CN110254744A - A kind of principal and subordinate wheel linkage mechanism method of adjustment - Google Patents
A kind of principal and subordinate wheel linkage mechanism method of adjustment Download PDFInfo
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- CN110254744A CN110254744A CN201910414612.8A CN201910414612A CN110254744A CN 110254744 A CN110254744 A CN 110254744A CN 201910414612 A CN201910414612 A CN 201910414612A CN 110254744 A CN110254744 A CN 110254744A
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- wheel hub
- movable door
- subpoint
- connecting rod
- upper connecting
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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
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automobile Manufacture Line, Endless Track Vehicle, Trailer (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
A kind of principal and subordinate wheel linkage mechanism method of adjustment, installs laser pen in active wheel hub, and the laser pen is axial vertical with active wheel hub rotational plane；Laser projection plate is pasted in driven wheel hub, and produces theoretical subpoint on the projection plate；By opening and closing movable door operating mechanism, the deviation of practical subpoint and the theoretical subpoint of the laser pen on the projection plate is observed；By adjusting cable wire overall length and cable tension, it is overlapped the practical subpoint with the theoretical subpoint.
Description
Technical field
This application involves technical field of aerospace, in particular to a kind of principal and subordinate wheel linkage mechanism method of adjustment.
Background technique
Large span multi link cable wire connection driven wheel linkage mechanism is mainly used for aircraft activity group (portion) part with respect to body
Unlatching, close, generally include hydraulic actuator, active wheel hub, driven wheel hub, switching rocker arm, adjustable drawbar, cable wire etc..It is main
Runner hub is the primary load bearing tie of activity group (portion) part and power feed system, due to the mechanism category linkage mechanism, driven wheel
Hub rotation is asynchronous or rod length adjust inaccuracy will lead to groups of significant size (portion) during the shutdown process stress it is asynchronous and
Unevenness, and then the cooperation precision with body is influenced, it is mainly shown as overproof with body gap clearance, scale or cable tension.
Currently, in practice process, though metastable rod length, pressurized strut length, rope length have been determined according to R&D experience
With the term of reference of tension, and installation, the process flow of debugging and control stress point, during only highlighting more hub rotations
Synchronism adjusts importance, but carries out movable door scale, gap and cable tension without reliable, cured process or means
Adjustment.
Apply for content
The application overcome it is existing only by rule of thumb value debugging wheel hub synchronism, pull rod, pressurized strut, cable tension deficiency,
Providing one kind can be used for practical operation, and can guarantee that final movable door scale, gap, cable tension meet engine request
Process.
In a first aspect, the application provides principal and subordinate wheel linkage mechanism method of adjustment, laser pen is installed in active wheel hub, institute
It is axial vertical with active wheel hub rotational plane to state laser pen；
Laser projection plate is pasted in driven wheel hub, and produces theoretical subpoint on the projection plate；
By opening and closing movable door operating mechanism, practical projection of the laser pen on the projection plate is observed
The deviation of point and the theoretical subpoint；
By adjusting cable wire overall length and cable tension, it is overlapped the practical subpoint with the theoretical subpoint.
Optionally, before laser pen being installed in the active wheel hub, method further include:
The work of installing mechanism components.
Optionally, the installing mechanism components work, specifically includes:
By default process installation activity hatch door operating mechanism；
Control active wheel hub, the depth of parallelism of driven wheel hub and Airplane frame plane；
Spacing is in default safe distance between control body and movable door, to guarantee in linkage mechanism motion process
Hatch door and body have safety clearance.
Optionally, after spacing is in default safe distance between control body and the movable door, the method
Include:
Adjust hydraulic actuator, upper connecting rod, lower link, small rod and cable wire overall length, the upper company of the upper movable door made
Upper connecting rod and the tie point of driven wheel hub, the lower link of lower movable door of bar and the tie point of active wheel hub, upper movable door
Within a preset range with the tie point of the tie point of active wheel hub, the lower link of lower movable door and driven wheel hub；
Optionally, after adjusting described in hydraulic actuator, upper connecting rod, lower link, small rod and cable wire overall length, method
Further include:
Itself stress of cable wire is eliminated by opening and closing movable door operating mechanism.
Optionally, after the practical subpoint is overlapped with the theoretical subpoint, the method is also included:
When active wheel hub, driven wheel hub rotate synchronously after, then adjust hydraulic actuator, upper connecting rod, lower link, small rod with
The upper connecting rod and driven wheel of the tie point of cable wire overall length, the upper connecting rod of the upper movable door made and active wheel hub, upper movable door
The tie point of hub, the tie point of the upper connecting rod of lower movable door and active wheel hub, the upper connecting rod of lower movable door and driven wheel hub
Tie point within a preset range.
