CN102381490B - Transition steering device for detecting rodless aircraft tractor - Google Patents
Transition steering device for detecting rodless aircraft tractor Download PDFInfo
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- CN102381490B CN102381490B CN2011102861124A CN201110286112A CN102381490B CN 102381490 B CN102381490 B CN 102381490B CN 2011102861124 A CN2011102861124 A CN 2011102861124A CN 201110286112 A CN201110286112 A CN 201110286112A CN 102381490 B CN102381490 B CN 102381490B
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Abstract
The invention discloses a transition steering device for detecting a rodless aircraft tractor, which is characterized in that the transition steering device is provided with a simulation undercarriage, aircraft testing wheels, a rotation mandrel, a locating shaft sleeve, a rotation torque-measuring bracket, a rotation locating pin shaft, an over-torque locating bracket, over-torque locating pin shafts, a torque sensor and an angle sensor, wherein one end of the simulation undercarriage is connected with a loading platform; a locating groove is arranged at the other end of the simulation undercarriage; the locating shaft sleeve is arranged in the locating groove and is connected with the simulation undercarriage; the rotation mandrel penetrates through the locating shaft sleeve; the upper end of the rotation mandrel is connected with the torque sensor; the lower end of the rotation mandrel is connected with the aircraft testing wheels through the rotation locating pin shaft; the lower end of the rotation torque-measuring bracket is connected with the torque sensor; the upper end of the rotation torque-measuring bracket is connected with the angle sensor; the over-torque locating pin shafts are respectively arranged at two sides of the rotation torque-measuring bracket and are fixedly connected with the simulation undercarriage through the over-torque locating bracket; the torque sensor and the angle sensor are respectively connected with a controller, therefore, the defects in design and production of the rodless aircraft tractor are reduced.
Description
Technical field
The present invention relates to Ground facility technology field, specifically a kind of detection non-rod aircraft tractor oversteer device.
Background technology
Be accompanied by more and more flourishing at present aircraft industry, non-rod aircraft tractor is owing to greatly save labour turnover and the advantage of use cost, be subjected to the favor of vast airport and airline company, because non-rod aircraft tractor directly contacts with the aircraft nose-gear, the torque peak that the nose-gear of aircraft can bear and steering angle have strict requirement, so non-rod aircraft tractor is when towing aircraft, torque peak and steering angle to the aircraft nose-gear have strict design standard, and the test problems that solves non-rod aircraft tractor design performance parameter is necessary.China is at aspects such as non-rod aircraft tractor design and uses, lag far behind the countries such as American-European, the oversteer function that very large restriction is not have the equipment of simulated aircraft nose-gear to test non-rod aircraft tractor, whether the non-rod aircraft tractor of simultaneously external import satisfies the aircraft parameters requires also can't determine, can only wait for information the parameter of non-rod aircraft tractor manufacturer fully, even to this day, still there is not like product to put on market both at home and abroad, best auxiliary facility was aircraft when non-rod aircraft tractor detected test, the non-rod aircraft tractor of common a kind of model can carry out towage to several even tens kinds of aircrafts, so the price of utilizing aircraft to carry out the oversteer test is very expensive.According to the international standard content, the process of the test of non-rod aircraft tractor does not allow flight test vehicle to make a service test, and, the shortcoming of existing non-rod aircraft tractor oversteer safety guard-safeguard performance scheme: 1, in the aircraft steering procedure, because the aircraft nose-gear has the requirement of steering locking angle degree, but non-rod aircraft tractor does not have relevant warning function, if surpass this angle during without bar tractor truck towing aircraft, to cause rigid injury to the aircraft nose-gear, or even nose-gear is scrapped directly; 2, because the moment of torsion that the aircraft nose-gear can bear also has strict demand, in the non-rod aircraft tractor distraction procedure, surpass this designing requirement, can produce injury to the aircraft nose-gear equally.
Summary of the invention
The objective of the invention is to solve above-mentioned the deficiencies in the prior art, a kind of design production defective that reduces non-rod aircraft tractor is provided, satisfy the parameter request that aircraft producer proposes, eliminate various potential safety hazards, reduce the loss of airport and airline company, improve the detectability of non-rod aircraft tractor in the industry, the detection non-rod aircraft tractor oversteer device whether the assessment non-rod aircraft tractor satisfies actual operation requirements.
