CN105539876B - Aircraft assembly posture adjustment ball head device - Google Patents
Aircraft assembly posture adjustment ball head device Download PDFInfo
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- CN105539876B CN105539876B CN201510932250.3A CN201510932250A CN105539876B CN 105539876 B CN105539876 B CN 105539876B CN 201510932250 A CN201510932250 A CN 201510932250A CN 105539876 B CN105539876 B CN 105539876B
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- 238000001514 detection method Methods 0.000 claims abstract description 18
- 238000009434 installation Methods 0.000 claims abstract description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 241000233855 Orchidaceae Species 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
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Abstract
The invention discloses a kind of aircraft assembly posture adjustment ball head devices, belong to aircraft manufacturing equipment field.Have the shortcomings that error is big, connecting portion stress is big to fuselage posture adjustment using special type frame or using manual operation jack mode at present.The present invention includes ball and socket base and the mounting base for connecting support fuselage, mounting base top is connecting flange, lower part is fixed by the connecting rod one bulb of connection, mounting base installation cavity is arranged in ball and socket base pedestal center, the installation cavity lower part is ball-and-socket corresponding with the bulb, and mounting base is placed in the ball and socket base；Ball and socket base side has been uniformly arranged in the circumferential direction 3 clamping devices, and the bottom of ball and socket base is provided with into a detection switch.The present invention combines three coordinate digital control location devices, effectively overcomes trueness error existing for artificial posture adjustment, improves the automation and intelligence of aircraft assembly, preferably makes 6 free posture adjustments in orientation of fuselage.
Description
Technical field
The invention belongs to aircraft manufacturing equipment fields, especially related with posture adjustment ball head device with a kind of aircraft assembly.
Background technique
In aircraft assembly, in order to guarantee the interchangeability and harmony of airframe docking, body parts are after the assembly is completed
Need to carry out finishing operations to eliminate accumulated error.Fuselage finishing before pose adjustment should meet the wing body cooperation accuracy and
Fuselage relative position accuracy requirement, i.e. wing body crossing point holes meet machinability evaluation, while meet fuselage measurement point height difference
Technical requirements.
In traditional aircraft assembly positioning, aircraft and component are fixed on special type often through shape snap-gauge and pin shaft
On frame, or more jack is used to jack up aircraft components, achievees the purpose that aircraft components position by adjusting jack.By
In the influence of the factors such as foozle, rigging error and temperature, it is difficult to avoid that use is more barbarous using the method that type frame positions
Assembling means force aircraft and component into position, erection stress is inevitable, and equipment frock can not almost reuse.
It is positioned using jack, needs field personnel to adjust jack according to personal operating experience, to the skill of field personnel
Art is more demanding, and again because manual operations is unable to ensure the cooperative motion of multiple jack, erection stress not can avoid.
Summary of the invention
Present invention aim to overcome to adjust fuselage posture by special type frame or manual operation jack at present
There is the defects of equipment utilization rate is low, posture adjustment error is big and inconvenient in mode, provide a kind of energy reuse, and be able to cooperate three
Coordinate digital control location device makes fuselage in the posture adjustment locator bulb mechanism of 6 free posture adjustments of angle in space.
For this purpose, the invention adopts the following technical scheme: aircraft, which assembles, uses posture adjustment ball head device, it is characterized in that: the ball
Head device includes ball and socket base and the mounting base for connecting support aircraft components bracket, and the mounting base top is connection method
Orchid, lower part are fixed by the connecting rod one bulb of connection, and mounting base installation cavity, the installation cavity is arranged in the ball and socket base pedestal center
Lower part is ball-and-socket corresponding with the bulb, and the bulb of the mounting base is placed in the ball and socket base, can be freely rotated；
The ball and socket base side is circumferentially arranged at least two clamping device, setting through-hole corresponding with clamping device on ball-and-socket wall,
Clamping device includes the gripping block that is set in the through-hole and can protrude into ball-and-socket and the clamping drive of driving gripping block telescopic moving
Motivation structure can be fixedly clamped to mounting base after the completion of the bracket posture adjustment being mounted in mounting base, prevent rotational displacement again；Institute
The bottom for the ball and socket base stated be provided with protrude into ball-and-socket enter a detection switch, this enters a detection switch for detecting whether bulb enters
Position is qualified.