Optionally, after the adjustment hydraulic actuator, upper connecting rod, lower link, small rod are with cable wire overall length, method is also
Include:
The scale of Survey Operations hatch door and fuselage, cable tension are all satisfied preset requirement, pass through filing movable door foreign steamer
Exterior feature, so that the gap of the movable door and the fuselage meets preset requirement.
Optionally, the installation site of laser pen is chosen at far from driving wheel center of rotation.
In conclusion this application provides a kind of connection driven wheel linkage mechanism adjustment of large span multi link cable wire
Process specifies that linkage mechanism adjusts benchmark in debugging process, reduces since mechanism constellation variable is more, make
At movable door mechanism debugging process in numerous variables such as the pull rod of adjustment repeatedly, pressurized strut length and cable wire overall length and produce
Raw workload, while shortening movable door mechanism debugging cycle, meet linkage mechanism cable tension requirement, and raising activity
Hatch door and the final fit clearance of fuselage, scale quality.
Detailed description of the invention
Fig. 1 is hatch door operating mechanism schematic diagram provided by the present application；
Fig. 2 is hatch door mechanism driving wheel side view diagram (A direction view in Fig. 1) provided by the present application；
Fig. 3 is hatch door mechanism driven wheel side view diagram (B direction view in Fig. 1) provided by the present application；
Fig. 4 is hatch door provided by the present application and operating mechanism installation procedure figure；
Fig. 5 is laser pen schematic diagram provided by the present application；
Fig. 6 is laser projection plate schematic diagram provided by the present application；
Fig. 7 is hatch door operating mechanism testing and measuring technology flow chart provided by the present application.
Wherein: 1. emergency springs, 2. cable wires, 3. upper-deck cabin door hinge chain joints, 4. active wheel hubs, 5. driven wheel hubs, 6. is hydraulic
Pressurized strut, 7. swing rods, hatch door on 8., 9. lower hatch doors, 10. bodies, 11. lower links, 12. upper connecting rods, 13. lower hatch door hinge-connections
Head, 14. switching rocker arms, 15. laser pen installation points, 16. small rods, 17. gas springs, 18. theoretical subpoints, hatch door machine under 19a.
Structure dead point, 19b upper-deck cabin door machine structure dead point.
Specific embodiment
Embodiment one
The application is achieved through the following technical solutions:
A is completed the installation of hatch door operating mechanism by process；(see Fig. 1)
B installation process priority control active wheel hub, the depth of parallelism of driven wheel hub and Airplane frame plane；
C slightly repairs surplus at body and movable door, guarantees that movable door and body have peace in linkage mechanism motion process
Full gap；
D just adjusts hydraulic actuator, upper connecting rod, lower link, small rod and cable wire overall length, grasps upper and lower movable door
Vertical mechanism dead point in theoretical claimed range, guarantee linkage mechanism open, in closing process can proper motion, and multiple folding and unfolding
Mechanism eliminates cable wire itself stress；(see Fig. 3)
E chooses laser pen installation point 15 on driving wheel, it is desirable that laser pen is axial vertical with active wheel hub rotational plane；
(installation site of laser pen is chosen in principle from driving wheel center of rotation farthest, sees Fig. 3, Fig. 5)
F pastes laser projection plate in driven wheel hub, and theoretical subpoint is produced on projection plate；(see Fig. 6)
G folding and unfolding movable door linkage mechanism, the practical subpoint of observation laser projection to rear-wheel hub and theoretical subpoint
Change of error situation；
H finely tunes cable wire overall length and tension, is overlapped practical subpoint with theoretical subpoint；
After I guarantees that active, driven wheel hub synchronize, then hydraulic actuator, upper connecting rod, lower link, small rod are finely tuned with overall length
Guarantee dead-centre position range, scale, the cable tension of Survey Operations hatch door and fuselage, last backfit gap.