The technical solution adopted for the present invention to solve the technical problems is:
A kind of detection non-rod aircraft tractor oversteer device; it is characterized in that being provided with the simulation alighting gear; the aircraft testing wheel; the rotation mandrel; positioning shaft sleeve; rotation is surveyed and is turned round support; the rotation alignment pin; cross and turn round locating support; cross and turn round alignment pin; torque sensor and angular transducer; simulation alighting gear one end is connected with bearing platform; the other end is provided with detent; be provided with positioning shaft sleeve in the detent; positioning shaft sleeve is connected with the simulation alighting gear; the rotation mandrel passes positioning shaft sleeve; the upper end is connected with torque sensor; the lower end is connected with the aircraft testing wheel through the rotation alignment pin; be beneficial to simulate dissimilar undercarriages and change dissimilar testing wheels; the rotation survey is turned round the support lower end and is connected with torque sensor; the upper end is connected with angular transducer; rotation is surveyed and to be turned round the support both sides and be respectively equipped with and turn round alignment pin; cross and turn round alignment pin through turning round locating support and simulating alighting gear and captive joint; torque sensor is connected with controller respectively with angular transducer; be beneficial to detect and the steering angle detection by the moment of torsion that adopts aircraft simulation alighting gear; realization detects non-rod aircraft tractor transition steering safety protective value; in testing process; when the steering locking angle that reaches simulated aircraft when the steering angle of aircraft testing wheel is spent; the rotation survey is turned round support and is excessively turned round the alignment pin location; at this moment; the two ends of torque sensor form relative torsion; angular transducer and torque sensor pass to controller with information; calculate the angle between simulation alighting gear and the non-rod aircraft tractor after controller is compared by the data of storage inside, thereby the angle of finishing non-rod aircraft tractor detects and the over-torque detection.
The present invention can be provided with master program(me) controller at the simulation alighting gear; be provided with storage card and calculation procedure in the master program(me) controller; so that the profile scanner that is fixed on the non-rod aircraft tractor sends to master program(me) controller with the profilograph that scans; master program(me) controller draws the angle of simulating this moment between alighting gear and the non-rod aircraft tractor behind the comparing by its storage inside again; if angle [alpha] exceeds the permissible value of aircraft simulation alighting gear; non-rod aircraft tractor must be reported to the police and protection system work; thereby finish the oversteer protection that detects non-rod aircraft tractor, prevent that non-rod aircraft tractor from damaging the aircraft nose-gear.
The present invention can be provided with tractive force sensor at the simulation alighting gear, tractive force sensor is hinged through pipe link and positioning shaft sleeve below, both sides, positioning shaft sleeve top respectively through hinge be fixed on the bearing of simulating on the alighting gear and be connected, so that the present invention is in the constant situation of main body, can change multiple aircraft testing wheel, to simulate multiple aircraft nose-gear and test without the load of bar tractor truck.
The present invention can be provided with stay bearing plate in the positioning inner sleeve upper end, captives joint with angular transducer in the stay bearing plate upper end, and captiveing joint with positioning inner sleeve in the lower end, is beneficial to the fixed angle sensor, reaches detection and act on accurately.
The present invention is owing to adopt said structure; can realize the mistake of non-rod aircraft tractor is turned round; cross and turn; the detection of the design parameterss such as tractive force; simulate the weight of multiple aircraft; inertia; the technical parameters such as nose-gear weight; check is without the towability of bar tractor truck; jacking capacity; the safety guard-safeguard performance; on a check implement, multiple aircraft is carried out the performance perameter checking; significantly reduced the experimentation cost of non-rod aircraft tractor manufacturer; strengthen the product test ability of tractor truck manufacturer; reduce non-rod aircraft tractor in design; potential various defectives in the production process; accident potential was eliminated in the primary stage; reduce the economic loss of airline company; retrieve numerous passengers' valuable life; and; when safety misadventure occurring; can provide full and accurate accurately data for technology and experimenter, eliminate non-rod aircraft tractor manufacturer can't verify performance perameter after producing tractor truck technical bottleneck.
Description of drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the left view of Fig. 1.
Fig. 4 is perspective view of the present invention.
Fig. 5 is the structural representation of the embodiment of the invention.
Fig. 6 is the structural representation of oversteer embodiment of the present invention.
Reference numeral: 1: angular transducer; 2: torque sensor; 3: cross and turn round locating support; 4: the rotation mandrel; 5: the test opinion; 6: the rotation alignment pin; 7: cross and turn round alignment pin; 8: the simulation alighting gear; 9: rotation is surveyed and is turned round support; 10: profile scanner; 11: the aircraft profile; 12: master program(me) controller; 13: non-rod aircraft tractor; 14: positioning shaft sleeve; 15: detent; 16: tractive force sensor; 17: stay bearing plate.
