CN108545211B - Rodless aircraft tractor overload protection device - Google Patents
Rodless aircraft tractor overload protection device Download PDFInfo
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- CN108545211B CN108545211B CN201810604427.0A CN201810604427A CN108545211B CN 108545211 B CN108545211 B CN 108545211B CN 201810604427 A CN201810604427 A CN 201810604427A CN 108545211 B CN108545211 B CN 108545211B
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- tractor
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- protection device
- overload protection
- sensor
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- 239000000872 buffer Substances 0.000 claims abstract description 51
- 230000001133 acceleration Effects 0.000 claims abstract description 21
- 230000001105 regulatory effect Effects 0.000 claims abstract description 14
- 230000003139 buffering effect Effects 0.000 abstract description 9
- 239000012464 large buffer Substances 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 13
- 238000000034 method Methods 0.000 description 6
- 239000010720 hydraulic oil Substances 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 230000003449 preventive effect Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
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Classifications
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- 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
- B64F1/223—Ground or aircraft-carrier-deck installations for handling aircraft for towing aircraft
- B64F1/225—Vehicles specially adapted therefor, e.g. aircraft tow tractors
- B64F1/227—Vehicles specially adapted therefor, e.g. aircraft tow tractors for direct connection to aircraft, e.g. tow tractors without towing bars
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Agricultural Machines (AREA)
Abstract
An overload protection device for a rodless aircraft tractor comprises a buffer device and a control system; the buffer device comprises a buffer hydraulic cylinder, a slide block track and four connecting rods; the control system comprises a speed sensor, a hydraulic pressure sensor, an acceleration sensor, a position sensor, a controller, a power supply, an alarm system, a display system and an electric control regulating valve; the invention has the advantages that: adopt buffering pneumatic cylinder, can cushion the variable traction load under the special condition, protection aircraft and tractor avoid destroying, prevent the overload, avoid the fatigue life of aircraft undercarriage structure to shorten, and then reduce airline's operation cost. Four buffering hydraulic cylinders are adopted, so that the buffering force is stable, and the comfort of a tractor driver and an airplane passenger can be improved. Four buffering pneumatic cylinders parallel distribution can not destroy the control performance of tractor. The four buffer hydraulic cylinders have large buffer force and are particularly suitable for dealing with the object with large mass such as an airplane.
Description
Technical Field
The invention relates to an overload protection device for a rodless aircraft tractor, and belongs to the field of rodless aircraft traction overload protection.
Background
Nowadays, as the utilization amount of tractors is increased, traction accidents are frequent, and a great amount of property loss is caused. Excessive traction loads are one of the main causes of traction accidents. For an aircraft operation department with zero tolerance to safety accidents, the aircraft traction accident is not allowed no matter what cause.
The ground traction of the aircraft is an important link for ensuring the aircraft to pass a station, and the aircraft tractor can be divided into a rod type aircraft tractor and a rodless type aircraft tractor in the form of traction. The rod aircraft tractor is mostly connected with a nose landing gear of an aircraft through a hinged rigid traction rod, a buffer device is arranged on part of aircraft traction rods, and the traction rods are used for transmitting force to carry out traction or pushing operation on the aircraft. The rodless aircraft tractor utilizes the clamping and lifting device to hold the front wheel of the aircraft and carries out traction or pushing operation on the aircraft. Compared with a rod tractor, the rodless tractor directly holds the front wheels of the airplane, so that a middle traction rod is omitted, and the flexibility of traction is improved. However, in the process of towing the airplane by the rodless airplane towing vehicle, towing accidents are occasionally caused. In the operation process of towing an airplane by a towing vehicle, under the conditions of poor operation environment, emergency, irregular operation of operators and the like, a towing vehicle driver can perform treatments of sudden braking, sudden acceleration and the like, and the treatment mode can generate large towing loads which can have serious consequences once the loads exceed the bearing limit of related components, particularly for the undercarriage part of the airplane. During the towing of an aircraft by a pole-type aircraft tow vehicle, if an overload condition occurs, other components are protected by the shear pins on the tow bar breaking. In the case of conventional rodless aircraft tractors, there is no corresponding overload protection device in order to avoid overload situations during the aircraft traction process. The current approach is: in the traction operation specification, strict regulations are made on the traction speed of the airplane, the type matching of the tractor, the traction program and the like. These regulations, while capable of ensuring safety to some extent, necessarily reduce speed and traction efficiency, are a preventive measure and are disadvantageous in the event of an emergency (e.g., rescue and war).
