CN101829900A - Layout method of grand cross butting locator of aircraft wing body - Google Patents
Layout method of grand cross butting locator of aircraft wing body Download PDFInfo
- Publication number
- CN101829900A CN101829900A CN 201010136786 CN201010136786A CN101829900A CN 101829900 A CN101829900 A CN 101829900A CN 201010136786 CN201010136786 CN 201010136786 CN 201010136786 A CN201010136786 A CN 201010136786A CN 101829900 A CN101829900 A CN 101829900A
- Authority
- CN
- China
- Prior art keywords
- wing
- locator
- fuselage
- locators
- auxiliary
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Automatic Assembly (AREA)
Abstract
The invention discloses a layout method of a grand cross butting locator of an aircraft wing body. An aircraft body and wings of an aircraft are in grand cross butting way; the whole aircraft body adopts 4 aircraft body main locators and 3 aircraft body auxiliary locators comprising 2 rear aircraft body auxiliary locators and 1 front aircraft body auxiliary locator, and the aircraft body locators and the aircraft body are in spherical hinge connection way; the whole wings adopt 4 wing main locators and 2 wing auxiliary locators, the wing main locators and the wings are in spherical hinge connection way, and the wing auxiliary locators and the wings are in vacuum chuck connection way. A grand cross butting way is adopted, large space is provided for the butting operation of a center wing and external wings, and the invention is easy to realize digital and mechanical drilling and ensures the processing efficiency and quality.
Description
Technical field
The present invention relates to a kind of aircraft wing body grand cross butt joint locator layout method.
Background technology
In the aircraft manufacturing field, the manufacture process of aircraft always earlier is assembled into assembly with part, and component assembling is become widget, and widget is assembled into airframe and wing, at last airframe and wing is docked assembling.The aircraft mounting technology is one of weak link of Chinese aircraft industry, in order to improve the efficient and the quality of airframe, wing butt joint assembling, just must change traditional aircraft general assembly pattern at present based on analog quantity, and then a kind of aircraft wing body grand cross butt joint locator layout designs proposed, in aircraft wing, fuselage butt joint assembling process, can realize involutory, the laser tracking measurement of the accurate posture adjustment of digitlization, take into full account the passability of manually-operated space accessibility and airframe, wing and complete machine simultaneously.
Summary of the invention
The purpose of this invention is to provide a kind of aircraft wing body grand cross butt joint locator layout method.
Aircraft wing body grand cross butt joint locator layout method is: the fuselage of aircraft and wing adopt the grand cross docking mode; Integral body adopts 4 fuselage master locators and 3 fuselage auxiliary locators, comprising 2 rear body auxiliary locators and 1 forebody auxiliary locator, adopts the ball pivot connected mode between fuselage locator and the fuselage; Whole wing adopts 4 wing master locators and 2 wing auxiliary locators, adopts the ball pivot connected mode between wing master locator and the wing, adopts the vacuum cup connected mode between wing auxiliary locator and the wing.
Forebody auxiliary locator bottom is provided with artificial travelling car in the described aircraft wing body grand cross butt joint locator layout method.Locator can move along three coordinate directions in the described aircraft wing body grand cross butt joint locator layout method.
Advantage of the present invention: 1) adopt the grand cross docking mode, central wing and outer wing docking operation space are big, realize digitlization, mechanization drilling easily, guarantee working (machining) efficiency and quality; 2) adopt the grand cross docking mode, the butt joint assembling earlier of central wing and middle outer wing not only helps seal construction, and is convenient to leakage check, guarantees the seal request of integral tank; 3) adopt the grand cross docking mode, left and right outer wing and central wing can simultaneously or successively be carried out pre-connection, carry out symmetry then and measure, and guarantee the symmetry of whole wing easily; 4) adopt the grand cross docking mode, whole wing is convenient to organization of production and management as parts of general assembly, the production efficiency height, and quality is guaranteed, meets the general trend that aircraft strange land modularization is made; 5) posture adjustment that takes into full account fuselage of the layout of fuselage master locator requires the trafficability characteristic with aircraft; 6) layout of fuselage auxiliary locator has taken into full account the butt joint requirement of the auxiliary fixing of fuselage and fuselage, wing; 7) posture adjustment that takes into full account wing of the layout of wing master locator requires the trafficability characteristic with aircraft; 8) layout of wing auxiliary locator has taken into full account the design feature and the auxiliary fixing requirement of wing.
Description of drawings
Fig. 1 fuselage locator layout front view;
Fig. 2 wing locator layout vertical view;
Fig. 3 wing locator layout front view;
Fig. 4 wing locator layout vertical view;
Fig. 5 aircraft wing fuselage grand cross butt joint locator layout front view;
Fig. 6 aircraft wing fuselage grand cross butt joint locator layout vertical view;
Among the figure: auxiliary locator 2, the preceding auxiliary locator 3 of fuselage, wing master locator 4, wing auxiliary locator 5 behind fuselage master locator 1, the fuselage.