The specific embodiment
The present invention is further described below in conjunction with accompanying drawing:
As shown in drawings; a kind of detection non-rod aircraft tractor oversteer device; it is characterized in that being provided with simulation alighting gear 8; aircraft testing wheel 5; rotation mandrel 4; positioning shaft sleeve 14; rotation is surveyed and is turned round support 9; rotation alignment pin 6; cross and turn round locating support 3; cross and turn round alignment pin 7; torque sensor 2 and angular transducer 1; simulation alighting gear 8 one ends are connected with bearing platform; the other end is provided with detent 15; be provided with positioning shaft sleeve 14 in the detent 15; positioning shaft sleeve 14 is connected with simulation alighting gear 8; rotation mandrel 4 passes positioning shaft sleeve 14; the upper end is connected with torque sensor 2; the lower end is connected with aircraft testing wheel 5 through rotation alignment pin 6; be beneficial to simulate dissimilar undercarriages and change dissimilar aircraft testing wheels 5; the rotation survey is turned round support 9 lower ends and is connected with torque sensor 2; the upper end is connected with angular transducer 1; rotation is surveyed and to be turned round support 9 both sides and be respectively equipped with and turn round alignment pin 7; cross turn round alignment pin 7 through turning round locating support 3 with the simulation alighting gear 8 captive joint; torque sensor 2 is connected with controller respectively with angular transducer 1; be beneficial to detect and the steering angle detection by the moment of torsion that adopts aircraft simulation alighting gear 8; realization detects non-rod aircraft tractor transition steering safety protective value; in testing process; when the steering locking angle that reaches simulated aircraft when the steering angle of aircraft testing wheel is spent; rotation is surveyed and to be turned round support 9 and crossed and turn round alignment pin 7 location; at this moment; the two ends of torque sensor 2 form relative torsion; angular transducer 1 and torque sensor 2 pass to controller with information; calculate the angle between simulation alighting gear 8 and the non-rod aircraft tractor 13 after controller is compared by the data of storage inside, thereby the angle of finishing non-rod aircraft tractor 13 detects and the over-torque detection.
The present invention can be provided with master program(me) controller 12 at simulation alighting gear 8; be provided with storage card and calculation procedure in the master program(me) controller 12; so that the profile scanner 10 that is fixed on the non-rod aircraft tractor sends to master program(me) controller 12 with the profilograph that scans; master program(me) controller 12 draw behind the comparing by its storage inside again this moment aircraft simulation alighting gear 8 and non-rod aircraft tractor 13 between angle; if angle [alpha] exceeds the permissible value of aircraft simulation alighting gear 8; non-rod aircraft tractor 13 must be reported to the police and protection system work; thereby finish the oversteer protection that detects non-rod aircraft tractor 13, prevent that 13 pairs of aircraft nose-gears of non-rod aircraft tractor from damaging.
The present invention can be provided with tractive force sensor 16 at simulation alighting gear 8, tractive force sensor 16 is hinged through pipe link and positioning shaft sleeve 14 belows, both sides, positioning shaft sleeve 14 top respectively through hinge be fixed on the bearing of simulation on the alighting gear 8 and be connected, so that the present invention is in the constant situation of main body, can change multiple aircraft testing wheel, to simulate multiple aircraft nose-gear and test without the load of bar tractor truck.
The present invention can be provided with stay bearing plate 17 in positioning shaft sleeve 14 upper ends, captives joint with angular transducer 1 in stay bearing plate 17 upper ends, and captiveing joint with positioning shaft sleeve 14 in the lower end, is beneficial to fixed angle sensor 1, reaches detection and act on accurately.
The present invention is when examinations, can profile scanner 10 be installed at non-rod aircraft tractor 13, the airplane skin assembly is installed on the simulation alighting gear 8, and non-rod aircraft tractor 13 is with after the nosewheel device docks, and profile scanner 10 just begins aircraft profile 11 is scanned.Different according to different aircraft weights; only need to change the requirement that testing wheel can satisfy the various aircrafts of simulation; when changing testing wheel; only need rotation alignment pin 6 is extracted; namely replaceable; handle master cock; make testing wheel 5 built on stilts; after non-rod aircraft tractor 13 holds up testing wheel 5; begin the simulation traction; forming steering angle between rotation mandrel 4 drive testing wheels 5 and the simulation alighting gear 8 detects by angular transducer 1; this moment, profile scanner 10 was with the profilograph that scans; angle and torque sensor 2 that angular transducer 1 detects the testing wheel rotation send to master program(me) controller 12 with the moment of torsion that detects; master program(me) controller 12 by and the comparing of its storage inside after draw angle between aircraft simulation alighting gear 8 and the non-rod aircraft tractor 13; when the steering locking angle that reaches simulated aircraft when steering angle is spent; rotation is surveyed and to be turned round support 9 and crossed and turn round alignment pin 7 location; this moment, the two ends of torque sensor 2 formed relative torsion; thereby finishing non-rod aircraft tractor 13 over-torque detects; at this moment, annunciator is reported to the police and protection system.
