CN203343705U - Boeing aircraft airtight support plate nut installation process device - Google Patents
Boeing aircraft airtight support plate nut installation process device Download PDFInfo
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- CN203343705U CN203343705U CN 201320435838 CN201320435838U CN203343705U CN 203343705 U CN203343705 U CN 203343705U CN 201320435838 CN201320435838 CN 201320435838 CN 201320435838 U CN201320435838 U CN 201320435838U CN 203343705 U CN203343705 U CN 203343705U
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Abstract
The utility model discloses a Boeing aircraft airtight support plate nut installation process device, which comprises a first process assembly, a second process assembly, a third process assembly and a fourth process assembly, wherein the second process assembly is propping iron, the anvil face of the propping iron is provided with a via hole which is matched with the top of an airtight support plate nut seal, and two opposite satellite holes, which are symmetrical about the via hole, are formed in the rest part of the anvil face; the third process assembly comprises a pre-tightening bolt and an axial positioning sleeve, the pre-tightening bolt is used for penetrating through a screw hole to be connected with an airtight support plate nut, the screw rod of the pre-tightening bolt is sleeved by the axial positioning sleeve, and the axial positioning sleeve is positioned at the bolt head side of the pre-tightening bolt of a skin; the fourth process assembly is the head of a riveting gun, the working face of the head is provided with an axial positioning hole, the axial positioning hole is guided by the axial positioning sleeve, and the working face covers the two satellite holes. The Boeing aircraft airtight support plate nut installation process device disclosed by the utility model can be used for improving the installation quality of the airtight support plate nut.
Description
Technical field
The utility model relates to the airtight plate nut mounting process of a kind of Boeing equipment.
Background technology
In aircraft maintenance work, fuselage radome fairing or this class of freight house wear strip for example are installed and need to see through pressurizing area and usually adopt airtight plate nut fitted bolt realization connection being connected of non pressurized zone.As shown in Fig. 1 middle and upper part, the airtight plate nut 10 of this class have the sealing top (its main part) of the round table-like or ladder arched roof shape of ladder and bottom (lower end in figure) with a rubber seal 11, by the satellite hole 12 that is symmetrically distributed in screw hole 3 both sides, the side generation extruding force after rivet, rubber seal 11 contacted with far-end covering (inside panel) 2 is installed and compresses and produce plastic deformation, and play the effect of sealing.
Due to the instrument that airtight plate nut is installed that is specifically designed to not yet being arranged at present, the existing general utility tools such as alignment pin, riveting gun, top iron that adopt are installed fastening rivet one by one.Therefore, existing airtight plate nut flow of installation has following shortcoming:
1. first alignment pin be inserted into to the corresponding screw hole of airtight plate nut 10 or mate in a securing member installing hole in satellite hole 12 via the screw hole 3 on covering or satellite hole 12 in above-mentioned technical process, utilizing the axial tension of alignment pin that airtight plate nut 10 is adjacent to far-end covering 2.The axial tension that only depends on interference fit to produce because of alignment pin, relatively little, the crimp that causes airtight plate nut base to produce because of rivet pier nose moulding meeting after first fastening rivet of installation, and the axial tension of alignment pin is not enough to overcome this distortion, the fine and close seal 11 of final guide rubber and covering laminating are not tight, and then cause pressurization gas or leak of liquid in body, bring potential safety hazard to aircraft flight.
2. the installation procedure technique of traditional airtight plate nut 10 efficiency that wastes time and energy is low.During examination, whether the worker only fits closely with covering with the rubber seal 11 of the airtight plate nut 10 of visual judgement, the inadequate rigorous and scientific of the method for inspection.Can't fundamentally guarantee the rubber seal 11 of airtight plate nut 10 and effective laminating of far-end covering 2, completing installation quality and the air-tightness of rivet after installing can't guarantee.
3. owing to varying in housing construction, common riveting gun head and top iron is for want of effectively supporter and object of reference often, can't complete the installation of two rivets simultaneously.And easily because vibrations make riveting gun head and top iron, produce significantly displacement radially and beat when riveted joint, the former usually makes near-end covering 1 surface produce pit and damage pneumatic flatness and the safety in utilization that is unfavorable for aircraft, the latter usually damages the overlay coating of airtight plate nut 10, affects airtight plate nut 10 anti-corrosion properties energy and durable usability.
4., when choosing 12 installation fastening rivet in satellite hole around the screw hole on fuselage skin 3, after generally adopting Steel Ruler measurement size data, with marking pen, transfer to screw hole 3 mark 12 positions, satellite hole, both sides.This method error more greatly can't be accurately be distributed in screw hole 3 both sides by satellite hole 12 symmetries.
