CN103434655A - Assembly test vehicle of airplane nose landing gear - Google Patents
Assembly test vehicle of airplane nose landing gear Download PDFInfo
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- CN103434655A CN103434655A CN2013103843090A CN201310384309A CN103434655A CN 103434655 A CN103434655 A CN 103434655A CN 2013103843090 A CN2013103843090 A CN 2013103843090A CN 201310384309 A CN201310384309 A CN 201310384309A CN 103434655 A CN103434655 A CN 103434655A
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Abstract
The invention discloses an assembly test vehicle of an airplane nose landing gear, and four universal wheels and five servo electric cylinders are used for achieving six-freedom-degree movement of the nose landing gear and rotation of a strut of the nose landing gear along an axle. The movement amount, along an X axis and a Y axis, of the nose landing gear and the rotation amount, along a Z axis, of the nose landing gear can be adjusted manually and quickly, the movement amount, along the Z axis, of the nose landing gear, the rotation amount, along the X axis and the Y axis, of the nose landing gear and the rotation amount, along the axle, of the strut of the nose landing gear can be adjusted quantitatively through the servo electric cylinders, and the six-freedom-degree movement is achieved through real-time quantitative control. The assembly test vehicle of the airplane nose landing gear is high in freedom degree, easy to position accurately in an assembly process and capable of achieving the quantitative control in the assembly process and flexible manual rapid adjustment, assembly accuracy of the nose landing gear is greatly improved, and assembly time is saved.
Description
Technical field
The present invention relates to Design of Mechanical Structure and equipment technical field, specifically, relate to a kind of aircraft nose-gear assembling test car.
Background technology
At present, its Degree of Structure Freedom of test car that is applied to the assembling of aircraft nose-gear is dumb, and operation is to be aimed at and the assembling difficulty by manual operation, not only expends time in and affects the precision of undercarriage assembling, and affect the safety of aircraft.The nose-gear assembling test car flexible operation of six-freedom degree motion, the activity space scope is large, and test car can carry out three-dimensional and move and Three dimensional rotation, the free motion of implementation space.
Disclose a kind of six degree of freedom buttjunction platform in patent CN101081504, this docking platform is to be superimposed with the function of erectting regulating mechanism by plane regulating mechanism, realizes the motion of six-freedom degree.Described a kind of servo platform of the six-freedom hydraulic with ball pivot in patent CN2677679, this hydraulic servo platform is used the running of ball strand, utilizes servocontrol can realize programming control, and whole platform can turn round arbitrarily and stop.Above-mentioned technology adopts the stack of motion to realize six degree of freedom, but six degree of freedom buttjunction platform manual regulation, but its degree of freedom can't quantitatively be regulated, though the six-freedom hydraulic servo platform with ball pivot can be by servo quantitative adjusting, but some less demanding degree of freedom can't be realized manually flexibly quick adjustment, can't realize the completing fast of carrying operation of whole mechanism.
Summary of the invention
The present invention proposes a kind of aircraft nose-gear assembling test car, is mainly used in nose-gear and transports the nose-gear position reached when docking with assembling test type frame, the adjustment of attitude in the assembling test factory building.Nose-gear is assemblied on nose-gear assembling test car, utilizes air floating platform to realize that nose-gear is along the movement of X-axis, Y-axis with around the rotation of Z axis; Utilize four vertical servo electric jars to realize that nose-gear is along the movement of Z axis with around the rotation of X-axis, Y-axis; Utilize a horizontal servo electric cylinder to realize the rotation of the pillar of nose-gear along wheel shaft.The horizontal radial of wheel shaft is X-direction, and the axial of wheel shaft is that Y direction, vertical direction are Z-direction, around wheel shaft, rotates to be pitching.Test car can move, turn in factory building, nose-gear is transported to type frame installation site from assembly station, realize that nose-gear is in X-axis, Y-axis, three axial movements of Z axis with around the rotation of three axles, realize the fine motion adjustment of nose-gear pitch attitude, realize the rotation of the pillar of nose-gear along wheel shaft.
