CN204843030U - Crackle gets rid of appurtenance around aircraft metallic structure's fastener hole - Google Patents
Crackle gets rid of appurtenance around aircraft metallic structure's fastener hole Download PDFInfo
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- CN204843030U CN204843030U CN201520353824.7U CN201520353824U CN204843030U CN 204843030 U CN204843030 U CN 204843030U CN 201520353824 U CN201520353824 U CN 201520353824U CN 204843030 U CN204843030 U CN 204843030U
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- hole
- auxiliary member
- metal structure
- drilling auxiliary
- crackle
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Abstract
The utility model provides a crackle gets rid of appurtenance around aircraft metallic structure's fastener hole, body be fixed in aircraft metallic structure when using on with install on the body drilling auxiliary member in the mounting hole I, mounting hole I runs through the body, I coaxial line of drilling auxiliary member and mounting hole is installed, has a plurality of station at the drilling auxiliary member that makes progress in week, can lock in every station department relative circumference position with the body of drilling auxiliary member, has the eccentric orfice that is used for drawing a circle to approve the scope of getting rid of that runs through the auxiliary member in the axial on the drilling auxiliary member. On the body was fixed in aircraft metallic structure, during mounting hole I was installed on the body to the drilling auxiliary member, the scope was got rid of in the eccentric orfice delineation of drilling auxiliary member, can eccentricly get rid of crackle around aircraft metallic structure's the fastener hole, the volume of getting rid of of guaranteeing the material with get rid of the direction.
Description
Technical field
The removal aid of crackle around the fastener hole that the utility model relates to a kind of Aircraft Metal Structure.
Background technology
Aircraft Metal Structure is the primary structure part of present generation aircraft and main part of the force, and the crackle modal type of impairment that is metal structure.In aircraft maintenance process, often can find crackle around the fastener hole of metal structure, in order to the removal metal material fragmented parts of minimum, thus ensure the structural strength of material remainder, eccentric mode generally can be selected to remove crackle.
Also there is no the eccentric tool set removing crackle at present, the individual skill of worker can only be relied on, use drill bit directly to bore crackle.But this mode poor accuracy, causes and once cannot remove crackle completely, or additionally eliminate structural metallic materials.If additionally eliminate structural metallic materials, can damage the structural strength of metal structure, causing originally can the damage of light maintenance, and needing carries out large repairs maybe must change parts.
Utility model content
The removal aid of crackle around the fastener hole that the technical problems to be solved in the utility model is to provide a kind of Aircraft Metal Structure, to remove crackle around fastener hole better.
In order to solve the problems of the technologies described above, the technical solution of the utility model is:
The removal aid of crackle around a kind of fastener hole of Aircraft Metal Structure, the drilling auxiliary member being fixed on the body on Aircraft Metal Structure when comprising use and being installed on body in installing hole I, installing hole I runs through body, drilling auxiliary member and installing hole I coaxial line are installed, drilling auxiliary member has several stations in the circumferential, can locking at each station place drilling auxiliary member and body the relative circumferential position, drilling auxiliary member having the eccentric orfice for drawing a circle to approve removal scope axially running through auxiliary member.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, installing hole I hole wall have some locating slots of circumference distribution, the periphery of drilling auxiliary member has locating slot, on hole wall, on locating slot and periphery, locating slot all axially extends, and alignment pin is arranged in simultaneously and locating slot and periphery completes drilling auxiliary member during locating slot to hole wall and body the relative circumferential position locks; Or,
The periphery of drilling auxiliary member have some locating slots of circumference distribution, install on hole wall and there is locating slot, on hole wall, on locating slot and periphery, locating slot all axially extends, and alignment pin is arranged in simultaneously and locating slot and periphery completes drilling auxiliary member during locating slot to hole wall and body the relative circumferential position locks; Or,
