CN100506646C - Method for preparing connection between two frame sections of airplane - Google Patents
Method for preparing connection between two frame sections of airplane Download PDFInfo
- Publication number
- CN100506646C CN100506646C CNB2006100834704A CN200610083470A CN100506646C CN 100506646 C CN100506646 C CN 100506646C CN B2006100834704 A CNB2006100834704 A CN B2006100834704A CN 200610083470 A CN200610083470 A CN 200610083470A CN 100506646 C CN100506646 C CN 100506646C
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- frame sections
- coupled
- boring
- hsd
- hole
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- Drilling And Boring (AREA)
Abstract
The present invention relates to process of preparing two fuselage sections of airplane to be connected. One drilling template, preferably without any guide hole, is first made to penetrate the covering and/or coupling device of one fuselage section and then drilled to form one group of ultimate holes at high speed. The present invention is relatively simple and less time consuming.
Description
Technical field
The present invention relates to a kind of bonded assembly method of preparing two frame sections (cylindrical shell) of aircraft.
Background technology
The manufacturing process of commercial aircraft comprises the connection of preparing frame sections.Must be accurate and firm because connect, existing connection preparation and connection itself are complicated and consuming time.Particularly aspect the length of fuselage, several millimeters little error can partly cause several centimetres very large error at tail cone, and then makes the flight characteristics of aircraft be difficult to prediction.
Bonded assembly method at two frame sections of present preparation aircraft provides exemplary Short Description:
The frame sections that will have seat bar (seat bar) and a stringer (stringer) of prepackage holds up and it is moved towards each other, and the width that utilizes seat bar for example or stringer and/or the slit between the leading edge of frame sections (annular gap with several millimeters fixed ranges) is with its accurately setting and until the line of centers of the fuselage cylindrical shell in-line that---is the longitudinal axis of fuselage---.Little bar cramp is at the stringer place and as being coupled device and compensating above-mentioned error.
At first, stringer itself is not fixed between the front edge of a terminal annular frame and a frame sections.Therefore, can further compensate error.In addition, in order to compensate the manufacturing errors of a frame sections, it also has longitudinal slot.The loop bracket that has calibration boring (CBH) be attached to the place, inboard of fuselage cylindrical shell and by inserting such as the anchor fitting of dummy rivet etc. and with the front edge overlaid of a fuselage cylindrical shell.The radius of this carriage is identical with the relevant portion of frame sections.
Except the accessory of above-mentioned little bar etc., this loop bracket also can adopt the tack riveting to be attached to simultaneously on another a fuselage cylindrical shell and the bore template by other connecting elements of for example dummy rivet etc.
Next procedure of processing is for each design-calculated finally gets out pilot hole, and described final boring is actually covering and each boring of carriage of passing frame sections.Owing to materials such as for example drilling cuttings can be passed in quite thin covering and the space that may exist between the loop bracket, therefore, fuselage cylindrical shell and accessory need be dismantled.After in covering and loop bracket, getting out pilot hole, can remove the boring burr and remove the oil stain of boring.
Summary of the invention
The bonded assembly method that the purpose of this invention is to provide two frame sections (cylindrical shell) of the little and few preparation aircraft consuming time of a kind of complexity.
This can be by preparation aircraft according to the present invention the bonded assembly method of two frame sections solve.Described method comprises the following steps: to use a bore template, pass the exterior skin of one of them frame sections at least and/or be coupled device high-speed drilling (HSD) and finally hole for one group, wherein said high-speed drilling (HSD) reaches 15,000 to 20,000 rev/min (RPM).
Major advantage of the present invention is to need not to get out pilot hole---particularly in the cradle of frame sections.High-speed drilling allows to hole in an one step.The power that acts on downwards on frame sections or the carriage can be significantly less than the power in the standard boring procedure known in the art.Therefore, can avoid the distortion of frame sections/carriage.
According to a first aspect of the invention, the bonded assembly method of preparing two frame sections can comprise the steps: to be provided with frame sections makes the frame sections peristome of each frame sections towards another frame sections, and will for example comprise calibration boring (CBA) carriage etc. be coupled the stringer that device is attached at least one frame sections and/or at least one frame sections, wherein " attaching " comprises longitudinal axis and/or the vertical axis adjusting machine figure along aircraft.
According to a second aspect of the invention, described high-speed drilling (HSD) comprising: lubricate described boring and conical countersink is carried out in described boring.
According to a third aspect of the invention we, described method can comprise frame sections from being coupled device separately.
According to a forth aspect of the invention, described method can comprise oil stain and the burr of removing on the frame sections.
According to a fifth aspect of the invention, described method can comprise to frame sections, especially be coupled device and apply aquaseal.
According to a sixth aspect of the invention, described method for example can comprise at pilot hole stationkeeping/rivet machine figure and be coupled device.