The technical solution adopted for the present invention to solve the technical problems is: alighting gear assembling test car, comprise erecting stage, cardan wheel, push rod, wherein, also comprise control housing, V shaped slab, vertical plate, overhanging adapter plate, flap, servo electric jar, slide block mechanism, safety limit switch, control housing is positioned at the outside of vertical plate on erecting stage, push rod is fixed on the vertical plate outer upper, four jiaos of erecting stage bottom surfaces installation cardan wheel; Described V shaped slab is fixed on the erecting stage middle part, slot is arranged in the middle of on two plate faces of V shaped slab, the V shaped slab quadripolar corners is connected by middle connecting plate and four vertical servo electric jar ends that are fixedly mounted on erecting stage, and flap and side shield are connected and are positioned at the V shaped slab side; Slide block mechanism and horizontal servo electric cylinder are mounted between overhanging adapter plate and flap, and safety limit switch is separately fixed between the vertical servo electric jar at V shaped slab two ends; Described overhanging adapter plate side and V shaped slab are connected, and the horizontal servo electric cylinder is connected with the vertical plate of overhanging adapter plate, and horizontal servo electric cylinder bar coordinates with the tapped bore of fixture block bottom; Described flap is L shaped and side shield is connected, and flap vertically has round tube hole in the middle of section, and lower end has dovetail furrow; Described slide block mechanism comprises fixture block and dovetail furrow slide block, the rectangular slab of slide block lower end snaps in the Baltimore groove of fixture block, little rotating shaft is through the through hole of rectangular blocks and the through hole of fixture block side, and the dovetail furrow slide block rotates around little rotating shaft, and the dovetail furrow slide block snaps in the dovetail furrow of flap; Described servo electric jar comprises four vertical servo electric jars and a horizontal servo electric cylinder; Four vertical servo electric jars are separately fixed on erecting stage, and spherical nut is installed in the end of four vertical servo electric jar bars, and fixes by large jam nut and little jam nut; The ball screw thread of four spherical nuts is arranged on respectively in the square slotted eye of circular slotted eye, the 4th spherical nut connecting panel of circular slotted eye, the 3rd spherical nut connecting panel of circular hole, the second spherical nut connecting panel of the first spherical nut connecting panel; Four spherical nut connecting panels are connected with four jiaos of V shaped slab respectively.
Beneficial effect
A kind of aircraft nose-gear assembling test car that the present invention proposes, utilize four cardan wheels and five servo electric jars, realizes the rotation of the pillar of the six-freedom motion of nose-gear and nose-gear along wheel shaft.Nose-gear along the amount of movement of X-axis, Y-axis and around Z axis the manual quick adjustment of amount of spin, nose-gear can quantitatively be regulated by servo electric jar along the amount of spin of wheel shaft along the Z axis amount of movement with around the amount of spin of X-axis and Y-axis, the pillar of nose-gear, can real time and determine amount control, realize six-freedom motion.The degree of freedom of nose-gear assembling test car is high, during assembling, aims at easily, and the quantitative control in the time of can realizing assembling, and manual quick adjustment flexibly, improve the assembly precision of nose-gear greatly, saves time of setting up.
The accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of aircraft nose-gear of the present invention assembling test car is described in further detail.
Fig. 1 is assembling test car of the present invention and nose-gear assembling schematic diagram.
Fig. 2 is assembling test bassinet structure schematic diagram of the present invention.
Fig. 3 is assembling test axletree mapping of the present invention.
Fig. 4 is assembling test car of the present invention and nose-gear assembling forward view.
The first spherical nut connecting panel that Fig. 5 is the assembling test car.
The second spherical nut connecting panel that Fig. 6 is the assembling test car.
The 3rd spherical nut connecting panel that Fig. 7 is the assembling test car.
The 4th spherical nut connecting panel that Fig. 8 is the assembling test car.
The spherical nut schematic diagram that Fig. 9 is the assembling test car.
Figure 10 is the slide block mechanism schematic diagram.
Figure 11 is the slide block mechanism birds-eye view.
Figure 12 is flap forward view.
Figure 13 is aircraft nose-gear structural representation.
Figure 14 is that aircraft nose-gear structure side is to view.
In figure:
1 test vehicle, 2 front landing gear tires, 3 front landing gear strut, 4. Mounting platform, 5.V shaped plate 6. Vertical electric servo cylinder 7. Caster, 8 left safety limit switches , 9 left baffle 10. overhanging fixed plate 11. horizontal electric servo cylinder 12. slider mechanism, 13. transfer, 14 shaft, 15. right bezel, 16. Right safety limit switch 17. side of the baffle, 18. vertical plate 19. putter, 20. fourth ball nut plate, 21 second ball nut plate 22. intermediate plate 23. third ball nut plate 24. first a ball nut plate 25. control cabinet 26 after safety limit switch 27. welded plate, 28. around the baffle 29. before the safety limit switch 30. vertical servo-electric cylinder rod 31. small lock nut, 32. large lock nut 33. threaded ball 34. dovetail slider 35. the small shaft 36. cards block 37. lock nut 38. horizontal electric servo cylinder rod
The specific embodiment
The present embodiment is a kind of aircraft nose-gear assembling test car.
