism and comprises a pressing plate rotatably arranged on the lifting frame along a horizontal axis and a pressing driving mechanism for driving the pressing plate to rotate. When the aircraft is lifted forward and moved onto the collet, the pressing plate is turned downwards to press the collet; when the traction is completed, the pressing plate can be turned upwards to release the bottom support, so that the bottom support is pressed or loosened through the pitching pressing mechanism, and the operation is convenient.
Scheme 9: on the basis of scheme 8, the clamp plate is installed on the lifting frame through the swing arm rotation, compresses tightly actuating mechanism and includes that one end is articulated with the lifting frame, the other end passes through the articulated flexible jar that compresses tightly of pivot of crank arm with the swing arm.
Scheme 10: on the basis of the scheme 5, the lifting frame comprises a U-shaped frame with a backward opening, the bottom support and the pushing mechanism are arranged in a U-shaped space of the U-shaped frame, and the lifting frame further comprises hinged connecting arms which are connected to the left side and the right side of the U-shaped frame and extend forwards.
The aircraft tractor of the invention adopts the following scheme:
scheme 1: the aircraft tractor comprises a vehicle body, wherein the rear end of the vehicle body is rotatably provided with a lifting frame along a horizontal axis, the lifting frame is provided with a collet for supporting the front of an aircraft, the lifting frame is also provided with a main pulling mechanism, the main pulling mechanism comprises a driving mechanism and a pull rope for connecting the driving mechanism with the main of the aircraft, the lifting frame is also provided with a pressing mechanism for pressing a front wheel on the collet, the driving mechanism is a linear driving mechanism for linear motion in the front-rear direction, the pull rope bypasses the output end of the linear driving mechanism and pulls the main to move forward when the linear driving mechanism stretches forward, and the rear end of the lifting frame is provided with an inclined plane inclined downwards from front to rear.
The beneficial effects are that: when the aircraft traction operation is carried out, the aircraft is moved to the collet from the front, the pressing mechanism presses the front wheels, the guy cable is connected with the aircraft main crane and pulls the main crane to move forward under the action of the driving mechanism, and the aircraft can be carried to move on the ground when the tractor moves, so that the pulling force is fully applied to the aircraft main crane, and the front crane cannot be subjected to forward force, so that the rodless traction of the aircraft of some special models is realized. And the total length of the inhaul cable is not influenced when the aircraft turns leftwards or rightwards in the traction process of the aircraft, and additional moment is not brought to forward-lifting steering, so that the normal forward-lifting steering of the aircraft is ensured.
Scheme 2: on the basis of scheme 1, the linear driving mechanism comprises two telescopic cylinders which are arranged in parallel, and the two telescopic cylinders are respectively arranged on the left side and the right side of the lifting frame. The two telescopic cylinders act on different parts of the same inhaul cable, the inhaul cable is tensioned when the two telescopic cylinders stretch out simultaneously, and the inhaul cable is loosened when the two telescopic cylinders retract simultaneously, so that the inhaul cable is more stable and convenient to tighten and loosen.
Scheme 3: on the basis of scheme 2, the left and right sides of collet is equipped with the guide rail that extends back and forth, and telescopic cylinder's output slidable mounting is on the guide rail, and is equipped with the switching-over pulley that supplies the cable to walk around on it. When the telescopic cylinder stretches out and draws back the action, the output of telescopic cylinder can slide along the guide rail back and forth to realize tightening up and loosening of cable, the switching-over pulley makes the cable take place the switching-over at the output of telescopic cylinder, and a cable can realize being connected with the aircraft owner like this.
Scheme 4: on the basis of the scheme 3, a guide pulley for the stay cable to bypass and guide the stay cable to a reversing pulley arranged at the output end of the stay cable is arranged on the telescopic cylinder. The guide pulley guides the inhaul cable, so that the inhaul cable is prevented from winding.
Scheme 5: on the basis of any one of the schemes 1-4, a pushing mechanism for pushing the front part from the bottom support is further arranged on the lifting frame. When the traction is completed, the forward lifting is pushed down from the bottom support through the pushing mechanism, so that the airplane is separated from the lifting frame.
Scheme 6: on the basis of the scheme 5, the pushing mechanism comprises a pushing driving mechanism and a pushing plate connected to the output end of the pushing driving mechanism.
Scheme 7: on the basis of the scheme 6, the output end of the pushing driving mechanism is connected with a pushing frame, the pushing plate is arranged at the rear end of the pushing frame, and the compressing mechanism is arranged on the pushing frame.