In addition, on covering, drill through when the satellite hole 12 of fastening rivet is installed, what Structure Repair Manual required satellite hole 12 axially should be perpendicular to the covering plane, if covering is thicker, rely on merely worker's skills and experience relatively large deviation can easily occur, cause satellite hole 12 axially and covering plane out of plumb, finally cause satellite hole 12 and the fastening rivet installing hole of airtight plate nut 10 disalignment on covering, satellite hole 12 pitch-rows and the fastening rivet hole pitch-row of airtight plate nut 10 on covering are inconsistent, the lighter is installing on faying face air-tightness and the airworthiness that there will be assemblage gap and affect aircraft, severe one can cause airtight plate nut to install.
Summary of the invention
Therefore, the purpose of this utility model is to provide the airtight plate nut of a kind of Boeing special-purpose mounting process equipment, to improve the installation quality of airtight carriage nut.
The utility model is by the following technical solutions:
According to an aspect of the present utility model, the airtight plate nut mounting process of a kind of Boeing equipment comprises:
The first technique component, there is a cuboid piece, a face of this cuboid piece be provided with perpendicular to this face to be positioned the tighten up a screw coaxial positioning pin in hole of covering, and then, have the satellite hole pilot hole that a pair of axis for satellite hole drill pin drill bit guiding is parallel to the coaxial positioning pin on the cuboid piece, and two satellite hole pilot holes are about the axis shaft symmetry of coaxial positioning pin;
The second technique component, be a top iron, and the anvil face of this top iron has the via hole at the airtight plate nut sealing of coupling top, partly covers two satellite holes of correspondence about the anvil face of this via hole symmetry;
The 3rd technique component, comprise one for through described screw hole with the pretension bolt that connects airtight plate nut be placed in the axial positioning sleeve on this pretension bolt screw rod, this axial positioning sleeve is positioned at the pretension bolt bolt head place side of covering; And
The 4th technique component, for working face has the riveting gun head in axial location hole, wherein the axial location hole is directed at described axial positioning sleeve, and working face covers two satellite holes.
According to the utility model, carry out satellite hole pore-forming by the first technique component, due to the first technique component by the coaxial positioning pin location in screw hole, guarantee the reference precision of satellite hole pore-forming, coordinate again the pier nose moulding of simultaneously two rivets being carried out manufactured head with the riveting gun head by top iron, not only improved working (machining) efficiency, and the crimp of thoroughly having stopped because of the rivet pier nose, airtight plate nut base to be produced after first fastening rivet of installation further causes rubber seal and covering untight problem of fitting, guarantee the quality of airtight plate nut riveted joint.Because the riveting gun head is led by axial positioning sleeve, it can only in axial direction be moved, when construction, it is produced to constraint and the support that footpath makes progress, can, because vibrations cause damage to structure on every side, further not guarantee the quality of processing.
The airtight plate nut mounting process of above-mentioned Boeing equipment produces damage when riveting airtight plate nut and covering for fear of covering, described the first technique component disposes neonychium at the face that is provided with the coaxial positioning pin.
The airtight plate nut mounting process of above-mentioned Boeing equipment, described neonychium gluing is mounted on corresponding surface, is convenient to change, and has certain adhesive force, guarantees carrying out smoothly of processing.
The airtight plate nut mounting process of above-mentioned Boeing equipment, described cuboid piece is provided with the leader in the Wei Di side, side to be provided with the coaxial positioning pin, the convenient cuboid piece of controlling.
The airtight plate nut mounting process of above-mentioned Boeing equipment, described top iron has three anvil faces, and wherein a pair of anvil face is parallel relatively, remainings an anvil face and parallel two anvil face quadratures, has reasonable adaptability.
The airtight plate nut mounting process of above-mentioned Boeing equipment, be communicated with the U-lag that forms top iron one termination, compact conformation corresponding to two via holes of two anvil faces of quadrature.
The accompanying drawing explanation
Fig. 1 is the explosive view that cloth hole, a kind of satellite hole device is at the use state.
The explosive view that Fig. 2 is the corresponding frock adaptation of airtight plate nut mounting process.
The structural representation that Fig. 3 is a kind of many anvil faces top iron.