Consult Fig. 1-Figure 14, invention aircraft nose-gear assembling test car, comprise erecting stage 4, cardan wheel 7, push rod 19, wherein, also comprise control housing 25, V shaped slab 5, vertical plate 18, overhanging adapter plate 10, flap 13, servo electric jar, slide block mechanism 12, safety limit switch, be fixed with slide block mechanism 12 on the cylinder rod end surface of horizontal servo electric cylinder 11, the cylinder bar can drive slide block mechanism 12 motions, one end of slide block mechanism and the cylinder bar of horizontal servo electric cylinder 11 are fixed, the other end is connected with flap 13, and can in the dovetail furrow of flap 13, slide, nose-gear pillar 3 leans against on flap 13, along with the flap motion.When the cylinder bar of horizontal servo electric cylinder moves, will make slide block mechanism 12 drive the flaps motion, the rotation of flap drives the rotation of nose-gear pillar 3 around wheel shaft, and the capable of regulating nose-gear is around the rotation of wheel shaft.When the cylinder bar of horizontal servo electric cylinder 11 is static, pillar is because Action of Gravity Field is pressed on the cylinder bar of horizontal servo electric cylinder 11 by flap and slide mechanism, realizes the fixing of nose-gear in fitting process, facilitates the assembling of nose-gear and fuselage.
Erecting stage four angles on a cardan wheel is installed respectively, and cardan wheel 7 is connected with the tapped bore hole of erecting stage 4 by self double-screw bolt.Vertical plate 18 is welded on erecting stage 4 right sides, and push rod 19 is welded on the rear side of vertical plate 18.Control housing 25 is fixed on the back that welded plate is welded on erecting stage.The tire of nose-gear is placed on V shaped slab 5, and tire is tangent with horizontal plate and two hang plates of V shaped slab 5 respectively.One end of welded plate is welded on the upper end of V shaped slab 5 right side hang plates, and keeps the vertical of welded plate and V shaped slab 5 horizontal surfaces.
Four vertical servo electric jars 6 are connected with air floating platform by four bolts respectively, respectively at the upper end of four vertical servo electric jar bars Plane Installation spherical nut, and fix by large jam nut 32 and little jam nut 31.The ball screw thread of four spherical nuts is arranged on respectively in the square groove of circular trough, the 4th spherical nut connecting panel 20 of circular trough, the 3rd spherical nut connecting panel 23 of circular hole, the second spherical nut connecting panel 21 of the first spherical nut connecting panel 24.Four spherical nut connecting panels are connected its vertical plate by four bolts respectively with an end of middle connecting plate.The other end of four middle connecting plates links together with four angles of V shaped slab hang plate respectively by welding, welds respectively four gussets in four junctions of middle connecting plate and V shaped slab 5 and fixes.
The trailing flank of the side of the horizontal plate of overhanging adapter plate 10 and V shaped slab horizontal plate is by being welded to connect.Horizontal servo electric cylinder 11 is connected with the vertical plate of overhanging adapter plate 10 by four bolts.Horizontal servo electric cylinder bar 38 is threaded connection with the tapped bore of fixture block bottom and coordinates.The rectangular slab of slide block lower end snaps in the Baltimore groove of fixture block, and the through hole of rectangular blocks is concentric with the through hole of fixture block side.Little rotating shaft 35 is through the through hole of rectangular blocks and the through hole of fixture block side.Dovetail furrow slide block 34 can freely rotate around little rotating shaft 35.Dovetail furrow slide block 34 snaps in the dovetail furrow groove of flap, and dovetail furrow slide block 34 can slide in dovetail furrow.Rotating shaft is through the manhole of flap and V shaped slab vertical plate, and flap 13 can freely rotate around the shaft, and the horizontal plate of flap contacts with nose-gear pillar 3.One of left baffle is held plate level level with both hands and is fixed on the edge of V shaped slab horizontal plate trailing flank, and makes the dull and stereotyped level of the other end forward.The biside plate of front and rear baffle is horizontally fixed on the downside of welding, and makes the U-shaped plate level towards the right side.Four safety limit switchs are bolted on erecting stage.Left side safety limit switch 8 is fixed on the left side of left side board, and right side safety limit switch 16 is fixed on the right side of right side board, and the front and back safety limit switch is arranged on respectively front side and the rear side of front and rear baffle.