Scheme 8: on the basis of any one of the schemes 1-4, the pressing mechanism is a pitching pressing mechanism and comprises a pressing plate rotatably arranged on the lifting frame along a horizontal axis and a pressing driving mechanism for driving the pressing plate to rotate. When the aircraft is lifted forward and moved onto the collet, the pressing plate is turned downwards to press the collet; when the traction is completed, the pressing plate can be turned upwards to release the bottom support, so that the bottom support is pressed or loosened through the pitching pressing mechanism, and the operation is convenient.
Scheme 9: on the basis of scheme 8, the clamp plate is installed on the lifting frame through the swing arm rotation, compresses tightly actuating mechanism and includes that one end is articulated with the lifting frame, the other end passes through the articulated flexible jar that compresses tightly of pivot of crank arm with the swing arm.
Scheme 10: on the basis of the scheme 5, the lifting frame comprises a U-shaped frame with a backward opening, the bottom support and the pushing mechanism are arranged in a U-shaped space of the U-shaped frame, and the lifting frame further comprises hinged connecting arms which are connected to the left side and the right side of the U-shaped frame and extend forwards.
Drawings
FIG. 1 is a schematic view of an embodiment 1 of an aircraft retractor of the invention;
in the figure: 1. lifting the frame; 2. a bottom support; 3. a main pulling mechanism; 31. the telescopic cylinder is pulled by the main jack; 32. a guy cable; 33. a reversing pulley; 34. a guide pulley; 4. a compressing mechanism; 41. a pressing plate; 42. compressing the telescopic cylinder; 5. a pushing mechanism; 51. pushing the telescopic cylinder; 52. a push plate; 53. pushing the frame; 6. a guide rail; 7. and (5) hinging the connecting arm.
Detailed Description
Embodiments of the present invention will be further described with reference to the accompanying drawings.
The specific embodiment 1 of the aircraft tractor comprises a vehicle body, wherein an aircraft connecting device is rotatably arranged at the rear end of the vehicle body, the aircraft connecting device is structurally shown in fig. 1 and comprises a lifting frame 1 rotatably arranged at the rear end of the vehicle body along a horizontal axis, a base 2 for supporting the front of an aircraft is arranged at the rear position on the lifting frame, a main lifting pulling mechanism 3 is arranged at the front position on the lifting frame, the main lifting pulling mechanism comprises a driving mechanism and a guy cable 32 for connecting the driving mechanism and the main lifting of the aircraft, the guy cable 32 is provided with two free ends, the two free ends are respectively connected with the main lifting of the aircraft, and a pressing mechanism 4 for pressing front wheels on the base 2 is arranged at the front side of the base 2 on the lifting frame. The driving mechanism is a linear driving mechanism for outputting linear motion in the front-rear direction, in the embodiment, two main pulling telescopic cylinders 31 which are arranged on the left side and the right side of the lifting frame 1 in parallel are specifically adopted, the stay rope 32 bypasses the output end of the main pulling telescopic cylinders 31 and pulls the main pulling to move forward when the main pulling telescopic cylinders extend forwards, and the setting has the advantages that the total length of the stay rope 32 is not influenced when the aircraft turns leftwards or rightwards in the traction process, additional torque is not brought to the forward turning, and the normal turning of the front turning of the aircraft is ensured; in addition, the two telescopic cylinders act on different parts of the same inhaul cable 32, the inhaul cable 32 is tensioned when the two telescopic cylinders extend simultaneously, and the inhaul cable 32 is loosened when the two telescopic cylinders retract simultaneously, so that the inhaul cable 32 is more stable and convenient to tighten and loosen.
The left and right sides of collet 2 is equipped with the guide rail 6 that extends along the fore-and-aft direction, and the output slidable mounting of telescopic cylinder is on guide rail 6, and when the telescopic cylinder carried out the flexible action, the output of telescopic cylinder can slide along guide rail 6 back and forth to realize tightening up and loosening of cable 32. The output end of the telescopic cylinder is provided with a reversing pulley 33 which is used for the stay rope 32 to bypass, and the reversing pulley enables the stay rope 32 to be reversed at the output end of the telescopic cylinder, so that one stay rope 32 can be connected with the main aircraft. The telescopic cylinder is further provided with a guide pulley 34 at the rear side of the reversing pulley, and the guide pulley guides the inhaul cable 32 to avoid the inhaul cable 32 from winding. The rotation axes of the diverting pulley 33 and the guide pulley 34 extend vertically, and the cable 32 sequentially passes around the guide pulley 34 in an S-shape and is finally guided to the diverting pulley 33.
