CN101081445B - Method of encoding for drilling implement for airplane and kit - Google Patents
Method of encoding for drilling implement for airplane and kit Download PDFInfo
- Publication number
- CN101081445B CN101081445B CN2006100834719A CN200610083471A CN101081445B CN 101081445 B CN101081445 B CN 101081445B CN 2006100834719 A CN2006100834719 A CN 2006100834719A CN 200610083471 A CN200610083471 A CN 200610083471A CN 101081445 B CN101081445 B CN 101081445B
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- China
- Prior art keywords
- coding
- groove
- bushing
- rig
- pin
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Abstract
The present invention relates to method of coding equipment for drilling holes in airplane part. The method includes the following steps: setting one drilling template with at least one hole on the workpiece, setting one bit holder inside the hole on the drilling template, and setting the drilling equipment in the hole on the drilling template. The bit holder includes one main coding device, and the drilling equipment includes one sleeve coding device suitable for fitting the main coding device.
Description
Technical field
The present invention relates to be used for the rig of aircraft, relate in particular to a kind of method and a kind of external member the encoding for drilling implement that is used for aircraft.
Background technology
Each wing fuselage coupling part all needs a plurality of borings that are used for drill bushing at present.Because the curvature of wing and fuselage surface is different, so drill bushing and corresponding boring have the different degree of depth.In addition, the diameter of boring, the grip of rivet and rivet shape (taper or cylindricality) also have nothing in common with each other.
So risk that exists the workman to select drilling machine mistakenly and bore wrong hole thus.
Summary of the invention
An object of the present invention is to provide a kind of coding method, this method can prevent to select wrong drilling machine and therefore bore wrong hole.
Method and apparatus according to the invention can address this problem.
According to first embodiment of the present invention, provide a kind of coding method that is used for encoding for drilling implement.This coding method comprises the steps.The bore template that will have at least one boring is placed on the workpiece, and this workpiece for example can be an aircraft.Particularly, this workpiece is the part of aircraft wing, fuselage, wing main body (wing box) or miscellaneous part.Drill bushing is placed in the boring of bore template, and rig is placed in the boring of bore template.
Drill bushing comprises coding main equipment (coding master device), and this coding main equipment comprises the drill bushing edge with first groove and second groove.Rig comprises coding bushing installation (codingsleeve device), and this coding bushing installation comprises the coding sleeve edge with the first coding pin and second coding pin.This coding bushing installation is engaged with each other when moving axially towards each other with the coding main equipment, makes the described first coding pin engage with described second groove with described first fillistered joint merging and the described second coding pin.
By using illustrative methods of the present invention and embodiment, this second groove is spaced apart with the predetermined angle and first groove along the drill bushing edge.The first and second coding pins are opened with predetermined angle intervals.
Bore template shows the position of pending boring with the boring pattern.Drill bushing is placed in the boring of bore template.Drill bushing plays the coding main equipment in mode as described below.Preferred drill bushing is the form of bayonet nut connector (BNC).In addition, drill bushing has two notches at its edge.One of them mark of these notches zero point.Another notch is spaced apart at the preposition and first notch.Can limit the angle between zero point and the precalculated position thus, and determine the type of boring.
Rig plays coding from equipment, because its function depends on the coding main equipment.A kind of preferred rig, for example drilling machine has the 2nd BNC, and it can engage with a BNC of drill bushing.In addition, rig has two coding pins.First coding pin with zero point notch engages, encoding to sell for second engages with second notch.Only,, can start rig then and hole with regard to lockable BNC by two pins are correctly engaged with two notches.
Description of drawings
Hereinafter, specifically describe exemplary of the present invention with reference to the accompanying drawings further to explain and to understand the present invention better:
Fig. 1 shows the exemplary of drill bushing (top) and associated rig (bottom)
The schematic diagram of embodiment.
Fig. 2 show second drill bushing and associated rig and
Fig. 3 shows the schematic diagram of another exemplary of rig.
Identical or relevant parts adopt identical Reference numeral to represent in a few width of cloth figure, and these accompanying drawings just schematically and not are to draw according to size fully.
The specific embodiment
The top of Fig. 1 shows an exemplary drill bushing 1, and its effect is as the first coding main equipment.Drill bushing 1 comprises a coding main equipment, comprises a drill bushing edge 2 particularly, and this edge 2 comprises first Lock Part 5 that has first groove 3 and second groove 4, and wherein second groove 4 and first groove 3 are spaced apart with the predetermined angular 6 of 180 degree along the drill bushing edge.
