CN202243127U - Test vehicle for testing rodless aircraft tractor - Google Patents
Test vehicle for testing rodless aircraft tractor Download PDFInfo
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- CN202243127U CN202243127U CN2011203603996U CN201120360399U CN202243127U CN 202243127 U CN202243127 U CN 202243127U CN 2011203603996 U CN2011203603996 U CN 2011203603996U CN 201120360399 U CN201120360399 U CN 201120360399U CN 202243127 U CN202243127 U CN 202243127U
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- bearing platform
- aircraft tractor
- control system
- aircraft
- alighting gear
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Abstract
The utility model relates to the technical field of aeronautical ground facilities, in particular to a test vehicle for testing a rodless aircraft tractor. The test vehicle is characterized by comprising a bearing platform; a driving cab, a power control system, a hydraulic control system and an electric control system are arranged on the bearing platform; a counter weight assembly is arranged at the upper end of the bearing platform; a supporting wheel set is arranged at the lower end of the bearing platform; and a nosewheel device is arranged at the front end of the bearing platform. Due to the adoption of the structure, the test to the design parameters such as excessive torsion, excessive rotation, traction and the like of the rodless aircraft tractor can be realized, the technical parameters such as the weight, the inertia, the nose gear weight and the like of various aircrafts are simulated, the tractive capability, the hoisting capability and the safety protection performance of the rodless aircraft tractor are tested, performance parameters of various aircrafts are verified on a testing device, various potential defects during the design and production process of the rodless aircraft tractor are reduced, the product test ability of tractor manufacturers is enhanced, and various potential safety hazards are eliminated for airports and airline companies.
Description
Technical field
The utility model relates to aviation surface facility technical field, and detailed saying so is used for the simulated aircraft partial parameters and non-rod aircraft tractor is carried out the test carriage that each item design parameters is tested.
Background technology
As everyone knows, aircraft towing producer is numerous both at home and abroad at present, and the aircraft towing model of its production is too numerous to enumerate especially.The bar tractor truck is arranged owing to aircraft is drawn through draw bar, direct contact aircraft nose-gear not, so detect require looser relatively.And do not have bar tractor truck and aircraft nose-gear direct contact, so need higher reliability and aircraft comformability.This has just proposed exacting requirements to no bar tractor truck each item design parameters.
At present; The model of the employed non-rod aircraft tractor in Civil Aviation Airport is more and more, and tonnage is also increasing, and its function also becomes increasingly complex; But it is very not in place that its each item detects; Can only describe its function and performance parameters by former manufacturer, can't provide files and reports and data report with cogency, just there are many uncertain potential safety hazards in this.If the untimely elimination of these potential safety hazards not only can cause economic loss to tractor truck manufacturer, also can cause damage, even can endanger the valuable life of passenger airport and airline company, generally speaking consequence is very serious.Best auxiliary facility was an aircraft when non-rod aircraft tractor made an experiment, and was very expensive but utilize the price of aircraft testing, and aircraft type is also a lot, and the risk that in process of the test, exists is also very big, and airline company can not provide aircraft to use as test yet; According to international industry standard, non-rod aircraft tractor is to ban use of aircraft as subjects in process of the test, and above factor causes non-rod aircraft tractor manufacturer to be difficult to vehicle is carried out detailed technical identification.Therefore, supporting test carriage is the main bottleneck of non-rod aircraft tractor development.This equipment can be simulated technical parameters such as the weight, inertia, nose-gear weight of multiple aircraft; Check non-rod aircraft tractor towability, the jacking capacity of equipment, safety guard-safeguard performance; A test carriage can be simulated multiple aircraft parameter, has significantly reduced design cost and experimentation cost like this.Various situation more than comprehensive; We are when producing increasing non-rod aircraft tractor; Also to guarantee the safety and the reliability of non-rod aircraft tractor, be necessary thus test carriage is designed and developed, so that the non-rod aircraft tractor of producing from now on carries out the performance perameter test on test carriage; And provide corresponding files and reports; Reduce non-rod aircraft tractor potential various defectives in design, production process,, strengthen the product test ability of tractor truck manufacturer for technological and testing crew provide full and accurate accurate data.