According to a seventh aspect of the invention, described method can comprise by anchor fitting and calibration boring at frame sections and/or be coupled the device place and utilize CBA to fix one bore template at least.
In addition, if though use the high-speed drilling method, so generally need not the brill that leads, but the method according to this invention can comprise also: get out one group of pilot hole (4.6mm) by the exterior skin that uses CBA to pass at least one fuselage cylindrical shell as pilot bore hole; And use a bore template, pass the exterior skin of at least one frame sections and/or be coupled device and one group of high-speed drilling (HSD) finally hole (4.8mm).
Description of drawings
Below, for further explaining and understanding better, an illustrative embodiments will be described with reference to the accompanying drawings.
The schematic side elevation of the part of fuselage 1 has been shown among Fig. 1, and it has first frame sections 2 and one second frame sections 3 of a front portion.
The specific embodiment
First of carriage 4 (framework) form be coupled the leading edge 5 that device is fixed on frame sections 2 ringwise.Not shown final and pilot hole in said apparatus/frame sections.Two frame sections 2,3 comprise stringer 6 forms another be coupled device.View among the figure is schematically, and ratio completely is not shown.
Should be pointed out that term " comprises " does not get rid of other elements or step, and " one " does not get rid of a plurality of situations.In addition, the element of describing in relevant different embodiments can make up.Should be pointed out that the reference number in the claim should not be interpreted as limiting the scope of claim.
Claims (9)
1. prepare the bonded assembly method of two frame sections (2,3) of aircraft, wherein, described method comprises the following steps:
Use a bore template, pass the exterior skin of one of them frame sections at least and/or be coupled device high-speed drilling (HSD) and finally hole for one group, wherein said high-speed drilling (HSD) reaches 15,000 to 20,000 rev/mins (RPM).
2. the method for claim 1 further comprises:
Peristome that described frame sections (2,3) makes each frame sections is set towards another frame sections, and will includes the stringer element (6) that device (4,6) is attached at least one frame sections (2,3) and/or at least one frame sections that is coupled of calibration boring (CBA).
3. method as claimed in claim 2 further comprises:
Described frame sections (2,3) is gone up separately from the described device (4,6) that is coupled.
4. the method according to any one of the preceding claims further comprises:
Remove the oil stain of described frame sections (2,3),
Remove the burr of described frame sections (2,3).
5. method as claimed in claim 2 further comprises:
To described frame sections be coupled device (4) and apply aquaseal,
In the pilot hole stationkeeping and rivet described frame sections (2,3) and the described device that is coupled.
6. method as claimed in claim 2 further comprises:
Utilize described calibration boring (CBA) to fix at least one bore template by anchor fitting with calibrating to hole at frame sections and/or be coupled the device place.
7. method as claimed in claim 6 further comprises:
By use calibration boring (CBA) as pilot bore hole, pass the exterior skin of at least one frame sections (2,3) and get out one group of pilot hole.
8. method as claimed in claim 1 or 2, wherein, described high-speed drilling (HSD) comprising:
Lubricated described boring.
9. method as claimed in claim 1 or 2, wherein, described high-speed drilling (HSD) comprising:
Conical countersink is carried out in described boring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100834704A CN100506646C (en) | 2006-05-30 | 2006-05-30 | Method for preparing connection between two frame sections of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100834704A CN100506646C (en) | 2006-05-30 | 2006-05-30 | Method for preparing connection between two frame sections of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101081642A CN101081642A (en) | 2007-12-05 |
| CN100506646C true CN100506646C (en) | 2009-07-01 |
Family
ID=38911492
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2006100834704A Expired - Fee Related CN100506646C (en) | 2006-05-30 | 2006-05-30 | Method for preparing connection between two frame sections of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100506646C (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2927606B1 (en) * | 2008-02-15 | 2010-07-30 | Airbus France | AIRCRAFT FUSELAGE IN COMPOSITE MATERIAL HAVING IMPROVED CRASH |
| DE102009021369A1 (en) | 2009-05-12 | 2010-11-18 | Airbus Operations Gmbh | Method for producing an aircraft fuselage and fuselage |
| CN101811575A (en) * | 2010-04-14 | 2010-08-25 | 桂林鑫鹰电子科技有限公司 | Portable low-altitude remote sensing miniature unmanned vehicle |
| US20180072433A1 (en) * | 2015-03-23 | 2018-03-15 | Bombardier Inc. | Simulation of loads on aerostructures during aircraft assembly |
-
2006
- 2006-05-30 CN CNB2006100834704A patent/CN100506646C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN101081642A (en) | 2007-12-05 |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: AIRBUS DEUTSCHLAND GMBH Free format text: FORMER NAME: AIRBUS GMBH |
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| CP01 | Change in the name or title of a patent holder |
Address after: hamburg Patentee after: Airbus Operations GmbH Address before: hamburg Patentee before: Airbus GmbH |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090701 Termination date: 20200530 |