In figure: 1. near-end covering, 2. far-end covering, 3. screw hole, 4. coaxial positioning pin; 5. neonychium, 6. satellite hole pilot hole, 7. vertical hole guiding device, 8. cloth hole device handle; 9. many anvil faces top iron, 10. airtight plate nut, 11. rubber seal, 12. satellite holes; 13. fastening rivet, 14. axial location sleeves, 15. pretension bolts, 16. axial location holes; 17. the riveting gun head, 18. anvil face A, 19. ladder round platform grooves; 20. anvil face B, 21.U type groove, 22. anvil face C.
The specific embodiment
With reference to Figure of description 1, relate to used the first technique component for accurately punching, can the drill bit of punching be led, guarantee the positional precision between hole and screw hole 3, the hole here on covering, near-end covering 2 and far-end covering 1 overlapping portion as shown in Figure 1.
Should be appreciated that near-end is to take the orientation that airtight plate nut 10 is reference, airtight plate nut 10 sides are near-end, and contrary orientation is far-end.
Screw hole 3 herein, for refering in particular to, namely mates the screw hole 3 on covering that is positioned at of airtight plate nut 10, as illustrated in fig. 1 and 2.
Drilling tool in Fig. 1 is vertical hole guiding device 7, and its main body is a rectangular structure, and the above has pair of satellite pilot hole 6, for lead plug, leads.
Should be appreciated that about the satellite hole distribution hole that to be expressed as about screw hole 3 axles be axle center.So near and, be provided with coaxial positioning pin 4 with corresponding screw hole 3 on the covering opposite face at vertical hole guiding device 7 in Fig. 1, two satellite guidance holes 6 are about the axis shaft symmetry of this coaxial positioning pin 4 so.
The concept that coaxial positioning pin 4 is alignment pin is retrained, according to general understanding mechanically, alignment pin adopts hole pin interference fit to realize accurately location usually, can be understood as coaxial positioning pin 4 at this and coordinate and form location by corresponding hole pin with screw hole 3, the position of adjusting so vertical hole guiding device 7 just can meet the accurate location in satellite hole 12.
Coaxial steady pin 4 is vertical with the bottom surface of vertical hole guiding device 7 in Fig. 1, as for perpendicularity, is that technique guarantees, more accurate better.
The lower end of coaxial steady pin 4 can be carried out chamfering or lead circle, to facilitate, it is imported to screw hole 3.
In the structure shown in Fig. 1; also is furnished with neonychium 5; perforate mode by the perforate mode of neonychium 5 with screw hole 3 and satellite hole 12; corresponding with vertical hole guiding device 7; the adhesive and the bottom surface that after contacting with vertical hole guiding device 7 bottom surfaces by alignment pin 4, with material number, are BMS5-95 are bonding, guarantee that the hole above neonychium 5 is coaxial with the institute's corresponding aperture on vertical hole guiding device 7.
In the structure shown in Fig. 1, vertical hole guiding device 7 also is furnished with the device of deploying to ensure effective monitoring and control of illegal activities handle 8, on long side surface as shown in Figure 1, vertically connects, and also can left-right symmetry connect each handles, does not affect boring.
Hold handle 8 in far-end covering 2 sides, coaxial positioning pin 4 is inserted in screw hole 3, wherein screw hole 3 coordinates for the hole axle with coaxial positioning pin 4, and radial dimension is identical, can be considered based on matched in clearance, guarantees the precision of location.
Holding handle 8 rotates to proper angle; make the design attitude of satellite hole guide hole 6 in satellite hole 7; certainly; still can not adjust vertical hole guiding device 7 if there is no handle; then firmly compress, make neonychium 5 be close to far-end covering 2, then the 40# drill jig is held on air drill; take vertical hole guiding device 7 satellite hole pilot hole 6 as the guiding, get out satellite hole 12 on near-end covering 1 and far-end covering 2.
Due to the most standardization of the parts on Boeing, thus this paper relate to as airtight plate nut 10 be also standard component, the parameter in corresponding satellite hole 12 is also determined, mates 40# drill bit described above and is processed.
In this process; neonychium 5 quality of rubber materials hardness used is less than covering aluminum alloy material used; can guarantee can not damage covering in rotation cloth hole; satellite hole pilot hole 6 above simultaneously vertical hole guiding device 7 plays the effect of plumb; can guarantee that got out satellite hole 12 is axially perpendicular to the covering plane; the spacing in two satellite holes 10 equates that with the securing member installing hole distance of installed airtight plate nut the securing member here corresponds to fastening rivet 13.
Behind the location of coaxial positioning pin 4, screw hole 3 is identical to the distance of screw hole with the securing member installing hole of airtight plate nut 10 with the distance in two satellite holes 12, above-mentioned two constraintss can guarantee fastening rivet 13] and the securing member installing hole of airtight plate nut 10 and the satellite hole 12 on covering there is higher axiality, meet the installation of airtight plate nut 10 to guarantee the satellite hole 12 processed.