Bottom at Fig. 1, partly show an exemplary rig 7, this rig 7 comprises the coding bushing installation with coding sleeve edge 8, the sleeve edge of wherein encoding comprises second locking device 9 that has the first coding pin, the 10 and second coding pin 11, and wherein the first and second coding pins also are spaced apart with the predetermined angular 6 ' of 180 degree.
Rig 8 and drill bushing 1 have constituted an external member 12, if wherein the first coding pin 10 engages with first groove 3, and second encode and sell 11 and engage with second groove 4, and first locking device can be connected to second locking device so.
Fig. 2 shows second external member 13, wherein has different angle 14,14 ' between the pin/groove.
Fig. 3 shows the 3rd rig 15 that has drill bit 16, and the diameter D of drill bit is 47mm.This rig also has the coding pin 17,18 of close BNC flange 19,20.
It should be noted that term " comprises " existence of not getting rid of miscellaneous part or step, " one " does not get rid of a plurality of situations.And the parts of describing in different embodiments can combine.Should also be noted that the Reference numeral in the claim should not be construed as the restriction of formation to the claim scope.
Claims (5)
1. one kind is carried out Methods for Coding to the rig (7,15) that is used for aircraft, and wherein this method comprises:
The bore template that will have at least one boring is placed on the workpiece;
Drill bushing (1) is placed in the boring of bore template;
Rig (7,15) is placed in the boring of bore template,
It is characterized in that:
Described drill bushing (1) comprises a coding main equipment, and this coding main equipment comprises the drill bushing edge (2) with first groove (3) and second groove (4);
Described rig comprises a coding bushing installation, and this coding bushing installation comprises the coding sleeve edge (8) with the first coding pin (10) and second coding pin (11); With
Described coding bushing installation and described coding main equipment are engaged with each other when moving axially towards each other, make the described first coding pin (10) engage with described first groove (3) and described second encode and sell (11) and engage with described second groove (4).
2. according to the method for claim 1, it is characterized in that:
Described second groove (4) is spaced apart at a predetermined angle along described drill bushing edge (2) with described first groove (3); With
The described first and second coding pins (10,11) are opened with another predetermined angular intervals.
3. according to the method for claim 1 or 2, it is characterized in that described coding main equipment is suitable for being connected by bayonet coupling connector with described coding bushing installation.
4. according to the method for claim 1, it is characterized in that described rig (7,15) comprises another coding bushing installation.
5. an external member (12,13) comprises drill bushing (1) and rig (7,15), it is characterized in that:
This drill bushing (1) comprises the coding main equipment, this coding main equipment comprises the drill bushing edge (2) with first groove (3) and second groove (4), wherein said second groove (4) is spaced apart at a predetermined angle along described drill bushing edge (2) with described first groove (3), and
This rig (7,15) comprise the coding bushing installation, this coding bushing installation comprises the coding sleeve edge (8) with the first coding pin (10) and second coding pin (11), and wherein said first coding pin (10) and the described second coding pin (11) are opened with another predetermined angular intervals
Wherein said coding bushing installation and described coding main equipment are suitable for being engaged with each other when moving axially towards each other, make the described first coding pin (10) engage with described first groove (3) and described second encode and sell (11) and engage with described second groove (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2006100834719A CN101081445B (en) | 2006-05-30 | 2006-05-30 | Method of encoding for drilling implement for airplane and kit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2006100834719A CN101081445B (en) | 2006-05-30 | 2006-05-30 | Method of encoding for drilling implement for airplane and kit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101081445A CN101081445A (en) | 2007-12-05 |
| CN101081445B true CN101081445B (en) | 2010-11-03 |
Family
ID=38911353
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2006100834719A Expired - Fee Related CN101081445B (en) | 2006-05-30 | 2006-05-30 | Method of encoding for drilling implement for airplane and kit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101081445B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101996331B (en) * | 2009-08-14 | 2012-10-17 | 中国石油天然气集团公司 | Drilling tool code recognition system |
-
2006
- 2006-05-30 CN CN2006100834719A patent/CN101081445B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN101081445A (en) | 2007-12-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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 |
|
| 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 |
|
| 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: 20101103 Termination date: 20170530 |