CN102205488A - Method for processing hole in split-sleeve cold extrusion manner - Google Patents
Method for processing hole in split-sleeve cold extrusion manner Download PDFInfo
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- CN102205488A CN102205488A CN2010101374117A CN201010137411A CN102205488A CN 102205488 A CN102205488 A CN 102205488A CN 2010101374117 A CN2010101374117 A CN 2010101374117A CN 201010137411 A CN201010137411 A CN 201010137411A CN 102205488 A CN102205488 A CN 102205488A
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Abstract
The invention relates to a method for processing a hole in a split-sleeve cold extrusion manner, which comprises the following steps: drilling a primary hole; reaming the primary hole; checking a diameter of the hole; checking a core rod; performing cold extrusion on the hole; checking the diameter of the hole after being subject to the cold extrusion; finely reaming the hole; and checking the diameter of the final hole. The method is characterized in that the process of drilling the primary hole is finished after drilling and broaching the hole for several times and the broaching quantity each time is controlled in 0.065 second. According to the method for processing the hole in the split-sleeve cold extrusion manner provided by the invention, the different diameters are processed for different times by utilizing the drilling and reaming tools in different sizes. A plug-gauge check result shows that the prepared primary hole meets the demand, thereby ensuring the requirement of the follow-up split-sleeve cold extrusion process.
Description
Technical field
The present invention relates to the processing of aircraft zero/assembly, particularly relate to processing technology the connecting hole of aircraft zero/all kinds of connection securing members of component assembling (as high locked bolts, bolt at materials such as aluminium, mild steel, titanium, high strength steels).
Background technology
In the aviation process industry, improve the fatigue life that aircaft configuration connects, it is one of everybody important technological problems of generally being concerned about, its coverage is very extensive, therefore study and strive improving between the aircaft configuration and structure and connector between be connected fatigue life, be a very significant job.
At present, the main method of attachment that aircraft structure adopts is a mechanical connection, and more than 100 ten thousand connectors are housed on the large aircraft.In order to satisfy the requirement of present generation aircraft high life, external many famous planemakers spend lot of manpower and material resources and financial resources are intended to improve the research work in aircraft jointing life-span to it, improve constantly competitiveness and occupation rate of market, obtain economic benefit.
Reached for 80,000 pilot time the fatigue life of many advanced aircrafts in the world today, even higher.In order to make the aircaft configuration of high life, must can reach by many-sided joint efforts such as design, material, technology and working services.Therefore, making the aircaft configuration of high life is a very complicated system works.
Cold-extrusion technology is to improve the connector hole new way of fatigue life, the cold expanding hole is also named in the cold extrusion hole usually, its mechanism be at room temperature utilize the high strength compression tool to hole wall, chamfering, immerse oneself in to exert pressure around nest and the hole, make the metal surface that is extruded the position that plastic deformation take place, form the residual compressive stress layer, thereby reach the purpose that improves structure fatigue life.
Cold-extrusion technology is used for the region of high stress, is used to improve the fatigue life of structural member.This cold work reinforced method is when metal is pushed, metal produces plastic deformation, when extrusion process finishes, the refinement of the crystal grain of metal material, the skin-material micro-hardness improves, microscopic asperity reduces, thereby improved YIELD STRENGTH, and the fatigue behaviour of metal material and yield strength are linear relationship within the specific limits, so hole wall, angle, garden and immerse oneself in all to make after the garden arc cold extrusion (stress impression) at the bottom of the nest change of hole wall plasticity to swell, form the residual compressive stress field, delay directly to center on the crackle appearance and the diffusion of bore region, thereby improve the fatigue life in hole.
The method in cold extrusion hole has three kinds usually: the one, and the not cold extrusion of belt material cover; The 2nd, the cold extrusion of band slotted liner bushing after the extruding is removed slotted liner bushing; Also having a kind of is with the not cold extrusion of slotted liner bushing, and the extruding back bush will be retained in the hole.