Erection unit and the technique of below further combined with installation and the accompanying drawing 1-3 of airtight plate nut 10, describing the airtight plate nut of Boeing.
With reference to Fig. 2, it is airtight plate nut mounting process explosive view.After satellite hole on the near-end covering is made into to counter sink, again by fastening rivet 13 after the securing member installing hole through the satellite hole 12 on covering and airtight plate nut 10, make pretension bolt 15 make airtight plate nut 10 and the laminating of covering distal flat surface through axial location sleeve 14 and the rear power that applies 30LB with screw gun or torque wrench of screw hole 3 successively.
Wherein pretension bolt 15 is as the part of the 3rd technique component, and for the pre-pressing of airtight plate nut 10, naturally its screw thread should be consistent with the screw thread of airtight plate nut 10, screw rod can comprise polished rod and two parts of screw mandrel, can be also only screw mandrel.
In the structure shown in Fig. 2, the screw portion of pretension bolt 15 comprises screw mandrel and polished rod, wherein the polished rod part is supporting an axial positioning sleeve 14, and the bolt head by pretension bolt 15 is pressed on near-end covering 1, and the polished rod part coordinates the reliable positioning guide column of formation with axial positioning sleeve 14.
And correspondingly, contain riveting gun head 17 As shown in the lower part of Figure 2 in the 4th technique component, its working face namely its upper surface has centre bore, namely the axial location hole 16, axial location hole 16 coordinates formation guide pillar guide sleeve structure with axial positioning sleeve 14 axle sleeves, riveting gun head 17 is formed to guide effect, for the pier nose of fastening rivet 13.
In the structure shown in Fig. 2, more clearly finds out, the setting based on symmetrical structure makes two fastening rivets 13 be covered under the working face of riveting gun head 17 in satellite hole 12 in other words.
Corresponding to pier nose technique, be furnished with top iron in far-end covering 2 sides, in the structure shown in Fig. 2, the top iron that uses is many anvil faces top iron 9, has met the installation of the airtight plate nut 10 of multiple application site.
As for top iron, nature need to have anvil face, should get out of the way the sealing top of airtight plate nut 10 simultaneously, namely in structure as shown in Figure 2 except the part of base, therefore, have via hole on anvil face, to get out of the way the sealing top, mate 12 position, satellite hole simultaneously and there is again the anvil face part.
In the structure shown in Fig. 2, many anvil faces top iron 9 has three anvil faces, wherein a pair of anvil face is parallel relatively, upper and lower surface as shown in Figure 2, remaining an anvil face and parallel two anvil face quadratures, the left surface of many anvil faces top iron 9 in Fig. 2, like this, can use different anvil faces in different positions, so that it has more application, and overall structure does not have therefore become too fat to move.
Further, for simplified structure, as shown in Fig. 2 top, corresponding to two via holes of two anvil faces of quadrature, be communicated with the U-lag that forms top iron one termination.
Because the existence of this pretightning force makes the rubber seal 11 on airtight plate nut 10 can produce strain and touch the far-end skin-surface, and this pretightning force with finally complete airtight plate nut after the moment of required mounting screw identical, can guarantee the optimum sealing of seal washer.During applying pretightning force, the constraint that fastening rivet 13 can produce on circumferencial direction airtight plate nut 10, make it can not produce the rotation on circumferencial direction along with the frictional force between screw thread pair.
Many anvil faces top iron 9 is placed in to airtight plate nut 10 rears, (with reference to Fig. 3: many anvil faces top iron is used schematic diagram) can select different anvil faces according to the complexity that approaches of position, wherein ladder round platform groove 19 is removed design of material according to the profile of airtight plate nut 10, the projection of airtight plate nut 10 can be inserted wherein, and make both coaxial, now anvil face A18 is as anvil face.U-shaped groove 21 is removed design of material according to the profile of airtight plate nut 10, if anvil face A18 can't be used in present position, by U-shaped groove 21, selects anvil face B20 or anvil face C22, as rivet, anvil face is installed airtight plate nut 10 and uses.
In said process, the working face of anvil face A18, anvil face B20, anvil face C22 and riveting gun head 15 all can cover the technique head of two fastening rivets 13 simultaneously, can be simultaneously by two disposable while installation formings of rivet in the time of installation, when significantly improving operating efficiency, thoroughly stopped after first fastening rivet of installation because of rivet pier nose moulding meeting to the plate nut base produce crimp cause sealing ring and the covering laminating not tight, the potential safety hazard that causes gas and leak of liquid to cause.