The present invention is put down in use, being fixed on the bulb mechanism to have first along tri- directions right angle three-coordinate X, Y, Z
It moves at the top of three number of coordinates control appearance locators of freedom degree, then will be connected with the bulb merging of the mounting base of aircraft components bracket
In ball and socket base, enter detection switch detection bulb enter position it is qualified after, the pose adjustment in 6 orientation can be carried out to fuselage, work as machine
After body pose adjustment, start clamping device, mounting base is fixedly clamped, entire posture adjustment work finishes.
As further improving and supplementing to above scheme, the invention also includes following characteristics:
The clamping device quantity is 3, and is uniformly distributed circumferentially in ball and socket base side.
The clamping drive mechanism is cylinder, and the gripping block is connected to the piston rod of cylinder, the gripping block and bulb
The end face of contact is cambered surface, and when being fixedly clamped to mounting base, which can sufficiently be bonded bulb, and bulb firm grip is consolidated
It is fixed.
The ball and socket base bottom be provided with perforation ball-and-socket detection through-hole, it is described enter a detection switch include flange sleeve
Cylinder, inductor, gauge head and spring, flange sleeve are threaded onto the detection through-hole and are installed by screw and fixed, flange sleeve
Hollow cavity both ends are all fixedly installed with the end cap equipped with through-hole, and gauge head is provided with axial limiting end face, and gauge head passes through the axial direction
The limitation of limit end face is placed in flange sleeve hollow cavity, and the spring supporting by being placed in flange sleeve hollow cavity
At the top of hollow cavity, gauge head head passes through the through-hole of the end cap of ball-and-socket side and protrudes into ball-and-socket, the inductor
Head penetrates the hollow cavity of flange sleeve and is arranged with gauge head interval, and gauge head head is pressed against when bulb enters, is surveyed by making
Head moves down close to inductor and realizes induction feedback, and bulb is avoided directly to squeeze inductor and damage inductor.
The present invention can achieve following the utility model has the advantages that bulb and ball-and-socket under being controlled by clamping device cooperate, and realization connects
The mounting base energy Multi-angle free rotation of support aircraft components bracket is connect, and is used together with three number of coordinates control appearance locators,
It is able to achieve and is adjusted and docks by collaborative computer control posture adjustment locator grouping machine body pose, to improve posture adjustment essence
Degree, realizes the fuselage Butt Assembling of low stress, effectively overcomes trueness error existing for artificial posture adjustment, improves aircraft assembly oneself
Dynamicization and intelligence.
Detailed description of the invention
Fig. 1 is structure chart of the invention.
Fig. 2 is the A-A cross-sectional view of Fig. 1.
Fig. 3 is the partial enlarged view at a of Fig. 2.
Wherein, 1, ball and socket base；2, clamping drive mechanism；3, mounting base；4, gripping block；5, enter a detection switch；6, flange
Sleeve；7, gauge head；8, spring.
Specific embodiment
Specific embodiments of the present invention will be described in detail with reference to the accompanying drawing.