The first step, be assemblied in nose-gear on nose-gear assembling test car.First the tire of nose-gear is placed on V-type plate, tire is tangent with horizontal plate and two hang plates of V-type plate respectively, then the horizontal plate of the pillar of nose-gear and rotor plate is close together, and concrete assembly drowing as shown in Figure 1.
Second step, realize that nose-gear is along the movement of X-axis, Y-axis with around the rotation of Z axis.Owing on four angles of erecting stage, cardan wheel being installed, the operation push rod moves movement and the rotation that can drive cardan wheel, can be light make assembled car along X-axis, and y-axis shift is moving and rotate along Z axis, nose-gear along with the assembling car along the movement of X-axis, Y-axis with around the rotation of Z axis.When the assembling car while adjusting to correct position, the brake gear by cardan wheel fixes cardan wheel, realizes the fixing of whole mechanism.Operating personal operation push rod, can be light move in factory building, turn, be transported to type frame installation site by nose-gear from assembly station, and fixed mechanism, realizes transportation function.
The 3rd step, realize the movement of nose-gear along Z axis.After nose-gear is carried to installation site, can control the motion of five servo electric jars by the operation control housing.Lifting by four vertical servo electric jars can realize the movement of V shaped slab along Z-direction, and the capable of regulating amount of movement.Principle of work: the rising of four vertical servo electric jars drives the rising of four spherical nuts, and four spherical nuts head on four spherical nut connecting panels risings simultaneously, drive V shaped slab and rise.The decline of four vertical servo electric jars drives the decline of four spherical nuts, simultaneously due to the isostructural deadweight of V shaped slab, makes four spherical nut connecting panels press all the time respectively four spherical nuts.
The 4th step, realize the rotation of nose-gear around X-axis, Y-axis.Can realize respectively that by the lifting of controlling certain two vertical servo electric jar V-type plate is along directions X, the rotation of Y-direction.Principle of work: the lifting of two vertical servo electric jars, drive the rising of two spherical nuts, the centre distance between four spherical nuts changes, spherical nut slides and realizes the variation of centre distance in by circular trough, square groove, the first spherical nut is fixing can not slide, the second spherical nut slides in the left and right directions circular trough, realize only the motion of left and right directions, the 3rd spherical nut slides in the fore-and-aft direction circular trough, realize only the motion of left and right directions, and the 4th spherical nut slides in square groove, can realize the motion on XY plane.Four spherical nuts are used in conjunction with the rotation realized along X-axis, Y-axis.
The 5th step, realize the rotation of the pillar of nose-gear along wheel shaft.Its fundamental diagram: by the motion of level of control servo electric jar, drive slide block mechanism and move back and forth.The dovetail furrow slide block can slide in the dovetail furrow of flap.Drive flap when the dovetail furrow slide block slides and rotate around the axis, flap rotates the pillar that drives nose-gear and rotates around wheel shaft, realizes the rotation of the pillar of nose-gear along wheel shaft.
Four safety limit switchs are separately fixed on erecting stage; safety limit switch is used in conjunction with corresponding baffle plate, for the safe spacing of V shaped slab all around, with the protection operating personal, preserves from; and prevent that the V shaped slab anglec of rotation is excessive, cause between parts and bump against.
The devices such as motion controller, servo-driver are arranged in control housing, motion controller is the core of whole control system, it accepts operator's operating order, controls the power elements such as each servo electric jar and is moved by predetermined speed, realizes in fitting process the adjustment to each attitude of equipment.Motion controller is accepted the location information of each power element, and half-closed loop control is carried out in the position of each power element, guarantees the accurate control of position.Motion controller is controlled the motion of five axles: servo electric jar, according to the instruction of motion controller, realizes driving nose-gear to reach the rotation around X-axis, Y-axis along the movement of Z-direction, and the horizontal servo electric cylinder is realized the rotation of the pillar of nose-gear along wheel shaft.Servo electric jar by coder by current servo electric jar position feedback to motion controller, realize the half-closed loop control to the servo-electric cylinder position, to realize the accurate control to position.
Realize that by the operational test car nose-gear transports in the assembling test factory building, in the time of can realizing the docking of assembling test type frame by controller, nose-gear is moving along X-axis, y-axis shift, around Z axis, rotates, and pillar is around the rotation of wheel shaft.Lifting by four vertical servo electric jars can realize the movement of nose-gear along Z axis, lifting by certain two vertical servo electric jar can realize respectively the rotation of nose-gear around directions X, Y-direction, by horizontal servo electric cylinder drive slide block mechanism and flap, can realize the rotation of the pillar of nose-gear around wheel shaft.