Material is selected: neonychium 5 use rubber are made; coaxial positioning pin 4, vertical hole guiding device 7, cloth hole device handle 8 be common to be formed vertical cloth hole, satellite hole device coaxial positioning pin 4, vertical hole guiding device 7, cloth hole device handle 8 and adopts No. 45 steels to do, but machined one-body molded also can be under the prerequisite that guarantees precision welding production.
Many anvil faces top iron 9 adopts No. 45 steels to do, and has and processes preferably intensity and hardness.Riveting gun head 17 adopts No. 45 steels to do, and the working face contacted with the rivet technique head adopts mirror finish to process, and to prevent that the technique head of rivet is produced to damage, axial location sleeve 14 adopts the 2024-T3 aluminum alloy materials to make.
The airtight plate nut 10 mounting process engineering drawings of Boeing carry out processing and fabricating.Airtight plate nut 10 and fastening rivet 13 selection works are implemented desired Boeing standard component, and pretension bolt 15 is selected Boeing standard component BACB30VF.
Claims (6)
1. the airtight plate nut mounting process of a Boeing equipment, is characterized in that, comprising:
The first technique component, there is a cuboid piece, a face of this cuboid piece be provided with perpendicular to this face to be positioned the tighten up a screw coaxial positioning pin in hole of covering, and then, have the satellite hole pilot hole that a pair of axis for satellite hole drill pin drill bit guiding is parallel to the coaxial positioning pin on the cuboid piece, and two satellite hole pilot holes are about the axis shaft symmetry of coaxial positioning pin;
The second technique component, be a top iron, and the anvil face of this top iron has the via hole at the airtight plate nut sealing of coupling top, partly covers two satellite holes of correspondence about the anvil face of this via hole symmetry;
The 3rd technique component, comprise one for through described screw hole with the pretension bolt that connects airtight plate nut be placed in the axial positioning sleeve on this pretension bolt screw rod, this axial positioning sleeve is positioned at the pretension bolt bolt head place side of covering; And
The 4th technique component, for working face has the riveting gun head in axial location hole, wherein the axial location hole is directed at described axial positioning sleeve, and working face covers two satellite holes.
2. the airtight plate nut mounting process of Boeing according to claim 1 equipment, is characterized in that, described the first technique component disposes neonychium at the face that is provided with the coaxial positioning pin.
3. the airtight plate nut mounting process of Boeing according to claim 2 equipment, is characterized in that, described neonychium gluing is mounted on corresponding surface.
4. according to the airtight plate nut mounting process of the arbitrary described Boeing of claims 1 to 3 equipment, it is characterized in that, described cuboid piece is provided with the leader in the Wei Di side, side to be provided with the coaxial positioning pin.
5. the airtight plate nut mounting process of Boeing according to claim 1 equipment, is characterized in that, described top iron has three anvil faces, and wherein a pair of anvil face is parallel relatively, remainings an anvil face and parallel two anvil face quadratures.
6. the airtight plate nut mounting process of Boeing according to claim 5 equipment, is characterized in that, corresponding to two via holes of two anvil faces of quadrature, is communicated with the U-lag that forms top iron one termination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320435838 CN203343705U (en) | 2013-07-22 | 2013-07-22 | Boeing aircraft airtight support plate nut installation process device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320435838 CN203343705U (en) | 2013-07-22 | 2013-07-22 | Boeing aircraft airtight support plate nut installation process device |
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| Publication Number | Publication Date |
|---|---|
| CN203343705U true CN203343705U (en) | 2013-12-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320435838 Expired - Fee Related CN203343705U (en) | 2013-07-22 | 2013-07-22 | Boeing aircraft airtight support plate nut installation process device |
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| CN (1) | CN203343705U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103386600A (en) * | 2013-07-22 | 2013-11-13 | 山东太古飞机工程有限公司 | Boeing aircraft airtight support plate nut installation process device and process |
| 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 |
-
2013
- 2013-07-22 CN CN 201320435838 patent/CN203343705U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103386600A (en) * | 2013-07-22 | 2013-11-13 | 山东太古飞机工程有限公司 | Boeing aircraft airtight support plate nut installation process device and process |
| CN103386600B (en) * | 2013-07-22 | 2015-09-02 | 山东太古飞机工程有限公司 | Boeing airtight plate nut mounting process instrument and supplies |
| 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131218 Termination date: 20160722 |
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| CF01 | Termination of patent right due to non-payment of annual fee |