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide an overload protection device for a rodless aircraft tractor, so as to improve the safety of an airport and reduce the loss of lives and properties.
In order to achieve the aim, the rodless aircraft tractor overload protection device comprises a buffer device and a control system; the buffer device comprises four buffer hydraulic cylinders, a slide block track and four connecting rods; the slide block tracks are formed along the sliding direction of the airplane or arranged on the inner surfaces of the two sides of the rear part of the upper frame of the rodless airplane tractor; the sliding block is arranged at the inner rear part of the frame, the bosses on the two side surfaces and the sliding rods on the two sides of the front end are respectively inserted into corresponding positions of the sliding block track, and the two side parts of the upper end and the lower end are respectively provided with a notch; the front part of the frame is provided with a clamping and lifting mechanism; the circumferential surfaces of the front part and the rear part of the cylinder body of the buffer hydraulic cylinder are respectively provided with an oil inlet and an oil outlet, and the interior of the cylinder body is divided into two chambers by a piston; the front ends of the cylinder bodies of the four buffer hydraulic cylinders are respectively fixed at four corners of the rear end surface of the frame, the hydraulic rod forwards penetrates through the rear end plate of the frame and then is hinged with the rear end of one connecting rod through one notch on the sliding block, and the front ends of the four connecting rods are simultaneously hinged on the rear end surface of the clamping and lifting mechanism; the control system comprises a speed sensor, a hydraulic pressure sensor, an acceleration sensor, a position sensor, a controller, a power supply, an alarm system, a display system and an electric control regulating valve; the electric control regulating valve is respectively connected with two oil inlets and two oil outlets on the cylinder body of the buffer hydraulic cylinder through a high-pressure hydraulic pipeline; the speed sensor and the acceleration sensor are arranged on the frame; the hydraulic pressure sensor is arranged at an oil inlet and an oil outlet on the cylinder body; the position sensor is arranged on the sliding block; the speed sensor, the hydraulic pressure sensor, the acceleration sensor, the position sensor, the alarm system, the display system and the electric control regulating valve are simultaneously electrically connected with the controller; the power supply is used for supplying power to all electric components in the device.
And the cavities on two sides of the piston in the cylinder body of the buffer hydraulic cylinder are respectively provided with a buffer spring.
The alarm system and the display system are installed on a central control platform of a tractor cab.
The power supply adopts a storage battery of the tractor.
The overload protection device for the rodless aircraft tractor provided by the invention has the following advantages:
1. the invention adopts the buffer hydraulic cylinder, can buffer variable traction load under special conditions, protects the airplane and the tractor from being damaged, prevents overload, avoids the fatigue life shortening of the structural member of the undercarriage of the airplane, and further reduces the operation cost of an airline company.
2. The four buffer hydraulic cylinders are adopted, so that the buffer force is stable, and the comfort of a tractor driver and an airplane passenger can be improved. Four buffering pneumatic cylinders parallel distribution can not destroy the control performance of tractor. The four buffer hydraulic cylinders have large buffer force and are particularly suitable for dealing with the object with large mass such as an airplane.
3. The invention adopts the detection signals of an acceleration sensor, a speed sensor and a hydraulic pressure sensor as the input signals of the controller. Because the input signal of the controller is less, the controller is favorable for fast processing and fast reacting, and related parts and personnel are protected at the fastest speed.
4. The invention adopts four spatial slideways, can perfectly ensure the longitudinal parallel sliding of the sliding block, ensures that the buffer hydraulic cylinder only bears the axial force and ensures the reliability of the mechanism.
Drawings
Fig. 1 is a schematic diagram of the overload protection device for the rodless aircraft tractor provided by the invention.