Summary of the invention
The purpose of the utility model is the deficiency that solves above-mentioned prior art; Provide a kind of novel structure, easy to operate, through the simulation multiple aircraft state; No bar tractor truck was realized that the various design parameterss of turning round, cross commentaries on classics and tractive force carried out detection validation, the test carriage that is used to detect non-rod aircraft tractor that data are reliable, advanced in performance, safe, cost is low, easy to detect.
The technical scheme that the utility model technical solution problem is adopted is:
Be used to detect the test carriage of non-rod aircraft tractor, it is characterized in that being provided with bearing platform, bearing platform is provided with operator's compartment, power control system; Hydraulic control system and electric control system, the bearing platform upper end is provided with the counterweight assembly, and the lower end is provided with the support wheels; Front end is provided with the nosewheel device, and bearing platform is to be formed by stull in metal framework and the metal framework and the mutual cross fixation of vertical support, and the counterweight assembly is to be plugged fixedly by the unit clump weight to form; Require to peg graft according to the load of different simulated aircrafts when being beneficial to test, the nosewheel device comprises that simulation alighting gear, aircraft testing wheel, rotation mandrel, location axle sleeve, rotation are surveyed to be turned round support, positioning of rotating bearing pin, crosses and turn round locating support, cross and turn round alignment pin, torque sensor and angular transducer, and simulation alighting gear one end is connected with bearing platform; The other end is provided with detent, is provided with the location axle sleeve in the detent, and the location axle sleeve is connected with the simulation alighting gear; The rotation mandrel passes the location axle sleeve, and the upper end is connected with torque sensor, and the lower end is connected with the aircraft testing wheel through the positioning of rotating bearing pin; Be beneficial to simulate dissimilar undercarriages and change dissimilar testing wheels; Rotation is surveyed and to be turned round the support lower end and be connected with torque sensor, and the upper end is connected with angular transducer, rotates survey and turns round the support both sides and be respectively equipped with and turn round alignment pin; Cross turn round alignment pin through turning round locating support with the simulation alighting gear captive joint; Torque sensor is connected with electric control system respectively with angular transducer, is beneficial to detect and the steering angle detection through the moment of torsion that adopts aircraft simulation alighting gear, realizes non-rod aircraft tractor oversteer safety guard-safeguard performance is detected; In testing process; When the steering locking angle that reaches simulated aircraft when the steering angle of aircraft testing wheel was spent, rotation was surveyed and is turned round support and crossed and turned round the alignment pin location, at this moment; The two ends of torque sensor form relatively to be reversed, thereby angular detection and the over-torque of accomplishing non-rod aircraft tractor detect.
Operator's compartment in the utility model is captiveed joint with the bearing platform lower end of simulation alighting gear one side, detects with convenient the driving.
The utility model can be provided with summary display screen, engine data indicator gauge, charging water gauge, master cock and vehicle data read-out in operator's compartment; The summary display screen is used to show non-rod aircraft tractor each item data parameters of being tested, and has storage and output function, and the vehicle data read-out is used to show test carriage height, analogue machine shape parameter; Can set according to experimental subjects; Be provided with the processing module, display module, memory module and the print module that are used to detect data in the electric control system, the simulation alighting gear is provided with master program(me) controller, is 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 again through draw after the data comparison of memory module with itself and storage inside this moment the aircraft nose-gear and non-rod aircraft tractor between angle, treated module is handled with display module, through summary display shield, vehicle data read-out and vehicle data read-out show; Handle the back output print through print module; When safety misadventure occurring, also can provide full and accurate technical data, for the judgement of problem provides important basis; Reach effect, prevent that non-rod aircraft tractor from damaging the aircraft nose-gear each item Data Detection.
The utility model can be provided with tractive force sensor on the simulation alighting gear; Tractive force sensor is hinged through pipe link and axle sleeve below, location; Both sides, fix shaft cover top respectively through hinge be fixed on the bearing of simulating on the alighting gear and be connected; So that the utility model under main body unmodified situation, can be changed multiple aircraft testing wheel, to simulate the load of multiple aircraft nose-gear and the no bar tractor truck of test.