The periphery of drilling auxiliary member has some teeth of annular array, correspondingly, install some teeth groove hole wall with annular array, tooth locks with coordinated drilling auxiliary member and body the relative circumferential position of teeth groove; Or,
Install some teeth hole wall with annular array, correspondingly, the periphery of drilling auxiliary member has some teeth groove of annular array, tooth locks with coordinated drilling auxiliary member and the body circumference relative position of teeth groove.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, drilling auxiliary member has multiple, and their eccentric orfice aperture eccentric throw that is not identical and/or eccentric orfice is not identical.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, the outer end of drilling auxiliary member has the outward flange that external diameter is greater than aperture, installing hole I outer end.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, body also has the elongated hole-shape installing hole II being scattered in installing hole I periphery that at least two axis run through body, in each installing hole II, installing is used for assisting the auxiliary fixing member be fixed on by body on Aircraft Metal Structure, auxiliary fixing member has the elongated hole that the axial fastening spiral of confession running through itself wears, auxiliary fixing member entirety is in long annular, the width of elongated hole is identical with the fastener hole aperture just right with this elongated hole, this fastener hole is positioned at around crackle fastener hole to be removed, the outer end of auxiliary fixing member has the outward flange that size is greater than installing hole II, wherein at least two auxiliary fixing member are vertically arranged.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, auxiliary fixing member has multiple, and their outer peripheral face is measure-alike, and the elongated hole width of auxiliary fixing member not of the same race is different to mate from different fastener hole.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, installing hole II is four, lays respectively at four angles place of rectangle, is divided into two groups, often group comprises two that be arranged in parallel, and the installing hole II in a group is vertical with the installing hole II in another group to be arranged.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, body is fixed on Aircraft Metal Structure by fixture.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, body is plate, and eccentric orfice is circular hole.
The removal aid of crackle around the fastener hole of above-mentioned Aircraft Metal Structure, adopts the CRES corrosion-resistant stainless steel meeting Boeing material standard to make.
Body is fixed on Aircraft Metal Structure, drilling auxiliary member to be installed on body in installing hole I, the eccentric orfice delineation removal scope of drilling auxiliary member, can crackle around the eccentric fastener hole removing Aircraft Metal Structure, ensures the removal amount of material and removes direction.
Accompanying drawing explanation
Below in conjunction with accompanying drawing to the further detailed description of the utility model:
Fig. 1 is structural representation of the present utility model.
Fig. 2 is structural representation of the present utility model.
Fig. 3 is the structural representation of body.
Fig. 4 is the structural representation of drilling auxiliary member.
Fig. 5 is the structural representation of alignment pin.
Fig. 6 is the structural representation of auxiliary fixing member.
Detailed description of the invention
As shown in Figures 1 to 6, the removal aid of crackle a around a kind of fastener hole of Aircraft Metal Structure, the drilling auxiliary member 2 being fixed on the body 1 on Aircraft Metal Structure 5 when comprising use and being installed on body in installing hole I 11, installing hole I runs through body, drilling auxiliary member and installing hole I coaxial line are installed, drilling auxiliary member has several stations in the circumferential, can locking at each station place drilling auxiliary member and body the relative circumferential position, drilling auxiliary member having the eccentric orfice 21 for drawing a circle to approve removal scope axially running through auxiliary member.Drilling auxiliary member is positioned at different station, and its eccentric orfice delineation removal scope is different.Can lock at each station place drilling auxiliary member and body the relative circumferential position, to remove crackle around fastener hole.Eccentric orfice delineation removal scope, the direction of advancing for guiding drill bit, ensures that drill bit operationally can not yawing moment.