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Claims (1)
1. an aircraft nose-gear assembling test car, comprise erecting stage, cardan wheel, push rod, it is characterized in that: also comprise control housing, V shaped slab, vertical plate, overhanging adapter plate, flap, servo electric jar, slide block mechanism, safety limit switch, control housing is positioned at the outside of vertical plate on erecting stage, push rod is fixed on the vertical plate outer upper, four jiaos of erecting stage bottom surfaces installation cardan wheel; Described V shaped slab is fixed on the erecting stage middle part, slot is arranged in the middle of on two plate faces of V shaped slab, the V shaped slab quadripolar corners is connected by middle connecting plate and four vertical servo electric jar ends that are fixedly mounted on erecting stage, and flap and side shield are connected and are positioned at the V shaped slab side; Slide block mechanism and horizontal servo electric cylinder are mounted between overhanging adapter plate and flap, and safety limit switch is separately fixed between the vertical servo electric jar at V shaped slab two ends; Described overhanging adapter plate side and V shaped slab are connected, and the horizontal servo electric cylinder is connected with the vertical plate of overhanging adapter plate, and horizontal servo electric cylinder bar coordinates with the tapped bore of fixture block bottom; Described flap is L shaped and side shield is connected, and flap vertically has round tube hole in the middle of section, and lower end has dovetail furrow; Described slide block mechanism comprises fixture block and dovetail furrow slide block, the rectangular slab of slide block lower end snaps in the Baltimore groove of fixture block, little rotating shaft is through the through hole of rectangular blocks and the through hole of fixture block side, and the dovetail furrow slide block rotates around little rotating shaft, and the dovetail furrow slide block snaps in the dovetail furrow of flap; Described servo electric jar comprises four vertical servo electric jars and a horizontal servo electric cylinder; Four vertical servo electric jars are separately fixed on erecting stage, and spherical nut is installed in the end of four vertical servo electric jar bars, and fixes by large jam nut and little jam nut; The ball screw thread of four spherical nuts is arranged on respectively in the square slotted eye of circular slotted eye, the 4th spherical nut connecting panel of circular slotted eye, the 3rd spherical nut connecting panel of circular hole, the second spherical nut connecting panel of the first spherical nut connecting panel; Four spherical nut connecting panels are connected with four jiaos of V shaped slab respectively.
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| CN201310384309.0A CN103434655B (en) | 2013-08-29 | 2013-08-29 | A kind of aircraft nose landing gear assembling test car |
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| CN201310384309.0A CN103434655B (en) | 2013-08-29 | 2013-08-29 | A kind of aircraft nose landing gear assembling test car |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104401502A (en) * | 2014-09-30 | 2015-03-11 | 中航通飞华南飞机工业有限公司 | Flexible installation and storage two-purpose device for large undercarriage |
| CN105253325A (en) * | 2015-11-11 | 2016-01-20 | 北京特种机械研究所 | Aircraft main landing gear assembling and disassembling equipment |
| CN105292519A (en) * | 2015-11-11 | 2016-02-03 | 北京特种机械研究所 | Disassembly and assembly device for front landing gear of airplane |
| CN105345420A (en) * | 2015-11-11 | 2016-02-24 | 北京特种机械研究所 | Dismounting and mounting device of undercarriage |
| CN106379392A (en) * | 2016-11-17 | 2017-02-08 | 中航通飞华南飞机工业有限公司 | Flexible mounting and storage dual-purpose device for nose landing gear |
| CN108128480A (en) * | 2017-11-28 | 2018-06-08 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine lower-grade fuel bracket car |
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| CN110834739A (en) * | 2019-11-14 | 2020-02-25 | 昌河飞机工业（集团）有限责任公司 | Undercarriage moving installation device and method |