The utility model can be provided with weight adjustment device on bearing platform, it comprises guide rail, hydraulic actuating cylinder, roller and roller shaft, and bearing platform is provided with guide rail and hydraulic actuating cylinder; Roll with guide rail through roller and be connected in the roller shaft two ends, the counterweight assembly is fixed on the roller shaft through pallet, and hydraulic actuating cylinder one end is connected with bearing platform; The other end is connected with pallet, because dissimilar aircrafts, it varies in weight; Also there are a lot of differences in the weight of its testing wheel; Therefore can vertically move through before and after the Driven by Hydraulic Cylinder counterweight assembly, the weight of preceding nosewheel is adjusted, reach the purpose of accurate simulation.
The utility model can be provided with running brake on the support wheels, be beneficial to can't simulate under the situation of large aircraft in the test carriage load-carrying, tire is implemented plugging power, thereby increase tractive load, reaches the purpose of little tonnage simulation large aircraft tonnage.
The utility model can be provided with automatic height-regulating device on the support wheels; It comprises footstock, up-down fluid cylinder, goes up toggle and following toggle; Last toggle is captiveed joint with footstock, and following toggle one end and last toggle are hinged, and the other end is captiveed joint with the support wheels; Up-down fluid cylinder one end and last toggle are hinged, and the other end is hinged with following toggle.
The utility model can be provided with stay bearing plate in the fix shaft set upper side, captives joint with angular transducer in the stay bearing plate upper end, and captiveing joint with the location axle sleeve in the lower end, is beneficial to the fixed angle sensor, reaches and detect purpose accurately.
The utility model can be provided with annunciator, and annunciator is connected with master program(me) controller, is beneficial to the protection system normal operation, and protection detects the non-rod aircraft tractor transition and turns to situation, prevents that non-rod aircraft tractor from damaging the aircraft nose-gear.
The utility model can realize that design parameterss such as commentaries on classics, tractive force are turned round, crossed to the mistake of non-rod aircraft tractor to be detected owing to adopt said structure, simulates the technical parameters such as weight, inertia, nose-gear weight of multiple aircraft; Check towability, jacking capacity, the safety guard-safeguard performance of no bar tractor truck; 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 potential various defectives in design, 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 with the experimenter full and accurate accurate data be provided for technology, eliminated non-rod aircraft tractor manufacturer can't verify performance perameter behind the production tractor truck technical bottleneck.
Description of drawings
Fig. 1 is the structural representation of the utility model.
Fig. 2 is the perspective view of the utility model.
Fig. 3 is the cutaway view of operator's compartment in the utility model.
Fig. 4 is the perspective view of nosewheel device in the utility model.
Fig. 5 is the front view of Fig. 4.
Fig. 6 is the birds-eye view of Fig. 5.
Fig. 7 is the left view of Fig. 5.
Fig. 8 is the partial view of Fig. 7.
Fig. 9 is the utility model analog detection scheme drawing.
Figure 10 is that the utility model simulation turns to the detection scheme drawing.
Figure 11 is the automatic height-regulating device scheme drawing that supports wheels in the utility model.
Figure 12 is the automatic height-regulating device perspective view that supports wheels in the utility model.
Reference numeral: 1: nosewheel device; 2: operator's compartment; 3: bearing platform; 4: support wheels; 5: running brake; 6: the counterweight assembly; 7: guide rail; 8: the summary display screen; 9: the engine data indicator gauge; 10: charging water gauge; 11: master cock; 12: the vehicle data read-out; 13: angular transducer; 14: rotation is surveyed and is turned round support; 15: cross and turn round locating support; 16: the simulation alighting gear; 17: the aircraft testing wheel; 18: the positioning of rotating bearing pin; 19: cross and turn round alignment pin; 20: tractive force sensor; 21: non-rod aircraft tractor; 22: detent; 23: torque sensor; 24: the rotation mandrel; 25: the location axle sleeve; 26: profile scanner; 27: airplane skin; 28: master program(me) controller; 29: the up-down fluid cylinder; 30: hinge; 31: following toggle; 32: hinge; 33: go up toggle; 34: hinge; 35: footstock; 36: stay bearing plate.