Embodiment two
It elaborates in conjunction with attached drawing 1-7 adjustment a kind of to the application and check device:
This application provides a kind of large span multi link cable wires to connect the process that driven wheel linkage mechanism adjusts,
It is main to be implemented by following procedure:
It carries out completing active wheel hub 4 in linkage mechanism by Fig. 1, driven wheel hub 5, switching rocker arm 14, hydraulic actuator 6, answer
Anxious spring 1, cable wire 2, upper hatch door 2, swing rod 7, gas spring 17, lower hatch door 9, upper-deck cabin door hinge chain joint 3, lower hatch door knuckle joint 13
Installation and connection.Preparation includes: before linkage mechanism adjusts
A) body jacks up state, and body and linkage mechanism is made to be in free state；
B) connection linkage mechanism pressurized strut 6 and compression test platform guarantee to provide mechanism power source；
C) all movements or revolving member are required after installing, must not be collided with structure or element of installation, and is guaranteed mutually suitable
Suitable movement clearance；
D) after active wheel hub 4 and driven wheel hub 5 being installed, it should check and adjust the flat of hub rotation face and body frame interplanar
Row degree, making during hub rotation cable wire, stress in wheel hub steel moulds card slot bottom surface always；
E) connection pressurized strut 6 checks adjustable 6 overall length of pressurized strut, adjusts to overall length design tolerance range with before active wheel hub 4
Interior, being then turned on hydraulic car connect progress pressurized strut after the unilateral opening to range of pressurized strut 6 with active wheel hub；
F) in upper hatch door 8,9 surrounding of lower hatch door, gap, scale measurement point are marked, for detect adjustment process intermediate gap,
Scale variation.
It is as follows that hatch door linkage mechanism adjusts process:
To upper hatch door 8,9 shape of lower hatch door to body process allowance carry out just file repair, make hatch door during the shutdown process with machine
Body does not generate interference, and guarantees comparatively safe gap width, and gap width is not more than theory state gap width.Initial adjustment upper connecting rod 12, under
11 length of connecting rod makes the scale of hatch door 8, lower hatch door 9 and body 10 in theoretical claimed range, and it is each to press hatch door label record
Locate scale, for the variation comparison of subsequent scale.Just adjustment 16 length of small rod makes transfer rocker arm 14 and small rod 16, lower link
11 are lower than dead point 19a, 19b with lower 9 tie point connecting line of hatch door, and meet in theoretical claimed range；Adjust upper connecting rod 12, under
The length of connecting rod 11, small rod 16, pressurized strut 6 and cable wire 2, makes wheel hub (4,5) center of rotation and upper connecting rod 12 and swing rod 7
The line of tie point is lower than dead point 19b and meets in teachings.The multiple folding and unfolding of linkage mechanism sufficiently discharges cable wire 2 itself
Stress is allowed to tension and tends towards stability.Reality is looked on driven 5 projection plate of wheel hub with the laser pen light beam being mounted in active wheel hub 4
Border subpoint, and the actual deviation with theoretical subpoint is recorded, 2 length of cable wire and tension are adjusted according to differential location, makes reality
Subpoint is overlapped with theoretical subpoint 18.2 tension inspection of cable wire.Again to upper hatch door 8,9 operating mechanism dead point size of lower hatch door
It checks and finely tunes., such as there is relatively large deviation in the scale inspection of upper hatch door 8, lower hatch door 9 and body 10, again repeatedly linkage mechanism
Folding and unfolding discharges 2 tension of cable wire, until scale is met the requirements.2 tension inspection of cable wire.Solid state is met the requirements to scale, tension
Afterwards, then to body 10 and hatch door cooperation border refine is carried out, guarantees that gap meets engine request.
In conclusion the application belongs to technical field of aerospace, it is related to a kind of large span multi link cable wire connection driven wheel
The process of linkage mechanism adjustment.The application is optimized and is improved to linkage mechanism traditional debugging method, by actively
Increase between wheel hub and the inspection and amendment and active wheel hub and driven wheel hub of body frame plane when wheel hub, the installation of driven wheel hub
Rotation synchronism detection device is established, reduces Variable Factors of the linkage mechanism in debugging process, simplifies linkage mechanism tune
The complexity of examination.The application overcome Conventional processing methods it is asynchronous to active wheel hub and driven hub rotation caused by movable part
Part and body cooperate uncoordinated defect, by the hand for increasing driving and driven wheel hub synchronization check and adjustment in debugging process
Section, has cured adjustment benchmark, compensates for the deficiency that conventional method constantly adjusts each variation.
Claims (8)
1. a kind of principal and subordinate wheel linkage mechanism method of adjustment, it is characterised in that:,
Laser pen is installed in active wheel hub, the laser pen is axial vertical with active wheel hub rotational plane；
Laser projection plate is pasted in driven wheel hub, and produces theoretical subpoint on the projection plate；
By open and close movable door operating mechanism, observe practical subpoint of the laser pen on the projection plate with
The deviation of the theory subpoint；
By adjusting cable wire overall length and cable tension, it is overlapped the practical subpoint with the theoretical subpoint.