The lifting frame 1 is also provided with a pushing mechanism 5 for pushing the front part of the bottom support 2 from the bottom support 2, the pushing mechanism 5 comprises a pushing driving mechanism and a push plate 52 connected to the output end of the pushing driving mechanism, the pushing mechanism is specifically arranged in a mode that the output end of the pushing driving mechanism is connected with a pushing frame 53, the push plate 52 is arranged at the rear end of the pushing frame 53, and the pushing frame 53 is provided with a pressing mechanism 4. The pressing mechanism is specifically a pitching pressing mechanism and comprises a pressing plate 41 rotatably mounted on the lifting frame along a horizontal axis and a pressing driving mechanism for driving the pressing plate to rotate. Specifically, the pressing plate 41 is rotatably installed on the lifting frame 1 through a swinging arm, the pressing driving mechanism is a pressing telescopic cylinder 42, one end of the pressing telescopic cylinder is hinged with the lifting frame, and the other end of the pressing telescopic cylinder is hinged with a rotating shaft of the swinging arm through a crank arm. When the aircraft is lifted forward and moved onto the bottom support 2, the pressing plate 41 is turned downwards to press the bottom support 2; when the traction is completed, the pressing plate 41 is turned upwards to release the bottom support 2, so that the bottom support 2 is pressed or loosened through the pitching pressing mechanism, and the operation is convenient. The pushing drive mechanism and the compression drive mechanism here are telescopic cylinders, and other drive mechanisms may be used in other embodiments.
The lifting frame of this embodiment is the U-shaped frame that the opening is backward, and collet 2 and pushing mechanism set up in the U-shaped space of U-shaped frame, and the left and right sides of U-shaped frame is connected with articulated arm 7 that extends forward respectively.
When the aircraft traction operation is carried out, firstly, the aircraft tractor is moved to the front of the aircraft, the lifting frame is put down, and the guy cable is connected with the main aircraft; then the main driving mechanism acts, the inhaul cable is pulled forwards and the aircraft is driven to move forwards, and the inhaul cable is tightened when the front wheel of the aircraft rolls onto the bottom support; then the lifting frame is lifted to lift the front wheel of the airplane; finally, the pressing driving mechanism drives the pressing plate to move so as to press the front wheel on the bottom support, the docking of the aircraft tractor and the aircraft is completed, and the traction is started. After the aircraft is pulled in place, firstly, the lifting frame is dropped down, the pressing plate is rotated upwards, and the front wheel of the aircraft is released; then the inhaul cable is loosened; then the pushing driving mechanism pushes the pushing plate to push the airplane backwards until the front wheel of the airplane rolls off the bottom bracket; and finally, taking down the inhaul cable from the main body, and lifting the lifting frame to finish the separation of the tractor and the airplane.
Example 2: the difference from embodiment 1 is that the driving mechanism of the main pulling mechanism is two windlass arranged in parallel, at this time, two guy ropes are respectively arranged at the left side and the right side of the lifting frame, one end of each guy rope is connected to a roller of the windlass, the other end of each guy rope is used for connecting with the main of the aircraft, and the roller rotates to drive the guy ropes to tighten and loosen in the front-back direction.
Example 3: the difference from the embodiment 1 is that the linear driving mechanism adopts a gear rack, the output end of the rack is connected with a guy cable, and the linear driving can be realized by other modes such as screw-nut matching, a crank-slider mechanism or a linear motor.
Example 4: the difference from embodiment 1 is that the pressing mechanism includes an inclined pressing plate and a driving mechanism that carries the inclined pressing plate to perform linear motion in the front-rear direction, and in this case, the driving mechanism may be a telescopic cylinder or may be driven linearly by a screw-nut fit, a crank block mechanism, or a linear motor.
Example 5: the difference with the embodiment 1 is that the output end of the compressing telescopic cylinder is directly hinged with the swing arm, and the telescopic cylinder moves to drive the swing arm to rotate, so that the pressing plate on the swing arm rotates; the platen may be rotated by a motor, an engine, a hydraulic motor, or the like.
Example 6: the difference from embodiment 1 is that the stay is provided in a closed loop shape, and the stay is bypassed from the rear side of the aircraft main boom so as to move forward with the aircraft main boom.
The invention also provides an embodiment of the aircraft connecting device for the aircraft tractor, and the specific structure of the embodiment is the same as that of the aircraft connecting device in the aircraft tractor, and is not repeated here.