The specific embodiment:
Below in conjunction with accompanying drawing the utility model is further specified:
Shown in accompanying drawing, be used to detect the test carriage of non-rod aircraft tractor, it is characterized in that being provided with bearing platform 3; Bearing platform 3 is provided with operator's compartment 2, power control system, hydraulic control system and electric control system, and bearing platform 3 upper ends are provided with counterweight assembly 6; The lower end is provided with supports wheels 4, and the structure that supports wheels 4 is identical with prior art with annexation, and this does not give unnecessary details; Front end is provided with nosewheel device 1, and bearing platform 3 is to be formed by stull in metal framework and the metal framework and the mutual cross fixation of vertical support, and counterweight assembly 6 is to be plugged fixedly by the unit clump weight to form; Require to peg graft according to the load of different simulated aircrafts when being beneficial to test, nosewheel device 1 comprises that simulation alighting gear 16, aircraft testing wheel 17, rotation mandrel 24, location axle sleeve 25, rotation are surveyed to be turned round support 14, positioning of rotating bearing pin 18, crosses and turn round locating support 15, cross and turn round alignment pin 19, torque sensor 23 and angular transducer 13, and simulation alighting gear 16 1 ends are connected with bearing platform 3; The other end is provided with detent 22, is provided with location axle sleeve 25 in the detent 22, and location axle sleeve 25 is connected with simulation alighting gear 16; Rotation mandrel 24 passes location axle sleeve 25, and the upper end is connected with torque sensor 23, and the lower end is connected with aircraft testing wheel 17 through positioning of rotating bearing pin 18; Be beneficial to simulate dissimilar undercarriages and change dissimilar tires, the rotation survey is turned round support 14 lower ends and is connected with torque sensor 23, and the upper end is connected with angular transducer 13; Rotation is surveyed and to be turned round support 14 both sides and be respectively equipped with and turn round alignment pin 19; Cross and turn round alignment pin 19 and passed through and turn round locating support 15 and captive joint with simulation alighting gear 16, torque sensor 23 is connected with electric control system respectively with angular transducer 13, is beneficial to detect and the steering angle detection through the moment of torsion that adopts aircraft simulation alighting gear 16; 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 was spent, rotation was surveyed and is turned round support 14 and crossed and turn round alignment pin 19 location; At this moment; The two ends of torque sensor 23 form relatively to be reversed, thereby angular detection and the over-torque of accomplishing non-rod aircraft tractor detect the operator's compartment in the utility model, power control system; Hydraulic control system and electric control system can be prior art, and this does not give unnecessary details.
Operator's compartment 2 in the utility model is captiveed joint with bearing platform 3 lower ends of simulation alighting gear 16 1 sides, detects with convenient the driving.
The utility model can be provided with summary display screen 8, engine data indicator gauge 9, charging water gauge 10, master cock 11 and vehicle data read-out 12 in operator's compartment 2; Summary display screen 8 is used to show non-rod aircraft tractor each item data parameters of being tested; And have the storage and output function; Vehicle data read-out 12 is used to show test carriage height, analogue machine shape parameter; Can set according to experimental subjects, be provided with the processing module, display module, memory module and the print module that are used to detect data in the electric control system, simulation alighting gear 16 is provided with master program(me) controller 28; Be provided with storage card and calculation procedure in the master program(me) controller 28; So that the profile scanner that is fixed on the non-rod aircraft tractor sends to master program(me) controller 28 with the profilograph that scans, master program(me) controller 28 again through memory module draw after with the comparison of the data of its storage inside this moment the aircraft nose-gear and non-rod aircraft tractor between angle, treated module and display module processing; Show through summary display screen 8, reserves data display screen and vehicle data read-out 12; Handle the back output print through print module, reach effect, prevent that non-rod aircraft tractor from damaging the aircraft nose-gear each item Data Detection.
