CN106043661B - A kind of artificial rapid abutting joint method of fuselage wing - Google Patents
A kind of artificial rapid abutting joint method of fuselage wing Download PDFInfo
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- CN106043661B CN106043661B CN201610400433.5A CN201610400433A CN106043661B CN 106043661 B CN106043661 B CN 106043661B CN 201610400433 A CN201610400433 A CN 201610400433A CN 106043661 B CN106043661 B CN 106043661B
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- fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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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
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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- Orthopedics, Nursing, And Contraception (AREA)
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Abstract
The present invention relates to a kind of artificial rapid abutting joint methods of fuselage wing, belong to the baby plane fuselage wing artificial rapid abutting joint method field of fork ear formula fuselage wing docking structure.The present invention selects docking benchmark, pitches ear formula docking structure, and fuselage of being subject to docks wing, and docking benchmark is made of upper and lower benchmark, front and back benchmark, left and right benchmark；The upper auricle nipple orifice of upper and lower selection of reference frame maximum distance is that docking benchmark is positioned；Front and back reference position degree of freedom is positioned on the basis of intermediate lower contact auricle end face；Left and right reference position degree of freedom is positioned on the basis of intermediate lower contact auricle hole；The baby plane of more intersection points, high-precision, uncompensated fuselage wing docking structure is solved when army outfield and wartime etc. do not have advanced docking technique equipment and means, it realizes and quickly, manually docks, realize Fast-Maintenance and maintenance, opportunity of combat flight-line service is improved, existence of the opportunity of combat under the extreme unfavorable conditions in wartime, operational efficiency are improved.
Description
Technical field
The present invention relates to a kind of artificial rapid abutting joint methods of fuselage wing, belong to the small of fork ear formula fuselage wing docking structure
Type airframe wing artificial rapid abutting joint method field.
Background technology
The opportunity of combat of three generations or more makes aircraft be wanted with high aerodynamic configuration the requirements such as high maneuverability, high structural strength
It asks outer, also wants stringent control structure weight, thus design much using fork ear formula fuselage wing docking structure.Because air speed,
Overload, the difference of aerodynamic arrangement, small-sized opportunity of combat ear V shape fuselage wing mate are typically located on 4-5 load frame, have
The connector of 7-9 groups or so has the characteristics that more to contact point；Every group uses E9 mostly to contact point（Body joint hole）/f9（It is right
Connecting bolt）/H8（Wing Joint hole）Cooperation has the characteristics that cooperation is with high accuracy；Butt hole concentricity is in butt hole centre deviation
When no more than 0.15mm, allows to force assembly, have the characteristics that no design compensation.To solve the coaxial of fuselage wing mate
Degree problem, domestic and international planemaker are substantially all by the way of component finishing, are set by automatic butt in assembly workshop
Standby or auxiliary mould realizes the docking of fuselage wing.
Automatic butt equipment and numerous will not be equipped with substantially due to high expense, in the outfields such as army, system shop, field
Auxiliary butting tooling, if needing to decompose fuselage wing in outfield, and overhauled, repaired, maintaining when,
It is substantially only capable of carrying out the dismounting of fuselage wing by most basic bracket, personnel and tool.If in wartime, not only tooling device
It can not ensure, also to realize artificial fast assembling-disassembling, maintenance, to improve the viability and fighting capacity in battlefield, win future war.Cause
This, find it is a kind of it is artificial, fast implement the more intersection points of baby plane, high-precision, the method for uncompensated fuselage wing docking and seem outstanding
It is important.
Invention content
The present invention is in order to overcome drawbacks described above, and its purpose is to provide a kind of artificial rapid abutting joint method of fuselage wing, mesh
Be to solve the baby plane of more intersection points, high-precision, uncompensated fuselage wing docking structure in army outfield and wartime etc.
When not having advanced docking technique equipment and means, realizes quick, artificial docking, realize Fast-Maintenance and maintenance, improve and fight
Machine flight-line service improves existence of the opportunity of combat under the extreme unfavorable conditions in wartime, operational efficiency.
The present invention to achieve the goals above, adopts the following technical scheme that：
A kind of artificial rapid abutting joint method of fuselage wing：
Selection docking benchmark, pitches ear formula docking structure, and fuselage of being subject to docks wing, docking benchmark by upper and lower benchmark,
Front and back benchmark, left and right benchmark are constituted；
The upper auricle nipple orifice of upper and lower selection of reference frame maximum distance is that docking benchmark is positioned；
Front and back reference position degree of freedom is positioned on the basis of intermediate lower contact auricle end face；
Left and right reference position degree of freedom is positioned on the basis of intermediate lower contact auricle hole；
It is as follows：
A）, check fuselage, the surface quality at wing mate and interface, clear up fifth wheel on connector, smear
Lubricating grease；
B）, according to docking selection of reference frame requirement, it is primary carry out up and down, the docking of benchmark around；
C）, after benchmark docked, coaxality measurement is carried out to remaining each connection intersection point, concentricity meets design concentricity and wants
After asking, the connection installation of intersection point bolt is carried out；
D）, each system carries out reassembling for shoulder cowling, fuselage wing has docked after installation is complete at fuselage wing docking
At.