The slotted liner bushing cold extrusion is to aircraft zero/all kinds of connection securing member of component assembling high locked bolts, the bolt reinforcement process at material connecting holes such as aluminium, mild steel, titanium, high strength steel (aperture is between 0.125～1.0 " between); can apply effective residual compressive stress to the top layer of Strengthening Hole, increase substantially the endurance cracking resistance line performance in hole.
Will guarantee in the slotted liner bushing cold-extrusion technology that last essence twists whole hole and can satisfy process specification requirements, boring just, the hole is crucial.Adopting the slotted liner bushing cold extrusion to strengthen securing member connecting hole position is wing body docking area, and butt joint location space is limited, and the technology path is relatively poor, can only adopt hand-made hole.The securing member pre-manufactured hole will pass through the material of 4～5 layers of different-thickness, maximum ga(u)ge 52mm, and maximum gauge 19.05mm, the hand-made hole difficulty is very big.
Aircraft connector hole is made the continuous research of branch art technology along with us, practice and application, the aircraft manufacturing level of China is attained a new height again, will constantly prolong fatigue life, our aircraft is constantly improved at aspects such as security, economy thereby aircaft configuration is connected.This not only will produce remarkable economic efficiency, but also can bring the important social benefit.
Summary of the invention
The method, the particularly processing technology in first hole that the purpose of this invention is to provide a kind of slotted liner bushing cold extrusion processing connecting hole are with the first hole of processing accurately and efficiently, the fatigue life of improving connecting hole through the cold extrusion of being cracked in first hole again.
In the production of airplane component, the connecting hole for zero/all kinds of connection securing members of component assembling twists whole hole and can satisfy process specification requirements in order to guarantee last essence, and boring just, the hole is crucial.
Make the whole hole after the slotted liner bushing cold extrusion satisfy technological requirement, key is to prepare qualified first hole earlier., in acceptability limit, could guarantee follow-up cold extrusion, finish ream, whole hole detects and meet the demands in the first hole that needs before the cold-extrusion technology to prepare.
Usually the preparation section of fastener hole (being connecting hole) is as follows:
Brill hole → hinge hole → measurement hole → cold extrusion just just just → finish ream the such several steps in the smart hole of hole → measurement, but practical operation is difficult to reach requirement.
The present invention proposed repeatedly to bore the first hole of reaming preparation, and the number of times of brill reaming requires definite technical scheme according to first bore dia in order to address this problem.
Slotted liner bushing cold extrusion of the present invention prepares the method in hole, comprising: bore hole just; Hinge is the hole just; The diameter of inspection opening; Check plug; Cold extrusion is carried out in the hole; Check the diameter in cold extrusion hole; Finish ream the hole; Check whole bore dia; Wherein, when boring just the hole, bore reaming preparation holes just through at least three times, the boring hole enlargement amount of initial 1 time, 2 times or 3 times is controlled at each 0.055 "～0.065 " and (is expressed as in sometimes, refer to that unit be inch), the boring hole enlargement amount of last 1 time, 2 times or 3 times is controlled at each 0.010 "～0.032 ".
Preferably, the brill reaming mass runoff between initial 1 time, 2 times or 3 times and last 1 time, 2 times or 3 times is controlled at each 0.032 "～0.055 ".
Preferably, as nominal diameter (being the external diameter of standard component) is 3/8 " time, bore the reaming number of times by three times and finish brill hole just, wherein; initial twice boring hole enlargement amount is controlled at each 0.055 "～0.065 ", last boring hole enlargement amount is controlled at 0.010 "～0.032 ".
As nominal diameter is 7/16 " time, finish and bore hole just by boring reaming for four times, wherein, the boring hole enlargement amount of the junior three time is controlled at each 0.055 "～0.065 ", and last boring hole enlargement amount is controlled at 0.010 "～0.032 ".
As nominal diameter is 9/16 " time, finish and bore hole just by boring six reamings, wherein, the boring hole enlargement amount of the junior three time is controlled at each 0.055 "～0.065 ", and last twice boring hole enlargement amount is controlled at each 0.010 "～0.032 ".