Fig. 2 is a perspective view of the overload protection device for the rodless aircraft tractor according to the present invention.
Fig. 3 is a perspective view of a tractor frame in the overload protection device of the rodless aircraft tractor provided by the invention.
Fig. 4 is a perspective view of a sliding block structure in the overload protection device of the rodless aircraft tractor provided by the invention.
Detailed Description
The invention is further illustrated by the following examples and figures.
As shown in fig. 1-4, the overload protection device for a rodless aircraft tractor provided by the invention comprises a buffer device and a control system; the buffer device comprises four buffer hydraulic cylinders 2, a slide block 5, a slide block track 6 and four connecting rods 7; the slide block tracks 6 are formed along the sliding direction of the airplane or arranged on the inner surfaces of the two sides of the rear part of the upper frame 4 of the rodless airplane tractor; the slide block 5 is arranged at the rear part in the frame 4, the bosses 51 on the two side surfaces and the slide rods 52 on the two sides of the front end are respectively inserted into the corresponding positions of the slide block track 6, and the two side parts of the upper end and the lower end are respectively provided with a notch 53; the front part of the frame 4 is provided with a clamping and lifting mechanism 8; the circumferential surfaces of the front part and the rear part of the cylinder body of the buffer hydraulic cylinder 2 are respectively provided with an oil inlet and an oil outlet, and the interior of the cylinder body is divided into two chambers by a piston; the front ends of the four buffer hydraulic cylinders 2 are respectively fixed at four corners of the rear end surface of the frame 4, the hydraulic rod 1 forwards penetrates through the rear end plate of the frame 4 and then is hinged with the rear end of a connecting rod 7 through a notch 53 on the sliding block 5, and the front ends of the four connecting rods 7 are simultaneously hinged on the rear end surface of the clamping and lifting mechanism 8; the notch 53 is provided to ensure that when the slide block 5 rotates in a small range, the rotation is not transmitted to the buffer hydraulic cylinder 2, so that the buffer hydraulic cylinder 2 is not affected by bending moment, and the safety and reliability are realized; the control system comprises a speed sensor 10, a hydraulic pressure sensor 11, an acceleration sensor 12, a position sensor 13, a controller 14, a power supply 15, an alarm system 16, a display system 17 and an electric control regulating valve 18; the electric control regulating valve 18 is respectively connected with two oil inlet and outlet ports on the cylinder body of the buffer hydraulic cylinder 2 through a high-pressure hydraulic pipeline; the speed sensor 10 and the acceleration sensor 12 are mounted on the frame 4; the hydraulic pressure sensor 11 is arranged at an oil inlet and an oil outlet on the cylinder body; the position sensor 13 is arranged on the slide block 5; the speed sensor 10, the hydraulic pressure sensor 11, the acceleration sensor 12, the position sensor 13, the alarm system 16, the display system 17 and the electric control regulating valve 18 are simultaneously electrically connected with the controller 14; the power supply 15 is used to supply power to the various electrical components of the device.
And a buffer spring 3 is respectively arranged in the cavities at two sides of the piston in the cylinder body of the buffer hydraulic cylinder 2 so as to increase the buffer force.
The alarm system 16 and the display system 17 are installed on a central control platform of a tractor cab.
The power supply 15 adopts a storage battery of the tractor.
The working principle of the rodless aircraft tractor overload protection device provided by the invention is explained as follows: firstly, the nose landing gear 9 of the airplane is clamped and lifted by the clamping and lifting mechanism 8 under the operation of a rodless airplane tractor driver, and the two ends of the four connecting rods 7 on the device are respectively hinged with the clamping and lifting mechanism 8 and the sliding block 5, so that the nose landing gear 9 of the airplane can be ensured to freely incline.
In the process of pushing or dragging the airplane by using the tractor, a speed signal and an acceleration signal of the tractor, oil pressure signals of two cavities of a cylinder body and a position signal of a sliding block 5 are respectively detected by using a speed sensor 10, an acceleration sensor 12, a hydraulic pressure sensor 11 and a position sensor 13 and then transmitted to a controller 14; the controller 14 processes the signals and controls the display system 17 to display the speed and the acceleration of the tractor, the pressure of the buffer hydraulic cylinder 2 and the position data of the slide block 5 for the driver to refer when driving the tractor. If the value detected by one of the sensors exceeds its set value, the alarm system 16 sends an alarm signal under the control of the controller 14 to inform the tractor driver of safe driving.