As shown in Fig. 1 ~ Fig. 3, the present invention includes ball and socket base 1 and the mounting base 3 for connecting support aircraft components bracket, institute
3 top of mounting base stated is connecting flange, and lower part is fixed by the connecting rod one bulb of connection, the 1 pedestal center of ball and socket base
Mounting base installation cavity is set, which is ball-and-socket corresponding with the bulb, and the bulb of the mounting base 3 is placed in
In the ball and socket base 1；1 side of ball and socket base is circumferentially arranged 3 clamping devices, and 1 side of ball and socket base circumferentially
It is uniformly distributed；Be arranged on ball-and-socket wall clamping device it is corresponding and through-hole, clamping device includes being set in the through-hole and capable of stretching
Enter the gripping block 4 of ball-and-socket and the clamping drive mechanism 2 of driving gripping block telescopic moving, which is cylinder, described
Gripping block 4 is connected to the piston rod of cylinder, and the end face which contacts with bulb is cambered surface；The bottom of the ball and socket base 1
Be provided with protrude into ball-and-socket enter a detection switch 5,1 bottom of ball and socket base is provided with the detection through-hole of perforation ball-and-socket, described
Entering a detection switch 5 includes flange sleeve 6, inductor, gauge head 7 and spring 8, and flange sleeve 6 is threaded onto the detection through-hole
And installed and fixed by screw, 6 hollow cavity both ends of flange sleeve are all fixedly installed with the end cap equipped with through-hole, and gauge head 7 is arranged
There is axial limiting end face, gauge head 7 is placed in the hollow cavity of flange sleeve 6 by axial limiting end face limitation, and by setting
The support of the spring 8 in flange sleeve hollow cavity is located at the top of hollow cavity, and 7 head of gauge head passes through the institute of ball-and-socket side
It states the through-hole of end cap and protrudes into ball-and-socket, the inductor head penetrates the hollow cavity of flange sleeve 6 and sets with the interval of gauge head 7
It sets.
The present invention is in use, be fixed on the bulb mechanism has along tri- directions X, Y, Z of right angle three-coordinate first
At the top of three number of coordinates control appearance locators of translation freedoms, it then will be connected with the bulb of the mounting base 3 of aircraft components bracket
Be placed in ball and socket base 1, enter a detection switch 5 detect bulb enter position it is qualified after, the posture tune in 6 orientation can be carried out to fuselage
It is whole, after fuselage pose adjustment, start clamping device, mounting base is fixedly clamped, entire posture adjustment work finishes.
The above described is only a preferred embodiment of the present invention, not making in any form to structure of the invention
Limitation.Any simple modification, equivalent change and modification to the above embodiments according to the technical essence of the invention,
It falls within the scope of protection of the present invention.
Claims (3)
1. aircraft assembly posture adjustment ball head device, it is characterised in that: the ball head device includes ball and socket base (1) and for connecting
The mounting base (3) of aircraft components bracket is supported, the mounting base (3) top is connecting flange, and lower part is fixed by the connecting rod
A bulb is connected, mounting base installation cavity is arranged in the ball and socket base (1) pedestal center, which is and the bulb
Corresponding ball-and-socket, the bulb of the mounting base (3) are placed in the ball and socket base (1)；Described ball and socket base (1) side is circumferentially
It is provided at least two clamping device, through-hole corresponding with clamping device is set on ball-and-socket wall, clamping device is described including being set to
In through-hole and the gripping block (4) of ball-and-socket can be protruded into and drive the clamping drive mechanism (2) of gripping block telescopic moving；The ball-and-socket
The bottom of seat (1) be provided with protrude into ball-and-socket enter a detection switch (5)；Described ball and socket base (1) bottom is provided with perforation ball-and-socket
Detection through-hole, it is described enter a detection switch (5) include flange sleeve (6), inductor, gauge head (7) and spring (8), flange sleeve
Cylinder (6) is threaded onto the detection through-hole and is installed by screw and fixed, and flange sleeve (6) hollow cavity both ends are all fixedly mounted
There is the end cap equipped with through-hole, gauge head (7) is provided with axial limiting end face, and gauge head (7) is placed in by axial limiting end face limitation
In the hollow cavity of flange sleeve (6), and the support of the spring (8) by being placed in flange sleeve hollow cavity is positioned at hollow
Inner cavity top, gauge head (7) head pass through the through-hole of the end cap of ball-and-socket side and protrude into ball-and-socket, and the inductor head is worn
Enter the hollow cavity of flange sleeve (6) and be spaced with gauge head (7) to be arranged.
