CN106043661A - Manual fuselage and wing quick butt joint method - Google Patents
Manual fuselage and wing quick butt joint method Download PDFInfo
- Publication number
- CN106043661A CN106043661A CN201610400433.5A CN201610400433A CN106043661A CN 106043661 A CN106043661 A CN 106043661A CN 201610400433 A CN201610400433 A CN 201610400433A CN 106043661 A CN106043661 A CN 106043661A
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- wing
- frame
- fuselage
- butt joint
- mating
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Classifications
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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
-
- 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
Abstract
The invention relates to a manual fuselage and wing quick butt joint method and belongs to the field of manual fuselage and wing quick butt joint methods of small airplanes of fork lug type fuselage and wing butt joint structures. Butt joint standards of a fork lug type butt joint structure are selected, wings are in butt joint with a fuselage as the standard, and the butt joint standards are composed of the up and down standard, the front and back standard and the left and right standard. According to the up and down standard, an upper lug plate joint hole with the largest distance is selected as the butt joint standard for localization; according to the front and back standard position freedom degree, the end face of a middle lower joint lug plate serves as the standard for localization; and according to the left and right standard position freedom degree, a middle lower joint lug plate hole serves as the standard for localization. By the adoption of the method, quick manual butt joint of a small airplane of a multi-intersection, high-accuracy and uncompensated fuselage and wing butt joint structure is achieved when advanced butt joint technical equipment and measures are not available for the small airplane in the external field of troops and during wartime, quick maintenance and overhauling are achieved, the maintainability of a warplane on the external field is improved, and the survival and fighting capacity of the warplane under extremely adverse conditions during wartime is improved.
Description
Technical field
The present invention relates to a kind of fuselage wing artificial rapid abutting joint method, belong to the little of fork ear formula fuselage wing docking structure
Type airframe wing artificial rapid abutting joint method field.
Background technology
Three generations and above opportunity of combat to the requirement such as high maneuverability, high structural strength, make aircraft have high aerodynamic configuration want
Outside asking, also want strict control structure weight, thus a lot of employing of design pitches ear formula fuselage wing docking structure.Because of air speed,
Overload, the difference of aerodynamic arrangement, small-sized opportunity of combat ear V shape fuselage wing mate is typically located on 4-5 load frame, has
Joint about 7-9 group, has the feature many to contact point；Often group is to contact point most employing E9(body joint hole)/f9(pair
Connecting bolt)/H8(Wing Joint hole) coordinate, have the advantages that quality of fit is high；Butt hole axiality is at butt hole centre deviation
During less than 0.15mm, it is allowed to force assembling, there is the feature without design compensation.For solving the coaxial of fuselage wing mate
Degree problem, domestic and international planemaker is substantially all the mode using parts polish, is set by automatic butt at assembling Factory Building
Standby or auxiliary mould realizes the docking of fuselage wing.
Due to high expense, substantially without being equipped with automatic butt equipment and numerous in the outfield such as army, system shop, field
Auxiliary butting tooling, if needing fuselage wing is decomposed in outfield, and carry out overhauling, repair, maintaining time,
Substantially it is only capable of carrying out the dismounting of fuselage wing by most basic bracket, personnel and instrument.If in wartime, not only tooling device
Cannot ensure, also to realize artificial fast assembling-disassembling, maintenance, to improve viability and the fighting capacity in battlefield, win future war.Cause
This, find a kind of manually, quickly realize the many intersection points of baby plane, in high precision, uncompensated fuselage wing docking method seem outstanding
For important.
Summary of the invention
The present invention, in order to overcome drawbacks described above, its object is to provide a kind of fuselage wing artificial rapid abutting joint method, mesh
Be in order to solve many intersection points, in high precision, the baby plane of uncompensated fuselage wing docking structure is in army outfield and wartime etc.
When not possessing docking technique equipment and the means of advanced person, it is achieved quickly, manually dock, it is achieved Fast-Maintenance and maintenance, improve war
Machine flight-line service, improves opportunity of combat existence under the extreme unfavorable conditions in wartime, operational efficiency.
The present invention to achieve these goals, adopts the following technical scheme that
A kind of fuselage wing artificial rapid abutting joint method:
Select docking benchmark, pitch ear formula docking structure, be as the criterion docking wing with fuselage, its docking benchmark by upper and lower benchmark, front and back
Benchmark, left and right benchmark are constituted；
The upper auricle nipple orifice of selection of reference frame ultimate range positions for docking benchmark up and down；
Front and back reference position degree of freedom positions on the basis of middle lower contact auricle end face；
Reference position, left and right degree of freedom positions on the basis of middle lower contact auricle hole；
It specifically comprises the following steps that
A), check the surface quality at fuselage, wing mate and interface, fifth wheel on cleaning joint, smear lubrication
Fat；
B), according to docking selection of reference frame requirement, once carry out up and down, the docking of around benchmark；
C), after benchmark docked, remaining each connection intersection point being carried out coaxality measurement, axiality meets design axiality requirement
After, the connection carrying out intersection point bolt is installed；
D), after each system installation of fuselage wing joint, carrying out reassembling of shoulder cowling, fuselage wing has docked.