The specific embodiment
Shown in accompanying drawing 1,2,3,4,5,6, aircraft wing body grand cross butt joint locator layout method is characterized in that the fuselage of aircraft and wing adopt the grand cross docking mode; Integral body adopts 4 fuselage master locators and 3 fuselage auxiliary locators, comprising 2 rear body auxiliary locators and 1 forebody auxiliary locator, adopts the ball pivot connected mode between fuselage locator and the fuselage; Whole wing adopts 4 wing master locators and 2 wing auxiliary locators, adopts the ball pivot connected mode between wing master locator and the wing, adopts the vacuum cup connected mode between wing auxiliary locator and the wing.
Forebody auxiliary locator bottom is provided with artificial travelling car in the described aircraft wing body grand cross butt joint locator layout method.Locator can move along three coordinate directions in the described aircraft wing body grand cross butt joint locator layout method.
Locator is the final executing agency of posture adjustment, docking system, comprises locator basic machine and electric driving control, has automation mechanized operation and two kinds of patterns of manual operations.Locator is divided into auxiliary locator 3 and wing master locator 4 before auxiliary locator 2 behind fuselage master locator 1, the fuselage, the fuselage, wing auxiliary locator 5 according to Support Position and carrying different.
Its middle machine body locator comprises 4 fuselage master locators 1, is used for realizing that the fuselage attitude is adjusted and support, finishes the butt joint of wing body grand cross, take into full account fuselage and accurately go into the convenience and the security requirement of position, be connected with the process connection formation ball-and-socket hinge style on the fuselage, three-dimensional control, self adaptation is gone into the position; Auxiliary locator 2 behind 2 fuselages is used for the whole fuselage of supplemental support, does not participate in the adjustment of fuselage attitude, improves the stability of wing body grand cross docking operation.Be connected with the process connection formation ball-and-socket hinge style on the fuselage, three-dimensional control, self adaptation is gone into the position; Auxiliary locator 3 before 1 fuselage is used for the supplemental support airframe, does not participate in the adjustment of fuselage attitude, and auxiliary fuselage master locator is finished the butt joint of wing body grand cross, guarantees the stable of docking operation.In order to satisfy the space requirement of testing with undercarriage control of moving of aircraft, the preceding auxiliary locator of fuselage manually shift-in shifts out, and realizes locating fast the bolt connection with the taper hole on the pre-embedded steel slab of ground.Be connected with the process connection formation ball-and-socket hinge style on the fuselage, three-dimensional control, self adaptation is gone into the position.
The wing locator comprises 4 wing master locators 4, is used for realizing the attitude adjustment and the support of wing, realizes docking of wing and fuselage by the cooperative motion between a plurality of locators.Take into full account wing and go into the convenience of position, posture adjustment, docking operation, security requirement.Be connected three-dimensional control with the process connection formation ball-and-socket hinge style on the wing; 2 wing auxiliary locators 5, treat that the wing attitude is determined after, be used for the supplemental support wing.Vacuum cup by the locator top contacts with wing cover, improves the fixing stability of wing assembling.
Use step of the present invention as follows:
1. fuselage is gone into position and posture adjustment
1) locator self check, each locator resets.Before its middle machine body master locator 1 and the fuselage auxiliary locator 3 along Y to move to appointment with fuselage interference position not; 2) integral body is gone into the position by trailer traction, fuselage master locator 1 along Y to moving into the position; 3) 4 fuselage master digital control location devices 1 are gone into the position successively, reach given load after, the jack-up fuselage that rises synchronously makes the undercarriage built on stilts; 4) based on the measurement result of laser tracker, the attitude adjustment of integral body is finished in 1 co-operating of fuselage master digital control location device, carries out the attitude evaluation, the locking process connection; 5) auxiliary locator 2 is assisted and is held fuselage and lock process connection with stepping into the position behind the fuselage; 6) manually promote to be inducted into the position by taper hole after auxiliary locator 3 arrives assigned addresses before the fuselage, bolt is connected and fixed, and auxiliaryly holds fuselage and locks process connection.
2 wings are gone into position and posture adjustment
1) whole wing lifts body upper, and 1 wing master digital control location device 4 is gone into the position, locking technology bulb; Other 3 wing master digital control location devices 4 are gone into the position successively, and bulb is not locked; 2) wing master digital control location device 4 unclamps the technology bulb, wing master digital control location device 4 synchronous rising jack-up whole wings, and suspender is withdrawn; 3) based on the measurement result of laser tracker, 4 pairs of wings of wing master digital control location device carry out posture adjustment and attitude evaluation, locking technology bulb; 4) wing supplemental support locator 5 rises, and supports wing in appointed positions, and the locator top chuck vacuumizes auxiliary fixing wing.
