CN105539876A - Pose adjusting ball device for airplane assembly - Google Patents
Pose adjusting ball device for airplane assembly Download PDFInfo
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- CN105539876A CN105539876A CN201510932250.3A CN201510932250A CN105539876A CN 105539876 A CN105539876 A CN 105539876A CN 201510932250 A CN201510932250 A CN 201510932250A CN 105539876 A CN105539876 A CN 105539876A
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Abstract
The invention discloses a pose adjusting ball device for airplane assembly and belongs to the field of airplane manufacturing equipment. The defects that errors are large and the stress of the connecting portion is large exist in the airplane body pose adjustment process due to the adoption of a special fixture or a jack manual operation manner currently. The pose adjusting ball device comprises a ball socket seat and an installation seat used for being connected with and supporting an airplane body. A connecting flange is arranged at the upper portion of the installation seat and the lower portion of the installation seat is fixedly connected with a ball through a connecting rod. An installation seat installation cavity is formed in the center of the ball socket seat. A ball socket corresponding to the ball is arranged at the lower portion of the installation cavity. The installation seat is installed in the ball socket seat. Three clamping devices are evenly arranged on the sides of the ball socket seat in the circumferential direction. An in-position detection switch is arranged at the bottom of the ball socket seat. The pose adjusting ball device is combined with a three-coordinate numerical control locator, accuracy errors existing in manual pose adjustment are effectively avoided, airplane assembly automation and intelligence are improved, and the pose of the airplane body can be better adjusted in six directions.
Description
Technical field
The invention belongs to aircraft manufacturing equipment field, especially relevant with a kind of transporation by plane posture adjustment ball head device.
Background technology
In transporation by plane, in order to ensure the interchangeability that airframe docks and harmony, need after body parts has assembled to carry out finishing operations to eliminate accumulated error.Pose adjustment before fuselage fine limit work should meet wing body and coordinate accuracy and fuselage relative position accuracy requirement, and namely wing body crossing point holes meets machinability evaluation, makes the fuselage measurement point discrepancy in elevation meet technical requirements simultaneously.
In traditional transporation by plane location, often through profile clamp and bearing pin, aircraft and parts are fixed in special type frame, or adopt multiple stage jack by aircraft components jack-up, by the object regulating jack to reach aircraft components location.Due to the impact of the factors such as manufacturing errors, assembly error and temperature, adopt the method for type frame location to be difficult to avoid adopting more barbarous assembling means to make aircraft and parts force into position, assembly stress is inevitable, and equipment frock almost cannot reuse.Utilize jack to locate, need field man to regulate jack according to individual operating experience, higher to the technical requirements of field man, and also again because manual operations cannot guarantee the cooperative motion of multiple jack, assembly stress cannot be avoided.
Summary of the invention
Object of the present invention is exactly will overcome at present to have that equipment Occupation coefficient is low, posture adjustment error large by the mode of special type frame or manual operation jack reconditioner figure state and the defect such as operation inconvenience, a kind of energy repeated usage is provided, and three-dimensional digital control location device can be coordinated to make fuselage at the posture adjustment steady arm bulb mechanism of 6 free posture adjustments of angle in space.
For this reason, the present invention is by the following technical solutions: transporation by plane posture adjustment ball head device, it is characterized in that: described ball head device comprises ball seating and the mount pad for being connected support aircraft components bracket, described mount pad top is butt flange, bottom is fixedly connected with a bulb by pipe link, described ball seating pedestal center arranges mount pad installation cavity, this installation cavity bottom is the ball-and-socket corresponding with described bulb, the bulb of described mount pad is placed in described ball seating, can freely rotate; Described ball seating sidepiece is circumferentially provided with at least 2 fixing devices, ball-and-socket wall arranges the through hole corresponding with fixing device, fixing device comprises the clamp being arranged at and also can stretching into ball-and-socket in described through hole and the clamping drive mechanism driving clamp telescopic moving, can be fixedly clamped to mount pad when being arranged on after the bracket posture adjustment on mount pad completes, preventing rotational displacement again; The bottom of described ball seating be provided with stretch into ball-and-socket enter a detector switch, this enters a detector switch, and for detecting bulb, whether to enter position qualified.
When the present invention uses, first this bulb mechanism is fixed on the three-dimensional numerical control posture adjustment steady arm top had along right angle three-coordinate X, Y, Z tri-direction translation freedoms, then the bulb of the mount pad being connected with aircraft components bracket is inserted in ball seating, enter detector switch detect a bulb enter position qualified after, just can carry out the pose adjustment in 6 orientation to fuselage, after fuselage pose adjustment, start fixing device, be fixedly clamped by mount pad, whole posture adjustment work is complete.
As improving further and supplementing such scheme, the present invention also comprises following characteristics:
Described fixing device quantity is 3, and is uniformly distributed circumferentially at ball seating sidepiece.