Claims (20)
1. The aircraft connecting device for the aircraft tractor is characterized by comprising a lifting frame, wherein a collet for supporting the front of an aircraft is arranged on the lifting frame, a main pulling mechanism is further arranged on the lifting frame and comprises a driving mechanism and a pull rope for connecting the driving mechanism with the main of the aircraft, a pressing mechanism for pressing a front wheel on the collet is further arranged on the lifting frame, the driving mechanism is a linear driving mechanism for linear motion in the front-rear direction, the pull rope bypasses the output end of the linear driving mechanism and pulls the main to move forward when the linear driving mechanism stretches forward, and the rear end of the lifting frame is provided with an inclined plane inclined downwards from front to rear.
2. An aircraft connection device for an aircraft retractor according to claim 1 wherein the linear drive mechanism comprises two telescopic cylinders arranged side by side, the two telescopic cylinders being arranged on the left and right sides of the lifting frame respectively.
3. The aircraft connection device for an aircraft tractor according to claim 2, wherein the left and right sides of the shoe are provided with guide rails extending back and forth, the output end of the telescopic cylinder is slidably mounted on the guide rails, and a reversing pulley for the stay cable to bypass is provided thereon.
4. An aircraft connection device for an aircraft retractor according to claim 3 wherein the telescopic cylinder is provided with a guide pulley around which the cable is passed to guide the cable to a reversing pulley provided at its output.
5. An aircraft connection device for an aircraft retractor according to any of claims 1-4 wherein the lifting frame is further provided with a pushing mechanism on the front side of the shoe for pushing the nose down from the shoe.
6. The aircraft connection device for an aircraft retractor of claim 5 wherein the ejector mechanism comprises an ejector drive mechanism and a push plate coupled to an output of the ejector drive mechanism.
7. The aircraft connection device for an aircraft tractor according to claim 6, wherein the output end of the pushing driving mechanism is connected with a pushing frame, the push plate is arranged at the rear end of the pushing frame, and the pressing mechanism is mounted on the pushing frame.
8. An aircraft connection device for an aircraft retractor according to any of claims 1-4 wherein the hold down mechanism is a pitch hold down mechanism comprising a hold down plate rotatably mounted to the lifting frame along a horizontal axis and a hold down drive mechanism for driving the rotation of the hold down plate.
9. The aircraft connection device for an aircraft retractor of claim 8 wherein the pressure plate is rotatably mounted to the lifting frame by a swing arm and the compression drive mechanism comprises a compression telescoping cylinder having one end hinged to the lifting frame and the other end hinged to the pivot of the swing arm by a crank arm.
10. The aircraft connection device for an aircraft retractor of claim 5 wherein the lifting frame comprises a U-shaped frame with an opening facing rearward, the shoe and the pushing mechanism being disposed in the U-shaped space of the U-shaped frame, the lifting frame further comprising hinged connection arms extending forwardly and laterally of the U-shaped frame.
11. The aircraft tractor comprises a vehicle body, and is characterized in that the rear end of the vehicle body is rotatably provided with a lifting frame along a horizontal axis, the lifting frame is provided with a collet for supporting the front of an aircraft, the lifting frame is also provided with a main pulling mechanism, the main pulling mechanism comprises a driving mechanism and a pull rope for connecting the driving mechanism with the main of the aircraft, the lifting frame is also provided with a pressing mechanism for pressing a front wheel on the collet, the driving mechanism is a linear driving mechanism for linear motion in the front-rear direction, the pull rope bypasses the output end of the linear driving mechanism and pulls the main to move forward when the linear driving mechanism stretches forward, and the rear end of the lifting frame is provided with a slope inclined downwards from front to rear.
12. The aircraft retractor of claim 11, wherein the linear drive mechanism comprises two telescoping cylinders disposed in parallel, the two telescoping cylinders being disposed on left and right sides of the lifting frame, respectively.
13. The aircraft retractor of claim 12, wherein the left and right sides of the shoe are provided with guide rails extending back and forth, the output end of the telescopic cylinder is slidably mounted on the guide rails, and a reversing pulley is provided thereon for the cable to bypass.
14. An aircraft retractor according to claim 13 wherein the telescopic cylinder is provided with a guide pulley around which the cable is passed to guide the cable to a reversing pulley provided at its output.
15. An aircraft retractor according to any of claims 11-14, wherein the lifting frame is further provided with a pushing mechanism on the front side of the shoe for pushing the nose down from the shoe.
16. The aircraft retractor of claim 15, wherein the ejector mechanism comprises an ejector drive mechanism and a push plate coupled to an output of the ejector drive mechanism.