2. aircraft assembly posture adjustment ball head device according to claim 1, it is characterised in that: the clamping device quantity
It is 3, and is uniformly distributed circumferentially in ball and socket base (1) side.
3. aircraft assembly posture adjustment ball head device according to claim 2, it is characterised in that: the clamping drive mechanism
It (2) is cylinder, the gripping block (4) is connected to the piston rod of cylinder, and the end face which contacts with bulb is cambered surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510932250.3A CN105539876B (en) | 2015-12-14 | 2015-12-14 | Aircraft assembly posture adjustment ball head device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510932250.3A CN105539876B (en) | 2015-12-14 | 2015-12-14 | Aircraft assembly posture adjustment ball head device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105539876A CN105539876A (en) | 2016-05-04 |
| CN105539876B true CN105539876B (en) | 2018-12-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510932250.3A Active CN105539876B (en) | 2015-12-14 | 2015-12-14 | Aircraft assembly posture adjustment ball head device |
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| Country | Link |
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| CN (1) | CN105539876B (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108247555B (en) * | 2016-12-28 | 2019-05-10 | 大连四达高技术发展有限公司 | Ball hinge clamping and stress monitoring device and method based on flexible butt joint of large components |
| CN106826171B (en) * | 2017-03-09 | 2022-09-23 | 上海奇灏特自动化工程有限公司 | Bolt type anti-escape ball positioning device and using method thereof |
| CN107263351B (en) * | 2017-05-09 | 2019-01-29 | 浙江大学 | A kind of mechanical ball head locking device of locator |
| CN107512404A (en) * | 2017-07-04 | 2017-12-26 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft component attitude adjusting system space kinematic accuracy detecting system and method |
| CN113397712B (en) * | 2018-09-30 | 2023-01-24 | 南京迈科视医疗科技有限公司 | Surgical robot based on ball joint and tactile feedback |
| CN110174082A (en) * | 2019-06-03 | 2019-08-27 | 西安飞机工业（集团）有限责任公司 | A kind of restructural positioning system and localization method |
| CN112078820A (en) * | 2020-09-04 | 2020-12-15 | 江西昌河航空工业有限公司 | Adjustable supporting device of small airplane assembly tool and pose adjusting method |
| CN112192264B (en) * | 2020-11-30 | 2021-03-05 | 中国航空制造技术研究院 | Flexible supporting mechanism for automatic hole making of machine body |
| CN114871799B (en) * | 2022-05-18 | 2023-07-11 | 中航沈飞民用飞机有限责任公司 | Automatic drilling and riveting modularized flexible tool |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19929471C1 (en) * | 1999-06-26 | 2001-01-18 | Eads Airbus Gmbh | Method and device for producing a three-dimensional large component |
| CN2830053Y (en) * | 2005-08-19 | 2006-10-25 | 河南安彩高科股份有限公司 | Probe of press |
| CN100560303C (en) * | 2008-09-26 | 2009-11-18 | 浙江大学 | A Follow-up Locator Based on Air Float and Universal Ball Seat |
| CN101695814B (en) * | 2009-10-15 | 2011-01-19 | 浙江大学 | A method and device for precise positioning of large aircraft parts |
| CN102582847B (en) * | 2012-03-22 | 2014-12-24 | 沈阳飞机工业（集团）有限公司 | Ball-hinged coupling mechanism of locator based on three-dimensional force sensor |
| CN102794728B (en) * | 2012-08-22 | 2014-07-02 | 浙江大学 | Ball head self-adaption positioning and locking device and method thereof |
| CN204152951U (en) * | 2014-08-01 | 2015-02-11 | 上海上飞飞机装备制造有限公司 | Ball-type Rapid reset device |
| CN205168941U (en) * | 2015-12-14 | 2016-04-20 | 浙江日发航空数字装备有限责任公司 | Appearance locator bulb mechanism transfers |
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| CN105539876A (en) | 2016-05-04 |
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