When the tractor is stationary, the electronically controlled regulating valve 18 is in a closed state; when the towing vehicle starts to push or drag the airplane, if the acceleration of the towing vehicle is smaller at the moment, the electric control regulating valve 18 is in a closed state to ensure enough traction force, and meanwhile, the comfort of a towing vehicle driver and an airplane passenger cannot be reduced due to the addition of the buffer device; when the acceleration detected by the acceleration sensor 12 is too large or the speed detected by the speed sensor 10 exceeds 2Km/h, the electrically controlled regulating valve 18 is opened under the control of the controller 14, hydraulic oil flows into the cavity on one side of the cylinder body from a certain oil inlet and outlet, so that the piston and the piston rod are pushed to move backwards or forwards, and the opening of the electrically controlled regulating valve 18 is continuously increased along with the increase of the speed of the tractor so as to increase the buffer capacity.
When the buffer hydraulic rod 1 and the piston move to compress the hydraulic oil, if the moving position is within the range of +/-100 mm, the buffer hydraulic cylinder 2 also has a buffer function, and is reset in the running process of the tractor, and the reset acceleration is not more than 0.01m/s2. If the moving position of the buffer hydraulic rod 1 exceeds the range of +/-100 mm, the buffer function of the buffer hydraulic cylinder 2 cannot be fully exerted, at the moment, an alarm signal is sent to a driver through the alarm system 16 under the control of the controller 14 to remind the tractor driver of driving stably, the buffer hydraulic cylinder 2 starts to reset, and the alarm is stopped after the buffer hydraulic cylinder is reset to the range of +/-100 mm.
When buffering hydraulic stem 1 resets, if position sensor 13 detects that the position of slider 5 is not when the intermediate position of buffering hydraulic stem 1 is 0 position, only when the tractor traveles or breaks away from the back with the tractor, automatically controlled governing valve 18 just can open, makes buffering hydraulic stem 1 get back to 0 position to guarantee that buffering pneumatic cylinder 2 has perfect buffer function. When the tractor runs stably, the reset acceleration of the buffer hydraulic rod 1 is not more than 0.01m/s2(ii) a When the tractor is disengaged from the nose landing gear 9 of the aircraft, the reset acceleration is not more than 0.1m/s2。
Claims (4)
1. The utility model provides a no pole formula aircraft tractor overload protection device which characterized in that: the overload protection device of the rodless aircraft tractor comprises a buffer device and a control system; the buffer device comprises four buffer hydraulic cylinders (2), a slide block (5), a slide block track (6) and four connecting rods (7); the sliding block tracks (6) are formed along the sliding direction of the airplane or arranged on the inner surfaces of the two sides of the rear part of the upper frame (4) of the rodless airplane tractor; the sliding block (5) is arranged at the inner rear part of the frame (4), the bosses (51) on the two side surfaces and the sliding rods (52) on the two side surfaces of the front end are respectively inserted into corresponding positions of the sliding block track (6), and the two side parts of the upper end and the lower end are respectively provided with a notch (53); the front part of the frame (4) is provided with a clamping and lifting mechanism (8); the circumferential surfaces of the front part and the rear part of the cylinder body of the buffer hydraulic cylinder (2) are respectively provided with an oil inlet and an oil outlet, and the interior of the cylinder body is divided into two chambers by a piston; the front ends of the cylinder bodies of the four buffer hydraulic cylinders (2) are respectively fixed at four corners of the rear end surface of the frame (4), the hydraulic rod (1) forwards penetrates through the rear end plate of the frame (4) and then is hinged with the rear end of a connecting rod (7) through a notch (53) in the sliding block (5), and the front ends of the four connecting rods (7) are simultaneously hinged on the rear end surface of the clamping and lifting mechanism (8); the control system comprises a speed sensor (10), a hydraulic pressure sensor (11), an acceleration sensor (12), a position sensor (13), a controller (14), a power supply (15), an alarm system (16), a display system (17) and an electric control regulating valve (18); the electric control regulating valve (18) is respectively connected with two oil inlets and two oil outlets on the cylinder body of the buffer hydraulic cylinder (2) through a high-pressure hydraulic pipeline; the speed sensor (10) and the acceleration sensor (12) are arranged on the frame (4); the hydraulic pressure sensor (11) is arranged at an oil inlet and an oil outlet on the cylinder body; the position sensor (13) is arranged on the sliding block (5); the speed sensor (10), the hydraulic pressure sensor (11), the acceleration sensor (12), the position sensor (13), the alarm system (16), the display system (17) and the electric control regulating valve (18) are simultaneously electrically connected with the controller (14); the power supply (15) is used for supplying power to all electric components in the rodless aircraft tractor overload protection device.