| CN110883565A (en) * | 2018-09-10 | 2020-03-17 | 华东至正工业自动化(常熟)有限公司 | Novel six-degree-of-freedom platform |
| CN114212272A (en) * | 2021-12-17 | 2022-03-22 | 江西洪都航空工业集团有限责任公司 | Quick loading and unloading mechanism |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2306188Y (en) * | 1997-02-01 | 1999-02-03 | 孙继库 | Vehicle for dismounting or mounting wheels of large-and medium-aircrafts |
| CN201077676Y (en) * | 2007-09-28 | 2008-06-25 | 大连浦州航空科技有限公司 | Universal hanging spring vehicle with gasoline and diesel oil |
| CN102107834A (en) * | 2011-02-24 | 2011-06-29 | 西北工业大学 | Lift adjusting device |
| CN202346691U (en) * | 2011-09-08 | 2012-07-25 | 西北工业大学 | Lifting device for accurate checking and assembly |
| CN103144782A (en) * | 2013-02-27 | 2013-06-12 | 中航飞机股份有限公司西安飞机分公司 | Posture alignment mounting device for component assembly |
| EP2631626A1 (en) * | 2012-02-24 | 2013-08-28 | Airbus Opérations SAS | Device for energising an aircraft landing gear on the ground |
-
2013
- 2013-08-29 CN CN201310384309.0A patent/CN103434655B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2306188Y (en) * | 1997-02-01 | 1999-02-03 | 孙继库 | Vehicle for dismounting or mounting wheels of large-and medium-aircrafts |
| CN201077676Y (en) * | 2007-09-28 | 2008-06-25 | 大连浦州航空科技有限公司 | Universal hanging spring vehicle with gasoline and diesel oil |
| CN102107834A (en) * | 2011-02-24 | 2011-06-29 | 西北工业大学 | Lift adjusting device |
| CN202346691U (en) * | 2011-09-08 | 2012-07-25 | 西北工业大学 | Lifting device for accurate checking and assembly |
| EP2631626A1 (en) * | 2012-02-24 | 2013-08-28 | Airbus Opérations SAS | Device for energising an aircraft landing gear on the ground |
| CN103144782A (en) * | 2013-02-27 | 2013-06-12 | 中航飞机股份有限公司西安飞机分公司 | Posture alignment mounting device for component assembly |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104401502B (en) * | 2014-09-30 | 2016-09-07 | 中航通飞华南飞机工业有限公司 | A kind of large-scale undercarriage flexible installing with deposit dual-purpose apparatus |
| CN104401502A (en) * | 2014-09-30 | 2015-03-11 | 中航通飞华南飞机工业有限公司 | Flexible installation and storage two-purpose device for large undercarriage |
| CN105253325A (en) * | 2015-11-11 | 2016-01-20 | 北京特种机械研究所 | Aircraft main landing gear assembling and disassembling equipment |
| CN105292519A (en) * | 2015-11-11 | 2016-02-03 | 北京特种机械研究所 | Disassembly and assembly device for front landing gear of airplane |
| CN105345420A (en) * | 2015-11-11 | 2016-02-24 | 北京特种机械研究所 | Dismounting and mounting device of undercarriage |
| CN105345420B (en) * | 2015-11-11 | 2017-08-08 | 北京特种机械研究所 | A kind of undercarriage attaching/detaching apparatus |
| CN106379392B (en) * | 2016-11-17 | 2019-11-26 | 中航通飞华南飞机工业有限公司 | A kind of aircraft nose landing gear flexible installing and storage dual-purpose apparatus |
| CN106379392A (en) * | 2016-11-17 | 2017-02-08 | 中航通飞华南飞机工业有限公司 | Flexible mounting and storage dual-purpose device for nose landing gear |
| CN108128480B (en) * | 2017-11-28 | 2021-03-23 | 中国航发沈阳黎明航空发动机有限责任公司 | Bracket vehicle for fuel accessories of aircraft engine |
| CN108128480A (en) * | 2017-11-28 | 2018-06-08 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine lower-grade fuel bracket car |
| CN110883565A (en) * | 2018-09-10 | 2020-03-17 | 华东至正工业自动化(常熟)有限公司 | Novel six-degree-of-freedom platform |
| CN110883565B (en) * | 2018-09-10 | 2024-04-26 | 华东至正工业自动化(常熟)有限公司 | Novel six-degree-of-freedom platform |
| CN109333474A (en) * | 2018-10-30 | 2019-02-15 | 广西玉柴机器股份有限公司 | A kind of universal support arrangement |
| CN110834739A (en) * | 2019-11-14 | 2020-02-25 | 昌河飞机工业（集团）有限责任公司 | Undercarriage moving installation device and method |
| CN114212272A (en) * | 2021-12-17 | 2022-03-22 | 江西洪都航空工业集团有限责任公司 | Quick loading and unloading mechanism |
| CN114212272B (en) * | 2021-12-17 | 2024-04-02 | 江西洪都航空工业集团有限责任公司 | Quick loading and unloading mechanism |
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| CN103434655B (en) | 2015-10-28 |
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