Further,
In step B) in: first with wing bracket, the 2nd interface frame, mating frame is adjusted in place with last 1 interface frame, mating frame top connection intersection point, adjusts
By the axiality of inspection pin inspection hole after putting in place, the 2nd interface frame, mating frame is located by connecting with last 1 interface frame, mating frame top connection intersection point,
Control wing upper and lower reference position degree of freedom；
During docking, first connect the intersection point of the 2nd interface frame, mating frame and last 1 interface frame, mating frame, then connect other intersection points；
If the 2nd interface frame, mating frame is with last 1 interface frame, mating frame top connection crossing point holes on an axis, the most just control a rotation
Axis；
After 2nd interface frame, mating frame controls to put in place with last 1 interface frame, mating frame top connection intersection point, slowly reduce wing and height is installed, utilize machine
Wing the 2nd interface frame, mating frame lower contact auricle is slowly inserted under fuselage in auricle by wing deadweight, in the middle of fuselage the 2nd interface frame, mating frame lower contact
Position on the basis of end face before or after auricle, control reference position degree of freedom before and after wing；
Adjust wing location status, check and adjust the axiality of the 2nd interface frame, mating frame and last 1 interface frame, mating frame bottom joint everywhere, with
Axiality state is most preferably as the criterion: the both all inspections in bottom pin maximums, is located by connecting crossing point holes under the 2nd interface frame, mating frame, controls
Reference position, wing left and right degree of freedom.
Beneficial effects of the present invention:
This invention makes aircraft in the outfields such as army, system shop, field, can only take during for fork ear formula fuselage wing docking
Bracket, attachment tools and a small amount of personnel just can complete rapid abutting joint, a large sum of frock expense of economization, and have the highest right
Connecing efficiency, the outfield that improve opportunity of combat is maintainable, thus improves the existence of aircraft, operational efficiency.This invention is applicable to many
Intersection point, fork ear formula baby plane fuselage wing quick, artificial docking, have universal guidance, dissemination.
Accompanying drawing explanation
Fig. 1 is wing mate schematic diagram on the left of Typical Aircraft (right side is symmetrical).
1-the 1st interface frame, mating frame intersection point in figure, 2-the 2nd interface frame, mating frame intersection point, 3-the 3rd interface frame, mating frame intersection point, 4-the 4th interface frame, mating frame intersection point,
5-the 5th interface frame, mating frame intersection point.
Detailed description of the invention
Describe the present invention below in conjunction with Figure of description:
It is as the criterion with fuselage during docking, uses bracket fixed main body, allow wing dock on fuselage.Fig. 1 is typical baby plane fork
The typical structure of ear formula fuselage wing docking, as a example by right side, is followed successively by the 1st interface frame, mating frame intersection point the 1, the 2nd interface frame, mating frame from front to back
Intersection point the 2, the 3rd interface frame, mating frame intersection point the 3, the 4th interface frame, mating frame intersection point the 4, the 5th interface frame, mating frame intersection point 5, wherein removing the 1st interface frame, mating frame intersection point is single cross
Outside Dian, remaining interface frame, mating frame be upper and lower two groups to contact point.As a example by Fig. 1, butt-joint process flow process and requirement are as follows:
Surface quality at a, inspection fuselage, wing mate and interface, fifth wheel on cleaning joint, smear lubrication
Fat.
B, first with wing bracket, the 2nd, the 5th interface frame, mating frame top connection intersection point is adjusted in place, with inspection pin after being adjusted in place
The axiality of inspection hole, is located by connecting to the 2nd, the 5th interface frame, mating frame top connection intersection point, controls wing upper-lower position degree of freedom.
In view of the operability manually adjusted with bracket docking, during actual docking, can first connect the 2nd or the 5th intersection point, then connect
Another intersection point.If the 2nd, the 5th interface frame, mating frame top connection crossing point holes is on an axis, the most just control a rotary shaft
Line.
After c, the 2nd, the 5th interface frame, mating frame top connection intersection point controls to put in place, slowly reduce wing and height is installed, utilize wing certainly
Wing the 2nd interface frame, mating frame lower contact auricle is slowly inserted under fuselage in auricle by weight, with auricle in the middle of fuselage the 2nd interface frame, mating frame lower contact
Position on the basis of front or rear end face, control (course) position freedom before and after wing.Require insertion process is carried out at any time
Regulation, is not allow for forcing.