Described clamping drive mechanism is cylinder, and described clamp is connected to the piston rod of cylinder, and the end face that this clamp contacts with bulb is cambered surface, and when being fixedly clamped to mount pad, this clamp can fully be fitted bulb, is fixed by bulb firm grip.
The detection through hole of through ball-and-socket is provided with bottom described ball seating, described enter a detector switch comprise flange sleeve, inductor, gauge head and spring, flange sleeve is threaded onto described detection through hole and is installed by screw fixing, flange sleeve hollow cavity two ends are all installed with the end cap being provided with through hole, gauge head is provided with axial limiting end face, gauge head is placed in flange sleeve hollow cavity by the restriction of this axial limiting end face, and be positioned at hollow cavity top by the described spring supporting being placed in flange sleeve hollow cavity, gauge head head passes the through hole of the described end cap of ball-and-socket side and stretches in ball-and-socket, described inductor head penetrate flange sleeve hollow cavity and and gauge head interval arrange, gauge head head is pressed against when bulb enters, move down by making gauge head and realize induction feedback close to inductor, bulb is avoided directly to extrude inductor and damage inductor.
The present invention can reach following beneficial effect: the bulb under being controlled by fixing device and ball-and-socket are coordinated, realize connecting the mount pad energy Multi-angle free rotation supporting aircraft components bracket, and use together with three-dimensional numerical control posture adjustment steady arm, can realize relying on collaborative computer to control posture adjustment steady arm grouping machine body pose to carry out adjusting and docking, thus improve posture adjustment precision, realize the fuselage Butt Assembling of low stress, effectively overcome the trueness error that artificial posture adjustment exists, improve automation and the intellectuality of transporation by plane.
Accompanying drawing explanation
Fig. 1 is constructional drawing of the present invention.
Fig. 2 is the A-A cutaway view of Fig. 1.
Fig. 3 is the partial enlarged drawing at a place of Fig. 2.
Wherein, 1, ball seating; 2, clamping drive mechanism; 3, mount pad; 4, clamp; 5, a detector switch is entered; 6, flange sleeve; 7, gauge head; 8, spring.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described in detail.
As shown in Fig. 1 ~ Fig. 3, the present invention includes ball seating 1 and the mount pad 3 for being connected support aircraft components bracket, described mount pad 3 top is butt flange, bottom is fixedly connected with a bulb by pipe link, described ball seating 1 pedestal center arranges mount pad installation cavity, this installation cavity bottom is the ball-and-socket corresponding with described bulb, and the bulb of described mount pad 3 is placed in described ball seating 1, described ball seating 1 sidepiece is circumferentially provided with 3 fixing devices, and is uniformly distributed circumferentially at ball seating 1 sidepiece, ball-and-socket wall is arranged fixing device corresponding and through hole, fixing device comprises the clamping drive mechanism 2 of the clamp 4 and driving clamp telescopic moving being arranged at and also can stretching into ball-and-socket in described through hole, this clamping drive mechanism 2 is cylinder, described clamp 4 is connected to the piston rod of cylinder, and the end face that this clamp 4 contacts with bulb is cambered surface, the bottom of described ball seating 1 be provided with stretch into ball-and-socket enter a detector switch 5, the detection through hole of through ball-and-socket is provided with bottom described ball seating 1, described enter a detector switch 5 comprise flange sleeve 6, inductor, gauge head 7 and spring 8, flange sleeve 6 is threaded onto described detection through hole and is installed by screw fixing, flange sleeve 6 hollow cavity two ends are all installed with the end cap being provided with through hole, gauge head 7 is provided with axial limiting end face, gauge head 7 is placed in the hollow cavity of flange sleeve 6 by the restriction of this axial limiting end face, and be positioned at hollow cavity top by described spring 8 support being placed in flange sleeve hollow cavity, gauge head 7 head passes the through hole of the described end cap of ball-and-socket side and stretches in ball-and-socket, described inductor head penetrate flange sleeve 6 hollow cavity and and gauge head 7 interval arrange.
When the present invention uses, first this bulb mechanism is fixed on the three-dimensional numerical control posture adjustment steady arm top of X, Y, Z tri-the direction translation freedoms had along right angle three-coordinate, then the bulb of the mount pad 3 being connected with aircraft components bracket is inserted in ball seating 1, enter a detector switch 5 detect bulb enter position qualified after, just can carry out the pose adjustment in 6 orientation to fuselage, after fuselage pose adjustment, start fixing device, be fixedly clamped by mount pad, whole posture adjustment work is complete.
The above is only preferred embodiment of the present invention, not does any pro forma restriction to structure of the present invention.Every above embodiment is done according to technical spirit of the present invention any simple modification, equivalent variations and modification, all fall within the scope of protection of the present invention.