Further,
In step B）In：The 2nd interface frame, mating frame and last 1 interface frame, mating frame top connection intersection point are adjusted in place with wing bracket first,
With the concentricity for examining pin inspection hole after being adjusted in place, positioning company is carried out to the 2nd interface frame, mating frame and last 1 interface frame, mating frame top connection intersection point
It connects, reference position degree of freedom above and below control wing；
When docking, the intersection point of the 2nd interface frame, mating frame and last 1 interface frame, mating frame is first connected, other intersection points are then connected；
If the 2nd interface frame, mating frame on an axis, actually just controls one with last 1 interface frame, mating frame top connection crossing point holes
Pivot center；
After 2nd interface frame, mating frame controls in place with last 1 interface frame, mating frame top connection intersection point, slowly reduces wing and height, profit are installed
Slowly the 2nd interface frame, mating frame lower contact auricle of wing is inserted under fuselage in auricle, with the 2nd interface frame, mating frame lower contact of fuselage with wing dead weight
It is positioned on the basis of end face before or after intermediate auricle, controls reference position degree of freedom before and after wing；
Wing location status is adjusted, checks and adjusts the 2nd interface frame, mating frame and dock the coaxial of frame bottom connector everywhere with last 1
Degree, concentricity state of being subject to are best：Both all inspection pins in lower part were maximum, were located by connecting to crossing point holes under the 2nd interface frame, mating frame,
Control wing or so reference position degree of freedom.
Beneficial effects of the present invention：
The invention makes aircraft in the outfields such as army, system shop, field, can be only when for fork ear formula fuselage wing docking
Rapid abutting joint can be completed by taking bracket, attachment tools and a small amount of personnel, the economization tooling expense of writing, and with very high
Docking efficiency, the outfield for improving opportunity of combat is maintainable, to improve existence, the operational efficiency of aircraft.The invention is applicable in
In more intersection points, fork ear formula baby plane is quick, the docking of artificial fuselage wing, has universal guidance, dissemination.
Description of the drawings
Fig. 1 is wing mate schematic diagram on the left of Typical Aircraft（Right side is symmetrical）.
The 1st interface frame, mating frame intersection points of 1- in figure, the 2nd interface frame, mating frame intersection points of 2-, the 3rd interface frame, mating frame intersection points of 3-, the 4th interface frame, mating frame intersection points of 4-,
The 5th interface frame, mating frame intersection points of 5-.
Specific implementation mode
The present invention will be described in detail with reference to the accompanying drawings of the specification：
It is subject to fuselage when docking, with bracket fixed main body, allows wing toward docking on fuselage.Fig. 1 is typical small-sized winged
Machine pitch ear formula fuselage wing docking typical structure, by taking right side as an example, be followed successively by from front to back the 1st interface frame, mating frame intersection point 1, the 2nd pair
Frame intersection point 2, the 3rd interface frame, mating frame intersection point 3, the 4th interface frame, mating frame intersection point 4, the 5th interface frame, mating frame intersection point 5 are connect, wherein except the 1st interface frame, mating frame intersection point is
Outside Intersection Point, remaining interface frame, mating frame is upper and lower two groups to contact point.By taking Fig. 1 as an example, butt-joint process flow and requirement are as follows：
A, it checks the surface quality at fuselage, wing mate and interface, clears up fifth wheel on connector, smear profit
Consistent lubricant.
B, the 2nd, the 5th interface frame, mating frame top connection intersection point is adjusted in place with wing bracket first, with inspection pin after being adjusted in place
The concentricity of inspection hole is located by connecting to the 2nd, the 5th interface frame, mating frame top connection intersection point, control wing upper and lower position degree of freedom.
In view of manually can first be connected the 2nd or the 5th intersection point when reality is docked with the operability of bracket docking adjustment, then connected
Another intersection point.If the 2nd, the 5th interface frame, mating frame top connection crossing point holes are on an axis, a rotation axis is actually just controlled
Line.
C, it after the control in place of the 2nd, the 5th interface frame, mating frame top connection intersection point, slowly reduces wing and height is installed, certainly using wing
The 2nd interface frame, mating frame lower contact auricle of wing is slowly inserted under fuselage in auricle by weight, with auricle among the 2nd interface frame, mating frame lower contact of fuselage
It is positioned on the basis of front or rear end face, before and after control wing（Course）Position freedom.It is required that being carried out at any time in insertion process
It adjusts, is not allow for forcing.
D, wing location status is adjusted, the concentricity of the 2-the 5 frame bottom connector everywhere is checked and adjust, with concentricity
Subject to state is best（Both all inspection pins in lower part were maximum）, it is located by connecting to crossing point holes under the 2nd interface frame, mating frame, control wing is left
Right position freedom.
E, at above-mentioned three after intersection point connection, wing positions completely, is carried out with to connecting bolt at this point, carrying out remaining intersection point
Connection.