3 wing bodies butt joint technical process
1) wing is protected attitude decline, finishes fuselage major joint and the inserting of wing major joint by operated by handwheel; 2) grand cross of manually finishing wing and fuselage is connected, and wing and the butt joint of fuselage grand cross are carried out quality evaluation, and the result deposits database in; 3) after the aircraft assembling is finished, fall wing auxiliary locator 5, wing master digital control location device 4; 4) falling before the fuselage auxiliary locator 3 decline pushers successively walks), auxiliary locator 2, fuselage master digital control location device 1 land the undercarriage of aircraft behind the fuselage; 5) after moving to home, aircraft changes the station by trailer traction along Y for fuselage master locator 1.
Claims (3)
1. an aircraft wing body grand cross butt joint locator layout method is characterized in that the fuselage of aircraft and wing adopt the grand cross docking mode; Integral body adopts 4 fuselage master locators (1) and 3 fuselage auxiliary locators, comprising 2 rear body auxiliary locators (2) and 1 forebody auxiliary locator (3), adopts the ball pivot connected mode between fuselage locator and the fuselage; Whole wing adopts 4 wing master locators (4) and 2 wing auxiliary locators (5), adopts the ball pivot connected mode between wing master locator (4) and the wing, adopts the vacuum cup connected mode between wing auxiliary locator (5) and the wing.
2. a kind of aircraft wing body grand cross butt joint locator layout method according to claim 1 is characterized in that described forebody auxiliary locator (3) bottom is provided with artificial travelling car.
3. a kind of aircraft wing body grand cross butt joint locator layout method according to claim 1 is characterized in that described locator can move along three coordinate directions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010136786 CN101829900B (en) | 2010-03-30 | 2010-03-30 | Layout method of grand cross butting locator of aircraft wing body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010136786 CN101829900B (en) | 2010-03-30 | 2010-03-30 | Layout method of grand cross butting locator of aircraft wing body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101829900A true CN101829900A (en) | 2010-09-15 |
| CN101829900B CN101829900B (en) | 2012-11-28 |
Family
ID=42714195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010136786 Expired - Fee Related CN101829900B (en) | 2010-03-30 | 2010-03-30 | Layout method of grand cross butting locator of aircraft wing body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101829900B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
| CN103171772A (en) * | 2013-03-11 | 2013-06-26 | 浙江大学 | System and layout method for airframe three-section involution and intersection hole machining |
| CN106697326A (en) * | 2015-11-06 | 2017-05-24 | 波音公司 | Advanced automated process for the wing-to-body join of an aircraft with predictive surface scanning |
| CN107020597A (en) * | 2017-04-21 | 2017-08-08 | 陕西飞机工业（集团）有限公司 | A kind of process assembled for aircraft big opening |
| CN107148384A (en) * | 2014-08-11 | 2017-09-08 | 埃姆普里萨有限公司 | For test device, the system and method for the clearance for statically determining flying vehicles control surface |
| CN107263044A (en) * | 2017-04-27 | 2017-10-20 | 浙江大学 | A kind of design method for the large aircraft outer wing wing box assembly system for considering cause of deformation |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB511762A (en) * | 1938-04-09 | 1939-08-23 | Messerschmitt Boelkow Blohm | Improvements in and relating to the construction or erection of large bodies, such as aircraft parts |
| EP0900726A1 (en) * | 1997-09-04 | 1999-03-10 | British Aerospace Public Limited Company | Manufacture of aircraft |
| DE19836366A1 (en) * | 1998-08-11 | 2000-02-24 | Delu Luftkissen | Support and transporting trestle for heavy load incorporates transverse beams holding telescopic rods extending vertically upward and may include air cushion arrangement |
| US20060266885A1 (en) * | 2005-05-26 | 2006-11-30 | Hardaker John C | Wing positioner for installing and removing an aircraft wing |
| CN101081643A (en) * | 2006-05-30 | 2007-12-05 | 空中客车德国有限公司 | Wings fixation |
| WO2009044362A2 (en) * | 2007-10-03 | 2009-04-09 | Alenia Aeronautica S.P.A. | A method of manufacturing wing structures. |
-
2010
- 2010-03-30 CN CN 201010136786 patent/CN101829900B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB511762A (en) * | 1938-04-09 | 1939-08-23 | Messerschmitt Boelkow Blohm | Improvements in and relating to the construction or erection of large bodies, such as aircraft parts |
| EP0900726A1 (en) * | 1997-09-04 | 1999-03-10 | British Aerospace Public Limited Company | Manufacture of aircraft |
| DE19836366A1 (en) * | 1998-08-11 | 2000-02-24 | Delu Luftkissen | Support and transporting trestle for heavy load incorporates transverse beams holding telescopic rods extending vertically upward and may include air cushion arrangement |