Claims (4)
1. transporation by plane posture adjustment ball head device, it is characterized in that: described ball head device comprises ball seating (1) and the mount pad (3) for being connected support aircraft components bracket, described mount pad (3) top is butt flange, bottom is fixedly connected with a bulb by pipe link, described ball seating (1) pedestal center arranges mount pad installation cavity, this installation cavity bottom is the ball-and-socket corresponding with described bulb, and the bulb of described mount pad (3) is placed in described ball seating (1); Described ball seating (1) sidepiece is circumferentially provided with at least 2 fixing devices, ball-and-socket wall arranges the through hole corresponding with fixing device, and fixing device comprises the clamp (4) being arranged at and also can stretching into ball-and-socket in described through hole and the clamping drive mechanism (2) driving clamp telescopic moving; The bottom of described ball seating (1) be provided with stretch into ball-and-socket enter a detector switch (5).
2. transporation by plane posture adjustment ball head device according to claim 1, is characterized in that: described fixing device quantity is 3, and is uniformly distributed circumferentially at ball seating (1) sidepiece.
3. transporation by plane posture adjustment ball head device according to claim 2, is characterized in that: described clamping drive mechanism (2) is cylinder, and described clamp (4) is connected to the piston rod of cylinder, and the end face that this clamp (4) contacts with bulb is cambered surface.
4. transporation by plane posture adjustment ball head device according to claim 3, it is characterized in that: described ball seating (1) bottom is provided with the detection through hole of through ball-and-socket, described enter a detector switch (5) comprise flange sleeve (6), inductor, gauge head (7) and spring (8), flange sleeve (6) is threaded onto described detection through hole and is installed by screw fixing, flange sleeve (6) hollow cavity two ends are all installed with the end cap being provided with through hole, gauge head (7) is provided with axial limiting end face, gauge head (7) is placed in the hollow cavity of flange sleeve (6) by the restriction of this axial limiting end face, and be positioned at hollow cavity top by described spring (8) support being placed in flange sleeve hollow cavity, gauge head (7) head passes the through hole of the described end cap of ball-and-socket side and stretches in ball-and-socket, described inductor head penetrate flange sleeve (6) hollow cavity and and gauge head (7) interval arrange.
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 true CN105539876A (en) | 2016-05-04 |
| CN105539876B 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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| CN (1) | CN105539876B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106826171A (en) * | 2017-03-09 | 2017-06-13 | 尚鳌自动化工程（上海）有限公司 | The anti-escape bulb of bolt-type enters a device and its application method |
| CN107263351A (en) * | 2017-05-09 | 2017-10-20 | 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 |
| CN108247555A (en) * | 2016-12-28 | 2018-07-06 | 大连四达高技术发展有限公司 | Flexural pivot clamping and stress monitor device and method based on big component flexible docking |
| CN109171986A (en) * | 2018-09-30 | 2019-01-11 | 泗洪县正心医疗技术有限公司 | Operating robot and its control device based on cup-and-ball joint and touch 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 |
| CN112192264A (en) * | 2020-11-30 | 2021-01-08 | 中国航空制造技术研究院 | Flexible supporting mechanism for automatic hole making of machine body |
| CN114871799A (en) * | 2022-05-18 | 2022-08-09 | 中航沈飞民用飞机有限责任公司 | Flexible frock of modularization is riveted towards automatic brill |
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| 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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| US20010054228A1 (en) * | 1999-06-26 | 2001-12-27 | Daimlerchrysler Aerospace Airbus Gmbh | Method and apparatus for assembling a three-dimensional structural component |
| CN2830053Y (en) * | 2005-08-19 | 2006-10-25 | 河南安彩高科股份有限公司 | Probe of press |
| CN101362326A (en) * | 2008-09-26 | 2009-02-11 | 浙江大学 | Follow-up locater based on air flotation and universal ball seat |
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Cited By (15)
| 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 | Flexural pivot clamping and stress monitor device and method based on big component flexible docking |
| CN108247555A (en) * | 2016-12-28 | 2018-07-06 | 大连四达高技术发展有限公司 | Flexural pivot clamping and stress monitor device and method based on big component flexible docking |
| CN106826171A (en) * | 2017-03-09 | 2017-06-13 | 尚鳌自动化工程（上海）有限公司 | The anti-escape bulb of bolt-type enters a device and its application method |
| 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 |
| CN107263351A (en) * | 2017-05-09 | 2017-10-20 | 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 |
| CN109171986B (en) * | 2018-09-30 | 2021-07-16 | 泗洪县正心医疗技术有限公司 | Surgical robot based on ball-and-socket joint and tactile feedback and control device thereof |
| CN109171986A (en) * | 2018-09-30 | 2019-01-11 | 泗洪县正心医疗技术有限公司 | Operating robot and its control device based on cup-and-ball joint and touch 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 |
| CN112192264A (en) * | 2020-11-30 | 2021-01-08 | 中国航空制造技术研究院 | Flexible supporting mechanism for automatic hole making of machine body |
| CN114871799A (en) * | 2022-05-18 | 2022-08-09 | 中航沈飞民用飞机有限责任公司 | Flexible frock of modularization is riveted towards automatic brill |
| 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 |
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| CN105539876B (en) | 2018-12-18 |
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