17. The aircraft tractor of claim 16, wherein the output end of the push drive mechanism is coupled to a push frame, the push plate is disposed at a rear end of the push frame, and the hold-down mechanism is mounted on the push frame.
18. An aircraft retractor according to any of claims 11-14, wherein the hold-down mechanism is a pitch hold-down mechanism comprising a hold-down plate rotatably mounted to the lifting frame along a horizontal axis and a hold-down drive mechanism for driving the rotation of the hold-down plate.
19. The aircraft retractor of claim 18, wherein the pressure plate is rotatably mounted to the lifting frame by a swing arm, and the compression drive mechanism includes a compression telescoping cylinder having one end hinged to the lifting frame and the other end hinged to the pivot of the swing arm by a crank arm.
20. The aircraft retractor of claim 15, wherein the lifting frame includes a U-shaped frame with an opening facing rearward, the shoe and the pushing mechanism being disposed in a U-shaped space of the U-shaped frame, the lifting frame further including hinged connecting arms extending forwardly and connected to left and right sides of the U-shaped frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810008491.2A CN110001992B (en) | 2018-01-04 | 2018-01-04 | Aircraft connection device for an aircraft tractor and aircraft tractor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810008491.2A CN110001992B (en) | 2018-01-04 | 2018-01-04 | Aircraft connection device for an aircraft tractor and aircraft tractor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110001992A CN110001992A (en) | 2019-07-12 |
| CN110001992B true CN110001992B (en) | 2024-02-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810008491.2A Active CN110001992B (en) | 2018-01-04 | 2018-01-04 | Aircraft connection device for an aircraft tractor and aircraft tractor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110001992B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0394534A1 (en) * | 1989-04-28 | 1990-10-31 | MAN Gutehoffnungshütte Aktiengesellschaft | Tractor for aircraft without a towing bar (rotating blade) |
| CN1076902A (en) * | 1992-03-24 | 1993-10-06 | 水陆公司 | Transport the vehicle of an aircraft on the ground |
| JP2001010597A (en) * | 1999-06-25 | 2001-01-16 | Komatsu Ltd | Aircraft tractor |
| DE202010002355U1 (en) * | 2010-02-13 | 2010-07-08 | Schickling, Axel | Towing vehicle for aircraft, which can turn in particular on the spot with just as freely rotatable Bugradaufnahmevorrichtung |
| CN102673799A (en) * | 2012-04-13 | 2012-09-19 | 威海广泰空港设备股份有限公司 | Wheel holding mechanism of rodless aircraft tractor |
| CN104943873A (en) * | 2014-03-26 | 2015-09-30 | 中国农业机械化科学研究院 | Small aircraft carrying device and loading and transporting method |
| CN106043733A (en) * | 2016-06-15 | 2016-10-26 | 沈阳飞机工业（集团）有限公司 | Traction system used for traction of aircraft |
| CN207725643U (en) * | 2018-01-04 | 2018-08-14 | 新乡平原航空技术工程有限公司 | A kind of aircraft attachment device and airplane tractor for airplane tractor |
-
2018
- 2018-01-04 CN CN201810008491.2A patent/CN110001992B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0394534A1 (en) * | 1989-04-28 | 1990-10-31 | MAN Gutehoffnungshütte Aktiengesellschaft | Tractor for aircraft without a towing bar (rotating blade) |
| CN1076902A (en) * | 1992-03-24 | 1993-10-06 | 水陆公司 | Transport the vehicle of an aircraft on the ground |
| JP2001010597A (en) * | 1999-06-25 | 2001-01-16 | Komatsu Ltd | Aircraft tractor |
| DE202010002355U1 (en) * | 2010-02-13 | 2010-07-08 | Schickling, Axel | Towing vehicle for aircraft, which can turn in particular on the spot with just as freely rotatable Bugradaufnahmevorrichtung |
| CN102673799A (en) * | 2012-04-13 | 2012-09-19 | 威海广泰空港设备股份有限公司 | Wheel holding mechanism of rodless aircraft tractor |
| CN104943873A (en) * | 2014-03-26 | 2015-09-30 | 中国农业机械化科学研究院 | Small aircraft carrying device and loading and transporting method |
| CN106043733A (en) * | 2016-06-15 | 2016-10-26 | 沈阳飞机工业（集团）有限公司 | Traction system used for traction of aircraft |
| CN207725643U (en) * | 2018-01-04 | 2018-08-14 | 新乡平原航空技术工程有限公司 | A kind of aircraft attachment device and airplane tractor for airplane tractor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110001992A (en) | 2019-07-12 |
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