2. The rodless aircraft tow truck overload protection device of claim 1, wherein: and a buffer spring (3) is respectively arranged in the cavities at the two sides of the piston in the cylinder body of the buffer hydraulic cylinder (2).
3. The rodless aircraft tow truck overload protection device of claim 1, wherein: the alarm system (16) and the display system (17) are installed on a central control platform of a tractor cab.
4. The rodless aircraft tow truck overload protection device of claim 1, wherein: the power supply (15) adopts a storage battery of the tractor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810604427.0A CN108545211B (en) | 2018-06-13 | 2018-06-13 | Rodless aircraft tractor overload protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810604427.0A CN108545211B (en) | 2018-06-13 | 2018-06-13 | Rodless aircraft tractor overload protection device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108545211A CN108545211A (en) | 2018-09-18 |
| CN108545211B true CN108545211B (en) | 2020-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810604427.0A Active CN108545211B (en) | 2018-06-13 | 2018-06-13 | Rodless aircraft tractor overload protection device |
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| Country | Link |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0788971A2 (en) * | 1995-09-27 | 1997-08-13 | MAN Gutehoffnungshütte Aktiengesellschaft | Overload protection for an aircraft nose landing gear attached to an aircraft tractor without a towbar |
| FR2967400B1 (en) * | 2010-11-16 | 2013-08-16 | Jacques Blatt | ELECTRICAL TRACTOR RADIO CONTROL FOR TOURISM AIRCRAFT |
| CN206202719U (en) * | 2016-09-23 | 2017-05-31 | 深圳市劲拓自动化设备股份有限公司 | A kind of novel electric omnidirectional non-intrusive method |
| CN107054681A (en) * | 2017-02-28 | 2017-08-18 | 天津航天机电设备研究所 | Non-rod aircraft tractor |
| CN108001703A (en) * | 2017-11-30 | 2018-05-08 | 江西洪都航空工业集团有限责任公司 | A kind of linkage of towing aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9056686B2 (en) * | 2012-08-14 | 2015-06-16 | Anthony Y. Chan | Aircraft tug vehicle |
-
2018
- 2018-06-13 CN CN201810604427.0A patent/CN108545211B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0788971A2 (en) * | 1995-09-27 | 1997-08-13 | MAN Gutehoffnungshütte Aktiengesellschaft | Overload protection for an aircraft nose landing gear attached to an aircraft tractor without a towbar |
| FR2967400B1 (en) * | 2010-11-16 | 2013-08-16 | Jacques Blatt | ELECTRICAL TRACTOR RADIO CONTROL FOR TOURISM AIRCRAFT |
| CN206202719U (en) * | 2016-09-23 | 2017-05-31 | 深圳市劲拓自动化设备股份有限公司 | A kind of novel electric omnidirectional non-intrusive method |
| CN107054681A (en) * | 2017-02-28 | 2017-08-18 | 天津航天机电设备研究所 | Non-rod aircraft tractor |
| CN108001703A (en) * | 2017-11-30 | 2018-05-08 | 江西洪都航空工业集团有限责任公司 | A kind of linkage of towing aircraft |
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| Publication number | Publication date |
|---|---|
| CN108545211A (en) | 2018-09-18 |
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