D, adjustment wing location status, check and adjust the axiality of the 2nd the 5th frame bottom joint everywhere, with axiality
State is most preferably as the criterion (the both all inspections in bottom pin maximums), is located by connecting crossing point holes under the 2nd interface frame, mating frame, controls wing left
Right position freedom.
E, after intersection point connects at above-mentioned three, wing positions the most completely, now, carries out remaining intersection point and carries out with to connecting bolt
Connect.
After f, each system installation of fuselage wing joint, carrying out the equipped of shoulder cowling, fuselage wing has docked.
Points for attention: wing is adjusted, in docking operation can artificial weak vibrations bracket, reduce docking stress；Sternly
Prohibit cruelty operation and fuselage or wing are caused damage.
Claims (2)
1. a fuselage wing artificial rapid abutting joint method, this docking calculation is characterised by:
Docking benchmark is made up of upper and lower benchmark, front and back benchmark, left and right benchmark；
The upper auricle nipple orifice of selection of reference frame ultimate range positions for docking benchmark up and down；
Front and back reference position degree of freedom positions on the basis of middle lower contact auricle end face；
Reference position, left and right degree of freedom positions on the basis of middle lower contact auricle hole；
It specifically comprises the following steps that
A), check the surface quality at fuselage, wing mate and interface, fifth wheel on cleaning joint, smear lubrication
Fat；
B), according to docking selection of reference frame requirement, once carry out up and down, the docking of around benchmark；
C), after benchmark docked, remaining each connection intersection point being carried out coaxality measurement, axiality meets design axiality requirement
After, the connection carrying out intersection point bolt is installed；
D), after each system installation of fuselage wing joint, carrying out reassembling of shoulder cowling, fuselage wing has docked.
Fuselage wing the most according to claim 1 artificial rapid abutting joint method, it is characterised in that:
In step B) in: first with wing bracket, the 2nd interface frame, mating frame is adjusted in place with last 1 interface frame, mating frame top connection intersection point, adjusts
By the axiality of inspection pin inspection hole after putting in place, the 2nd interface frame, mating frame is located by connecting with last 1 interface frame, mating frame top connection intersection point,
Control wing upper and lower reference position degree of freedom；
During docking, first connect the intersection point of the 2nd interface frame, mating frame and last 1 interface frame, mating frame, then connect other intersection points；
If the 2nd interface frame, mating frame is with last 1 interface frame, mating frame top connection crossing point holes on an axis, the most just control a rotation
Axis；
After 2nd interface frame, mating frame controls to put in place with last 1 interface frame, mating frame top connection intersection point, slowly reduce wing and height is installed, utilize machine
Wing the 2nd interface frame, mating frame lower contact auricle is slowly inserted under fuselage in auricle by wing deadweight, in the middle of fuselage the 2nd interface frame, mating frame lower contact
Position on the basis of end face before or after auricle, control reference position degree of freedom before and after wing；
Adjust wing location status, check and adjust the axiality of the 2nd interface frame, mating frame and last 1 interface frame, mating frame bottom joint everywhere, with
Axiality state is most preferably as the criterion: the both all inspections in bottom pin maximums, is located by connecting crossing point holes under the 2nd interface frame, mating frame, controls
Reference position, wing left and right 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106043661A true CN106043661A (en) | 2016-10-26 |
| CN106043661B CN106043661B (en) | 2018-08-24 |
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|---|---|---|---|
| CN201610400433.5A Active CN106043661B (en) | 2016-06-08 | 2016-06-08 | A kind of artificial rapid abutting joint method of fuselage wing |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111563904A (en) * | 2020-04-30 | 2020-08-21 | 南京航空航天大学 | Wing fork ear point cloud segmentation method based on three-dimensional feature descriptor |
| CN111746818A (en) * | 2020-06-12 | 2020-10-09 | 陕西飞机工业（集团）有限公司 | Method for installing 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 |
| CN113247299A (en) * | 2021-07-16 | 2021-08-13 | 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 |
| CN113664530A (en) * | 2021-09-06 | 2021-11-19 | 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 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111563904A (en) * | 2020-04-30 | 2020-08-21 | 南京航空航天大学 | Wing fork ear point cloud segmentation method based on three-dimensional feature descriptor |
| CN111746818A (en) * | 2020-06-12 | 2020-10-09 | 陕西飞机工业（集团）有限公司 | Method for installing 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 |
| CN113247299A (en) * | 2021-07-16 | 2021-08-13 | 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 |
| CN113664530A (en) * | 2021-09-06 | 2021-11-19 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043661B (en) | 2018-08-24 |
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