The utility model can be provided with tractive force sensor 20 on simulation alighting gear 16; Tractive force sensor 20 is hinged through pipe link and axle sleeve 25 belows, location; Both sides, axle sleeve 25 top, location respectively through hinge be fixed on the bearing of simulating on the alighting gear 16 and be connected; So that the utility model under main body unmodified situation, can be changed multiple aircraft testing wheel, to simulate the load of multiple aircraft nose-gear and the no bar tractor truck of test.
The utility model can be provided with weight adjustment device on bearing platform 3, it comprises guide rail 7, hydraulic actuating cylinder, roller and roller shaft, and bearing platform 3 is provided with guide rail 7 and hydraulic actuating cylinder; Roll with guide rail 7 through roller and be connected in the roller shaft two ends, counterweight assembly 6 is fixed on the roller shaft through pallet, and hydraulic actuating cylinder one end is connected with bearing platform 3; The other end is connected with pallet, because dissimilar aircrafts, it varies in weight; Also there are a lot of differences in the weight of its testing wheel; Therefore can vertically move through before and after the Driven by Hydraulic Cylinder counterweight assembly, the weight of preceding nosewheel is adjusted, reach simulation and act on accurately.
The utility model can be provided with running brake 5 on support wheels 4; The structure of running brake 5 is identical with prior art with annexation; This does not give unnecessary details, and is beneficial to can't simulate under the situation of large aircraft in the test carriage load-carrying, and tire is implemented plugging power; Thereby the increase tractive load reaches the purpose that little tonnage is simulated the large aircraft tonnage.
The utility model can be provided with automatic height-regulating device on support wheels 4; It comprises footstock 35, up-down fluid cylinder 29, goes up toggle 33 and following toggle 31; Last toggle 33 is captiveed joint with footstock 35, and following toggle 31 1 ends are hinged through hinge 32 and last toggle 33, and the other end is connected with the support wheels; Up-down fluid cylinder 29 1 ends are hinged through hinge 34 and last toggle 33, and the other end is hinged through hinge 30 and following toggle 31.
The utility model can be provided with stay bearing plate 36 in axle sleeve 25 upper ends, location, captives joint with angular transducer 13 in stay bearing plate 36 upper ends, and captiveing joint with location axle sleeve 25 in the lower end, is beneficial to fixed angle sensor 13, reaches detection and act on accurately.
The utility model can be provided with annunciator, and annunciator is connected with master program(me) controller 28, is beneficial to the protection system normal operation, and protection detects non-rod aircraft tractor oversteer situation, prevents that non-rod aircraft tractor from damaging the aircraft nose-gear.
The utility model is when implementing to detect; Profile scanner can be installed on non-rod aircraft tractor; The airplane skin assembly is installed on the simulation alighting gear 16, and non-rod aircraft tractor is with after nosewheel device 1 docks, and profile scanner 26 just begins airplane skin 27 profiles are scanned.Different according to different aircraft weights, only need to change the requirement that testing wheel can satisfy the various aircrafts of simulation, counterweight assembly 6 can carry out the manual work adjustment according to the weight of simulated aircraft; Chaufeur can be handled in operator's compartment, and the parameter of the height of test carriage, simulation type shows through vehicle data read-out 12, when changing testing wheel; Only need positioning of rotating bearing pin 18 is extracted; Handle master cock 11, hydraulic control system drives tractive force sensor 20, is beneficial to more transfer to flight testing wheel 17.After no bar tractor truck holds up aircraft testing wheel 17; Begin the simulation traction, owing to varying in weight of different aircrafts, also there is very big-difference in the weight of its aircraft testing wheel 17; At this moment can be through operating hydraulically operated control system; Driven by Hydraulic Cylinder counterweight assembly 6 on the bearing platform 3, the position that changes counterweight assembly 6 can be adjusted the weight of aircraft testing wheel 17, when the bigger aircraft of simulation; 5 pairs of running brake on the support wheels 4 capable of using support wheels 4 and brake; Rotation mandrel 24 drives and forms steering angle between aircraft testing wheels 17 and the simulation alighting gear 16 and detect through angular transducer, and this moment, profile scanner 26 sent to master program(me) controller 28 with the profilograph that scans, master program(me) controller 28 through and the data comparison of its storage inside after draw aircraft and simulate the angle between alighting gear 16 and the non-rod aircraft tractor; When the steering locking angle that reaches simulated aircraft when steering angle is spent; Rotation is surveyed and to be turned round support 14 and crossed and turn round alignment pin 19 location, and the two ends of torque sensor 23 formed relatively and reversed this moment, detected thereby accomplish the non-rod aircraft tractor over-torque.