2. according to the method described in claim 1, it is characterized by: in the active wheel hub install laser pen before, method
Further include:
The work of installing mechanism components.
3. according to the method described in claim 1, it is characterized by: installing mechanism components work, specifically includes:
By default process installation activity hatch door operating mechanism；
Control active wheel hub, the depth of parallelism of driven wheel hub and Airplane frame plane；
Spacing is in default safe distance between control body and movable door, to guarantee hatch door in linkage mechanism motion process
Has safety clearance with body.
4. according to the method described in claim 3, it is characterized by: spacing is pre- between control body and the movable door
If after in safe distance, which comprises
Adjust hydraulic actuator, upper connecting rod, lower link, small rod and cable wire overall length, the upper connecting rod of the upper movable door made with
The tie point of active wheel hub, the tie point of the upper connecting rod of upper movable door and driven wheel hub, the lower link of lower movable door and master
The tie point of the tie point of runner hub, the lower link of lower movable door and driven wheel hub is within a preset range；
5. according to the method described in claim 3, it is characterized by: in adjustment hydraulic actuator, upper connecting rod, lower link, little Lian
After described in bar and cable wire overall length, method further include:
Itself stress of cable wire is eliminated by opening and closing movable door operating mechanism.
6. according to the method described in claim 3, it is characterized by: the practical subpoint is overlapped it with the theoretical subpoint
Afterwards, the method also includes:
After active wheel hub, driven wheel hub rotate synchronously, then hydraulic actuator, upper connecting rod, lower link, small rod are adjusted with cable wire
The tie point of overall length, the upper connecting rod of the upper movable door made and active wheel hub, the upper connecting rod of upper movable door and driven wheel hub
Tie point, the tie point of the upper connecting rod of lower movable door and active wheel hub, the upper connecting rod of lower movable door and the company of driven wheel hub
Contact is within a preset range.
7. according to the method described in claim 6, it is characterized by: the adjustment hydraulic actuator, upper connecting rod, lower link,
After small rod is with cable wire overall length, method further include:
The scale of Survey Operations hatch door and fuselage, cable tension are all satisfied preset requirement, by filing movable door outer profile, make
The gap for obtaining the movable door and the fuselage meets preset requirement.
8. according to the method described in claim 3, it is characterized by:
The installation site of laser pen is chosen at far from driving wheel center of rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910414612.8A CN110254744B (en) | 2019-05-17 | 2019-05-17 | Method for adjusting driving and driven wheel linkage mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910414612.8A CN110254744B (en) | 2019-05-17 | 2019-05-17 | Method for adjusting driving and driven wheel linkage mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110254744A true CN110254744A (en) | 2019-09-20 |
| CN110254744B CN110254744B (en) | 2022-08-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910414612.8A Active CN110254744B (en) | 2019-05-17 | 2019-05-17 | Method for adjusting driving and driven wheel linkage mechanism |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001241922A (en) * | 2000-02-29 | 2001-09-07 | Mitsuboshi Belting Ltd | Belt size measuring apparatus |
| CN103029836A (en) * | 2011-10-08 | 2013-04-10 | 天津职业技术师范大学 | Information rapid access and emergency rescue airdrop robot system in disaster environment |
| CN205571459U (en) * | 2016-03-22 | 2016-09-14 | 杭州振华钣金有限公司 | Accurate rocking arm brill to drill bit location |
| CN106393012A (en) * | 2015-07-29 | 2017-02-15 | 空中客车运营简化股份公司 | Tool-support system and operating method thereof |
| CN109533392A (en) * | 2018-12-07 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of antenna cover inner surface foil gauge patch location determines method |
-
2019
- 2019-05-17 CN CN201910414612.8A patent/CN110254744B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001241922A (en) * | 2000-02-29 | 2001-09-07 | Mitsuboshi Belting Ltd | Belt size measuring apparatus |
| CN103029836A (en) * | 2011-10-08 | 2013-04-10 | 天津职业技术师范大学 | Information rapid access and emergency rescue airdrop robot system in disaster environment |
| CN106393012A (en) * | 2015-07-29 | 2017-02-15 | 空中客车运营简化股份公司 | Tool-support system and operating method thereof |
| CN205571459U (en) * | 2016-03-22 | 2016-09-14 | 杭州振华钣金有限公司 | Accurate rocking arm brill to drill bit location |
| CN109533392A (en) * | 2018-12-07 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of antenna cover inner surface foil gauge patch location determines method |
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| Publication number | Publication date |
|---|---|
| CN110254744B (en) | 2022-08-09 |
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