The present invention is owing to adopt said structure; can realize the mistake of non-rod aircraft tractor is turned round; cross and turn; the detection of the design parameterss such as tractive force; simulate the weight of multiple aircraft; inertia; the technical parameters such as nose-gear weight; check is without the towability of bar tractor truck; jacking capacity; the safety guard-safeguard performance; on a check implement, multiple aircraft is carried out the performance perameter checking; significantly reduced the experimentation cost of non-rod aircraft tractor manufacturer; strengthen the product test ability of tractor truck manufacturer; reduce non-rod aircraft tractor in design; potential various defectives in the production process; accident potential was eliminated in the primary stage; reduce the economic loss of airline company; retrieve numerous passengers' valuable life; and; when safety misadventure occurring; can provide full and accurate accurately data for technology and experimenter, eliminate non-rod aircraft tractor manufacturer can't verify performance perameter after producing tractor truck technical bottleneck.
Claims (4)
1. one kind is detected non-rod aircraft tractor oversteer device, it is characterized in that being provided with the simulation alighting gear, the aircraft testing wheel, the rotation mandrel, positioning shaft sleeve, rotation is surveyed and is turned round support, the rotation alignment pin, cross and turn round locating support, cross and turn round alignment pin, torque sensor and angular transducer, simulation alighting gear one end is connected with bearing platform, the other end is provided with detent, be provided with positioning shaft sleeve in the detent, positioning shaft sleeve is connected with the simulation alighting gear, the rotation mandrel passes positioning shaft sleeve, the upper end is connected with torque sensor, the lower end is connected with the aircraft testing wheel through the rotation alignment pin, the rotation survey is turned round the support lower end and is connected with torque sensor, the upper end is connected with angular transducer, rotation is surveyed and to be turned round the support both sides and be respectively equipped with and turn round alignment pin, cross and turn round alignment pin through turning round locating support and simulating alighting gear and captive joint, torque sensor is connected with controller respectively with angular transducer.
2. a kind of detection non-rod aircraft tractor oversteer device according to claim 1, it is characterized in that simulating alighting gear and be provided with tractive force sensor, tractive force sensor is hinged through pipe link and positioning shaft sleeve below, both sides, positioning shaft sleeve top respectively through hinge be fixed on the bearing of simulating on the alighting gear and be connected.
3. a kind of detection non-rod aircraft tractor oversteer device according to claim 1 is characterized in that the positioning inner sleeve upper end is provided with stay bearing plate, captives joint with angular transducer in the stay bearing plate upper end, captives joint with positioning inner sleeve in the lower end.
4. a kind of detection non-rod aircraft tractor oversteer device according to claim 1 is characterized in that simulating alighting gear and is provided with master program(me) controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102861124A CN102381490B (en) | 2011-09-24 | 2011-09-24 | Transition steering device for detecting rodless aircraft tractor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102861124A CN102381490B (en) | 2011-09-24 | 2011-09-24 | Transition steering device for detecting rodless aircraft tractor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102381490A CN102381490A (en) | 2012-03-21 |
| CN102381490B true CN102381490B (en) | 2013-03-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011102861124A Active CN102381490B (en) | 2011-09-24 | 2011-09-24 | Transition steering device for detecting rodless aircraft tractor |
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| CN (1) | CN102381490B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103085982A (en) * | 2012-12-11 | 2013-05-08 | 沈阳北方交通重工有限公司 | Device for protecting nose landing gear of rodless aircraft tractor |
| CN104071332B (en) * | 2013-08-07 | 2016-02-10 | 中科宇图天下科技有限公司 | 3 guide piecees and apply the method for this device after unmanned plane |
| CN112455711A (en) * | 2021-01-12 | 2021-03-09 | 新乡平原航空技术工程有限公司 | Aircraft tractor |
| CN114323694B (en) * | 2021-12-31 | 2022-11-15 | 上海交通大学 | Principle verification system for traction movement control performance of traction sliding operation mode |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4139027B2 (en) * | 1999-11-18 | 2008-08-27 | 株式会社東海理化電機製作所 | Turn signal canceling device |
| JP4261731B2 (en) * | 2000-04-26 | 2009-04-30 | 株式会社小松製作所 | Warning device for aircraft towing vehicle |
| EP1464577A1 (en) * | 2003-04-03 | 2004-10-06 | TLD Europe SA | Torque controlling device for the gripping system of an aircraft towing vehicle |
| GB0606087D0 (en) * | 2006-03-27 | 2006-05-03 | Airbus Uk Ltd | Aircraft steering angle warning system |
| CN201907558U (en) * | 2010-08-19 | 2011-07-27 | 天津奥瑞克科技有限公司 | Turning direction correcting control device of airplane tractor |
| CN202226069U (en) * | 2011-09-24 | 2012-05-23 | 威海广泰空港设备股份有限公司 | Device for detecting excessive turning of rodless airplane tractor |
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- 2011-09-24 CN CN2011102861124A patent/CN102381490B/en active Active
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| CN102381490A (en) | 2012-03-21 |
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