The utility model is owing to adopt said structure, can realize detection that the mistake of non-rod aircraft tractor is turned round, crossed design parameterss such as commentaries on classics, tractive force, simulates the technical parameters such as weight, inertia, nose-gear weight of multiple aircraft; Check towability, jacking capacity, the safety guard-safeguard performance of no bar tractor truck; 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 potential various defectives in design, 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 with the experimenter full and accurate accurate data be provided for technology, eliminated non-rod aircraft tractor manufacturer can't verify performance perameter behind the production tractor truck technical bottleneck.
Claims (7)
1. be used to detect the test carriage of non-rod aircraft tractor, it is characterized in that being provided with bearing platform, bearing platform is provided with operator's compartment, power control system, hydraulic control system and electric control system; The bearing platform upper end is provided with the counterweight assembly; The lower end is provided with the support wheels, and front end is provided with the nosewheel device, and bearing platform is to be formed by stull in metal framework and the metal framework and the mutual cross fixation of vertical support; The counterweight assembly is to be plugged fixedly by the unit clump weight to form; The nosewheel device comprises that simulation alighting gear, aircraft testing wheel, rotation mandrel, location axle sleeve, rotation are surveyed to be turned round support, positioning of rotating bearing pin, crosses and turn round locating support, cross and turn round alignment pin, tractive force sensor, torque sensor and angular transducer, and simulation alighting gear one end is connected with bearing platform, and the other end is provided with detent; Be provided with the location axle sleeve in the detent; The location axle sleeve is connected with the simulation alighting gear, and the rotation mandrel passes the location axle sleeve, and the upper end is connected with torque sensor; The lower end is connected with the aircraft testing wheel through the positioning of rotating bearing pin; Rotation is surveyed and to be turned round the support lower end and be connected with torque sensor, and the upper end is connected with angular transducer, rotates survey and turns round the support both sides and be respectively equipped with and turn round alignment pin; Cross turn round alignment pin through turning round locating support with the simulation alighting gear captive joint, torque sensor is connected with electric control system respectively with angular transducer.
2. the test carriage that is used to detect non-rod aircraft tractor according to claim 1 is characterized in that operator's compartment captives joint with the bearing platform lower end of simulation alighting gear one side.
3. the test carriage that is used to detect non-rod aircraft tractor according to claim 1; It is characterized in that being provided with in the operator's compartment summary display screen, engine data indicator gauge, charging water gauge, master cock and vehicle data read-out; The summary display screen is used to show non-rod aircraft tractor each item data parameters of being tested; And have the storage and output function; The vehicle data read-out is used to show test carriage height, analogue machine shape parameter, can set according to experimental subjects, is provided with the processing module, display module, memory module and the print module that are used to detect data in the electric control system; The simulation alighting gear is provided with master program(me) controller, is provided with storage card and calculation procedure in the master program(me) controller.
4. the test carriage that is used to detect non-rod aircraft tractor 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 axle sleeve below, location, both sides, fix shaft cover top respectively through hinge be fixed on the bearing of simulating on the alighting gear and be connected.
5. the test carriage that is used to detect non-rod aircraft tractor according to claim 1; It is characterized in that bearing platform is provided with weight adjustment device, it comprises guide rail, hydraulic actuating cylinder, roller and roller shaft, and bearing platform is provided with guide rail and hydraulic actuating cylinder; Roll with guide rail through roller and be connected in the roller shaft two ends; The counterweight assembly is fixed on the roller shaft through pallet, and hydraulic actuating cylinder one end is connected with bearing platform, and the other end is connected with pallet.