The embodiment that the station of drilling auxiliary member is determined is as follows:
Installing hole I hole wall have some locating slots of circumference distribution, the periphery of drilling auxiliary member has locating slot 22, on hole wall, on locating slot and periphery, locating slot all axially extends, and alignment pin 3 is arranged in simultaneously and locating slot and periphery completes drilling auxiliary member during locating slot to hole wall and body the relative circumferential position locks; Or,
The periphery of drilling auxiliary member have some locating slots of circumference distribution, install on hole wall and there is locating slot, on hole wall, on locating slot and periphery, locating slot all axially extends, and alignment pin is arranged in simultaneously and locating slot and periphery completes drilling auxiliary member during locating slot to hole wall and body the relative circumferential position locks; Or,
The periphery of drilling auxiliary member has some teeth of annular array, correspondingly, install some teeth groove hole wall with annular array, tooth locks with coordinated drilling auxiliary member and body the relative circumferential position of teeth groove; Or,
Install some teeth hole wall with annular array, correspondingly, the periphery of drilling auxiliary member has some teeth groove of annular array, tooth locks with coordinated drilling auxiliary member and the body circumference relative position of teeth groove.
Drilling auxiliary member has multiple, and their eccentric orfice aperture eccentric throw that is not identical and/or eccentric orfice is not identical, to select suitable drilling auxiliary member, realizes delineation and is more suitable for removal scope.During use, according to flaw size and size, select suitable drilling auxiliary member.
The outer end of drilling auxiliary member has the outward flange that external diameter is greater than aperture, installing hole I outer end, is convenient to the replacement of drilling auxiliary member.
Body also has the elongated hole-shape installing hole II 12 being scattered in installing hole I periphery that at least two axis run through body, in each installing hole II, installing is used for assisting the auxiliary fixing member 4 be fixed on by body on Aircraft Metal Structure, auxiliary fixing member has the elongated hole 41 that the axial fastening spiral 6 of confession running through itself wears, auxiliary fixing member entirety is in long annular, the width of elongated hole is identical with the fastener hole aperture just right with this elongated hole, this fastener hole is positioned at around crackle fastener hole to be removed, the outer end of auxiliary fixing member has the outward flange that size is greater than installing hole II, wherein at least two auxiliary fixing member are vertically arranged.The outer end of auxiliary fixing member has the outward flange that size is greater than installing hole II, and when can realize using, body is fixed on Aircraft Metal Structure, is convenient to the replacement of auxiliary fixing member.The fastener hole of two vertically disposed auxiliary fixing member and Aircraft Metal Structure is just right, and can realize the relative fixing of body and Aircraft Metal Structure by fastening bolt.
Auxiliary fixing member has multiple, and their outer peripheral face is measure-alike, and the elongated hole width of auxiliary fixing member not of the same race is different to mate from different fastener hole.
Installing hole II is four, and lay respectively at four angles place of rectangle, be divided into two groups, often group comprises two that be arranged in parallel, and the installing hole II in a group is vertical with the installing hole II in another group to be arranged.
Body can also be fixed on Aircraft Metal Structure by fixture.Body is plate.Eccentric orfice is circular hole.
Around the fastener hole of Aircraft Metal Structure, the removal aid of crackle adopts the CRES corrosion-resistant stainless steel meeting Boeing material standard to make.This material has higher intensity, good machining property, good moldability, resistant to rust, and Surface Finishing is good.
Claims (10)
1. the removal aid of crackle around the fastener hole of an Aircraft Metal Structure, it is characterized in that: the drilling auxiliary member being fixed on the body on Aircraft Metal Structure when comprising use and being installed on body in installing hole I, installing hole I runs through body, drilling auxiliary member and installing hole I coaxial line are installed, drilling auxiliary member has several stations in the circumferential, can locking at each station place drilling auxiliary member and body the relative circumferential position, drilling auxiliary member having the eccentric orfice for drawing a circle to approve removal scope axially running through auxiliary member.
2. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 1, it is characterized in that: some locating slots installing hole I hole wall with circumference distribution, the periphery of drilling auxiliary member has locating slot, on hole wall, on locating slot and periphery, locating slot all axially extends, and alignment pin is arranged in simultaneously and locating slot and periphery completes drilling auxiliary member during locating slot to hole wall and body the relative circumferential position locks; Or,
The periphery of drilling auxiliary member have some locating slots of circumference distribution, install on hole wall and there is locating slot, on hole wall, on locating slot and periphery, locating slot all axially extends, and alignment pin is arranged in simultaneously and locating slot and periphery completes drilling auxiliary member during locating slot to hole wall and body the relative circumferential position locks; Or,
The periphery of drilling auxiliary member has some teeth of annular array, correspondingly, install some teeth groove hole wall with annular array, tooth locks with coordinated drilling auxiliary member and body the relative circumferential position of teeth groove; Or,
Install some teeth hole wall with annular array, correspondingly, the periphery of drilling auxiliary member has some teeth groove of annular array, tooth locks with coordinated drilling auxiliary member and the body circumference relative position of teeth groove.
3. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 1 and 2, it is characterized in that: drilling auxiliary member has multiple, their eccentric orfice aperture eccentric throw that is not identical and/or eccentric orfice is not identical.
4. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 1 and 2, is characterized in that: the outer end of drilling auxiliary member has the outward flange that external diameter is greater than aperture, installing hole I outer end.
5. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 1 and 2, it is characterized in that: body also has the elongated hole-shape installing hole II being scattered in installing hole I periphery that at least two axis run through body, in each installing hole II, installing is used for assisting the auxiliary fixing member be fixed on by body on Aircraft Metal Structure, auxiliary fixing member has the elongated hole that the axial fastening spiral of confession running through itself wears, auxiliary fixing member entirety is in long annular, the width of elongated hole is identical with the fastener hole aperture just right with this elongated hole, this fastener hole is positioned at around crackle fastener hole to be removed, the outer end of auxiliary fixing member has the outward flange that size is greater than installing hole II, wherein at least two auxiliary fixing member are vertically arranged.
6. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 5, it is characterized in that: auxiliary fixing member has multiple, their outer peripheral face is measure-alike, and the elongated hole width of auxiliary fixing member not of the same race is different to mate from different fastener hole.
7. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 5, it is characterized in that: installing hole II is four, lay respectively at four angles place of rectangle, be divided into two groups, often group comprises two that be arranged in parallel, and the installing hole II in a group is vertical with the installing hole II in another group to be arranged.
8. around the fastener hole of Aircraft Metal Structure according to claim 1 and 2, the removal aid of crackle, is characterized in that: body is fixed on Aircraft Metal Structure by fixture.
9. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 1 and 2, it is characterized in that: body is plate, eccentric orfice is circular hole.
10. the removal aid of crackle around the fastener hole of Aircraft Metal Structure according to claim 1 and 2, is characterized in that: adopt the CRES corrosion-resistant stainless steel meeting Boeing material standard to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520353824.7U CN204843030U (en) | 2015-05-28 | 2015-05-28 | Crackle gets rid of appurtenance around aircraft metallic structure's fastener hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520353824.7U CN204843030U (en) | 2015-05-28 | 2015-05-28 | Crackle gets rid of appurtenance around aircraft metallic structure's fastener hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204843030U true CN204843030U (en) | 2015-12-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520353824.7U Withdrawn - After Issue CN204843030U (en) | 2015-05-28 | 2015-05-28 | Crackle gets rid of appurtenance around aircraft metallic structure's fastener hole |
Country Status (1)
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| CN (1) | CN204843030U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105149642A (en) * | 2015-05-28 | 2015-12-16 | 山东太古飞机工程有限公司 | Auxiliary tool for removing cracks around fastener hole of airplane metal structure |
-
2015
- 2015-05-28 CN CN201520353824.7U patent/CN204843030U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105149642A (en) * | 2015-05-28 | 2015-12-16 | 山东太古飞机工程有限公司 | Auxiliary tool for removing cracks around fastener hole of airplane metal structure |
| CN105149642B (en) * | 2015-05-28 | 2017-05-24 | 山东太古飞机工程有限公司 | Auxiliary tool for removing cracks around fastener hole of airplane metal structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20151209 Effective date of abandoning: 20170524 |