F, each system carries out the equipped of shoulder cowling after installation is complete at the docking of fuselage wing, and the docking of fuselage wing is completed.
Points for attention：Wing is adjusted, can reduce docking stress taking human as weak vibrations bracket in docking operation；Sternly
Prohibit barbarous operation fuselage or wing are caused to damage.
Claims (2)
1. a kind of artificial rapid abutting joint method of fuselage wing, the interconnection method are characterized in that：
Docking benchmark is made of upper and lower benchmark, front and back benchmark, left and right benchmark；
The upper auricle nipple orifice of upper and lower selection of reference frame maximum distance is that docking benchmark is positioned；
Front and back reference position degree of freedom is positioned on the basis of intermediate lower contact auricle end face；
Left and right reference position degree of freedom is positioned on the basis of intermediate lower contact auricle hole；
It is as follows：
A）, check fuselage, the surface quality at wing mate and interface, clear up fifth wheel on connector, smear lubrication
Fat；
B）, according to docking selection of reference frame requirement, it is primary carry out up and down, the docking of benchmark around；
C）, after benchmark docked, coaxality measurement is carried out to remaining each connection intersection point, concentricity meets design concentricity requirement
Afterwards, the connection installation of intersection point bolt is carried out；
D）, each system carries out reassembling for shoulder cowling, the docking of fuselage wing is completed after installation is complete at fuselage wing docking.
2. the artificial rapid abutting joint method of fuselage wing according to claim 1, it is characterised in that：
In step B）In：The 2nd interface frame, mating frame and last 1 interface frame, mating frame top connection intersection point are adjusted in place with wing bracket first, adjusted
It is located by connecting afterwards to the 2nd interface frame, mating frame and last 1 interface frame, mating frame top connection intersection point with the concentricity for examining pin inspection hole in place,
Control wing reference position degree of freedom up and down；
When docking, the intersection point of the 2nd interface frame, mating frame and last 1 interface frame, mating frame is first connected, other intersection points are then connected；
If the 2nd interface frame, mating frame on an axis, actually just controls a rotation with last 1 interface frame, mating frame top connection crossing point holes
Axis；
After 2nd interface frame, mating frame controls in place with last 1 interface frame, mating frame top connection intersection point, slowly reduces wing and height is installed, utilize machine
The 2nd interface frame, mating frame lower contact auricle of wing is slowly inserted under fuselage in auricle, among the 2nd interface frame, mating frame lower contact of fuselage by wing dead weight
It is positioned on the basis of end face before or after auricle, controls reference position degree of freedom before and after wing；
Wing location status is adjusted, the concentricity that the 2nd interface frame, mating frame docks frame bottom connector everywhere with last 1 is checked and adjust, with
Subject to concentricity state is best：That is the inspection pin of all insertions of lower connector all meets design requirement, to intersection point under the 2nd interface frame, mating frame
Hole is located by connecting, control wing or so reference position degree of freedom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610400433.5A CN106043661B (en) | 2016-06-08 | 2016-06-08 | A kind of artificial rapid abutting joint method of fuselage wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610400433.5A CN106043661B (en) | 2016-06-08 | 2016-06-08 | A kind of artificial rapid abutting joint method of fuselage wing |
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| Publication Number | Publication Date |
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| CN106043661A CN106043661A (en) | 2016-10-26 |
| CN106043661B true CN106043661B (en) | 2018-08-24 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111563904B (en) * | 2020-04-30 | 2021-04-30 | 南京航空航天大学 | Wing fork ear point cloud segmentation method based on three-dimensional feature descriptor |
| CN111746818B (en) * | 2020-06-12 | 2024-07-19 | 陕西飞机工业（集团）有限公司 | Method for mounting spoiler of airplane |
| CN112455717A (en) * | 2020-12-12 | 2021-03-09 | 江西洪都航空工业集团有限责任公司 | Wing body assembling and folding platform with transportation function |
| CN113247299B (en) * | 2021-07-16 | 2021-09-28 | 成都飞机工业（集团）有限责任公司 | Wing body finish machining system and method for rapid assembly of airplane |
| CN113664530B (en) * | 2021-09-06 | 2022-09-13 | 上海航天精密机械研究所 | Positioning device and assembling method for boosting tail section type frame tail butt joint |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0901228D0 (en) * | 2009-01-26 | 2009-03-11 | Airbus Uk Ltd | Aircraft joint |
| CN102060100B (en) * | 2010-12-14 | 2013-03-27 | 钱智声 | Aircraft fuselage-wing connecting mechanism |
| CN102092478B (en) * | 2010-12-30 | 2015-05-13 | 中国商用飞机有限责任公司 | Positioning device for butting wing body |
| CN103121194B (en) * | 2013-01-15 | 2014-10-15 | 西北工业大学 | Positioning fixture for splicing large wing wallboard and positioning method |
| CN203793615U (en) * | 2014-04-01 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Comb-shaped joint structure |
| CN105035356A (en) * | 2015-08-18 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Multipoint coplane high-precision hole axis matching aircraft component butt joint coordination method |
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