| US20060266885A1 (en) * | 2005-05-26 | 2006-11-30 | Hardaker John C | Wing positioner for installing and removing an aircraft wing |
| CN101081643A (en) * | 2006-05-30 | 2007-12-05 | 空中客车德国有限公司 | Wings fixation |
| WO2009044362A2 (en) * | 2007-10-03 | 2009-04-09 | Alenia Aeronautica S.P.A. | A method of manufacturing wing structures. |
Non-Patent Citations (2)
| Title |
|---|
| 《航空制造技术》 20080430 邹方等 飞机总装自动化校准对接系统 第32页至第35页 1-3 , 第7期 2 * |
| 《航空制造技术》 20100131 王建华 飞机总装对接技术 第32页至第35页 1-3 , 第2期 2 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
| CN103171772A (en) * | 2013-03-11 | 2013-06-26 | 浙江大学 | System and layout method for airframe three-section involution and intersection hole machining |
| CN107148384A (en) * | 2014-08-11 | 2017-09-08 | 埃姆普里萨有限公司 | For test device, the system and method for the clearance for statically determining flying vehicles control surface |
| CN107148384B (en) * | 2014-08-11 | 2020-07-24 | 埃姆普里萨有限公司 | Test device, system and method for statically determining the play of an aircraft control surface |
| CN106697326A (en) * | 2015-11-06 | 2017-05-24 | 波音公司 | Advanced automated process for the wing-to-body join of an aircraft with predictive surface scanning |
| CN107020597A (en) * | 2017-04-21 | 2017-08-08 | 陕西飞机工业（集团）有限公司 | A kind of process assembled for aircraft big opening |
| CN107263044A (en) * | 2017-04-27 | 2017-10-20 | 浙江大学 | A kind of design method for the large aircraft outer wing wing box assembly system for considering cause of deformation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101829900B (en) | 2012-11-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101829900B (en) | Layout method of grand cross butting locator of aircraft wing body | |
| CN101850850B (en) | Layout method of central airframe digital assembly of big plane | |
| CN108001708B (en) | Airplane wing butt joint posture adjusting reconfigurable device | |
| CN111238375B (en) | Laser tracker-based appearance reconstruction method for large-scale component of mobile detection robot | |
| CN102730199B (en) | Large-opening shape-preserving device used for large-scale airplane assembly | |
| CN106862908B (en) | A kind of full-automatic assembly interconnection method based on air flotation technology | |
| CN111673152B (en) | Manufacturing method of cabin body suitable for lunar exploration orbital vehicle | |
| CN105354360A (en) | Method for closed-loop establishment of coordinate measuring control network in aircraft large-component assembling interface finish machining | |
| CN103785874B (en) | A kind of method using numerical control device to process aircraft engine suspending assembly bolt hole | |
| CN103171772A (en) | System and layout method for airframe three-section involution and intersection hole machining | |
| CN112977874A (en) | Integrally movable large part butt joint and finish machining system | |
| CN109115211A (en) | A kind of plant area's high-precision personnel positioning method and positioning system | |
| CN105300339A (en) | Method And Apparatus For Aligning Segments | |
| CN202716050U (en) | Machine body siding folding flexible positioning device | |
| CN104477402A (en) | Airframe butt joint attitude-adjusting method meeting stringer reference alignment and straightness requirements | |
| CN108528755B (en) | Digital installation method of acceleration sensor | |
| CN109204871A (en) | One kind being used for aircraft wing integral panel posture adjustment positioning system and its application method | |
| CN102975866A (en) | Self-adaptive flexible airplane assembly device and method | |
| CN102205480B (en) | Method for manufacturing spatial curved surface spiral box type component | |
| CN108247312B (en) | High-precision assembly process of multipoint compression type large-scale equipment | |
| CN104647246A (en) | Double-rotating coordinate numerical control posture alignment platform | |
| US9643738B2 (en) | Loading of aircraft landing gear | |
| CN111093145A (en) | Positioning system and positioning method of mowing robot | |
| CN103895878B (en) | A kind of large aircraft rear body Digital assembly system | |
| CN103963992B (en) | Aircraft iron bird testing stand undercarriage and the installation method of hatch door |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| ASS | Succession or assignment of patent right |
Owner name: XI AN AIRCRAFT INDUSTRY (GROUP) CO., LTD. |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20110803 Address after: 310027 Hangzhou, Zhejiang Province, Xihu District, Zhejiang Road, No. 38, No. Applicant after: Zhejiang University Co-applicant after: Xi'an Aircraft Industry Group Co., Ltd. Address before: 310027 Hangzhou, Zhejiang Province, Xihu District, Zhejiang Road, No. 38, No. Applicant before: Zhejiang University |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121128 Termination date: 20140330 |