6. the test carriage that is used to detect non-rod aircraft tractor according to claim 1 is characterized in that supporting wheels and is provided with running brake.
7. the test carriage that is used to detect non-rod aircraft tractor according to claim 1; It is characterized in that supporting wheels and be provided with automatic height-regulating device, it comprises footstock, up-down fluid cylinder, goes up toggle and following toggle, and last toggle is captiveed joint with footstock; Following toggle one end and last toggle are hinged; The other end is captiveed joint with the support wheels, and up-down fluid cylinder one end and last toggle are hinged, and the other end is hinged with following toggle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203603996U CN202243127U (en) | 2011-09-24 | 2011-09-24 | Test vehicle for testing rodless aircraft tractor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203603996U CN202243127U (en) | 2011-09-24 | 2011-09-24 | Test vehicle for testing rodless aircraft tractor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202243127U true CN202243127U (en) | 2012-05-30 |
Family
ID=46104415
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011203603996U Withdrawn - After Issue CN202243127U (en) | 2011-09-24 | 2011-09-24 | Test vehicle for testing rodless aircraft tractor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202243127U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102358223A (en) * | 2011-09-24 | 2012-02-22 | 威海广泰空港设备股份有限公司 | Test car used for testing rodless airplane tractor |
| CN104002862A (en) * | 2014-05-08 | 2014-08-27 | 中航飞机股份有限公司西安飞机分公司 | Bearing rotary towing mechanism for tool class transport vehicle |
| CN104614108A (en) * | 2015-01-12 | 2015-05-13 | 清华大学 | Device and method for measuring ground hauling load of aircraft |
| EP3330184A1 (en) * | 2016-12-02 | 2018-06-06 | The Boeing Company | Trailer-mounted mock landing gear |
| CN112356761A (en) * | 2020-09-22 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Aircraft transportation method based on whole machine erection |
| US12012551B2 (en) | 2020-12-04 | 2024-06-18 | The Boeing Company | Systems and methods of use of UV-responsive laminates and methods of fabrication thereof |
-
2011
- 2011-09-24 CN CN2011203603996U patent/CN202243127U/en not_active Withdrawn - After Issue
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102358223A (en) * | 2011-09-24 | 2012-02-22 | 威海广泰空港设备股份有限公司 | Test car used for testing rodless airplane tractor |
| CN104002862A (en) * | 2014-05-08 | 2014-08-27 | 中航飞机股份有限公司西安飞机分公司 | Bearing rotary towing mechanism for tool class transport vehicle |
| CN104614108A (en) * | 2015-01-12 | 2015-05-13 | 清华大学 | Device and method for measuring ground hauling load of aircraft |
| EP3330184A1 (en) * | 2016-12-02 | 2018-06-06 | The Boeing Company | Trailer-mounted mock landing gear |
| US20180154715A1 (en) * | 2016-12-02 | 2018-06-07 | The Boeing Company | Trailer-Mounted Mock Landing Gear |
| CN108146651A (en) * | 2016-12-02 | 2018-06-12 | 波音公司 | Simulation undercarriage on trailer |
| US10279637B2 (en) | 2016-12-02 | 2019-05-07 | The Boeing Company | Trailer-mounted mock landing gear |
| US11260708B2 (en) | 2016-12-02 | 2022-03-01 | The Boeing Company | Trailer-mounted mock landing gear |
| US11602963B2 (en) | 2016-12-02 | 2023-03-14 | The Boeing Company | Trailer-mounted mock landing gear |
| CN112356761A (en) * | 2020-09-22 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Aircraft transportation method based on whole machine erection |
| US12012551B2 (en) | 2020-12-04 | 2024-06-18 | The Boeing Company | Systems and methods of use of UV-responsive laminates and methods of fabrication thereof |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20120530 Effective date of abandoning: 20120926 |