As nominal diameter is 12/16 " time, finish and bore hole just by boring reaming for ten times, wherein, the boring hole enlargement amount of the junior three time is controlled at each 0.055 "～0.065 ", and last three times boring hole enlargement amount is controlled at each 0.010 "～0.032 ".
Preferably, the reaming mass runoff of the brill reaming between initial 1 time, 2 times or 3 times and last 1 time, 2 times or 3 times preferably is controlled at each 0.032～0.055 ".
In boring just the hole,, also comprise fraising when the number of times that bores reaming during more than four times.
Preferably, after brill reaming four times, bore reaming and fraising and hocket.
Preferably, the amount of each fraising is 0.010～0.032 ".
Preferably, bore in the first hole, bit diameter is 0.1935 first ".
Preferably, when nominal diameter was 3/8 inch, the boring flow process comprises: head bored 0.1935 ", brill diffuses into 0.2490 for the first time ", brill diffuses into 0.3120 for the second time ", expand Shen to 0.3437 for the third time ", and finish ream 0.3700 ".
Preferably, when nominal diameter was 7/16 inch, the boring flow process comprised: head brill 0.1935 ", the first time, brill diffused into 0.2490 ", brill diffuses into 0.3120 for the second time ", brill diffuses into 0.3740 for the third time ", the 4th expansion Shen to 0.4062 ", finish ream 0.4325 ".
Preferably, when nominal diameter was 9/16 inch, the boring flow process comprised: first brill 0.1935 ", brill diffuses into 0.2490 for the first time ", bore for the second time and diffuse into 0.3120 "; brill diffuses into 0.3740 for the third time ", No. the 4th time brill diffuses into 0.4219 ", cut with scissors 0.4370 for the first time ", No. the 5th time brill diffuses into 0.4688 "; cut with scissors 0.4995 for the second time ", the 6th expansion Shen to 0.5156 ", and finish ream 0.5570 ".
Preferably, when nominal diameter is 3/4 inch, the flow process of holing is comprising: head brill 0.1935 "; brill diffuses into 0.2490 for the first time ", brill diffuses into 0.3120 for the second time ", brill diffuses into 0.3740 for the third time ", No. the 4th time brill diffuses into 0.4219 "; cut with scissors 0.4370 for the first time ", No. the 5th time brill diffuses into 0.4688 ", cut with scissors 0.4995 for the second time ", No. the 6th time brill diffuses into 0.5312 "; cut with scissors 0.5620 for the third time ", No. the 7th time brill diffuses into 0.5938 ", cut with scissors 0.6245 for the third time ", expand Shen to 0.6445 the 8th time "; the 9th expansion Shen to 0.6645 ", the tenth expansion Shen to 0.6875 ", and finish ream 0.7495 ".
Preferably, in the first hole of above-mentioned brill, before finish reaming, also comprise hinge just, check and cold extrusion.
Preferably, in the first hole of above-mentioned brill, after finish reaming, also comprise the feeler gauge check.
Certainly, method of the present invention is not limited only to above-described aperture, also can be used for the processing in the first hole in other apertures.
The first hole of preparation is carried out just strand, check, cold extrusion, check, smart strand and feeler gauge check again.
The present invention cooperates different bore, cut with scissors instrument specification and number of times combinations by different-diameter is imposed, and the first hole of preparation meets the demands with the feeler gauge inspection, has guaranteed follow-up slotted liner bushing cold extrusion operation needs.
Preferably, the method according to this invention, at the processing of nominal diameter " between four kinds of apertures (3/8 ", 7/16 ", 9/16 ", 3/4 ") 3/8～3/4, the brill reaming number of times in first hole is 3～10 times.For making things convenient for the workman to operate, designed a rational drilling flow process of cover and a step, 3 boring is divided in less hole, bigger hole branch expands more frequently and cuts with scissors, as to prepare nominal diameter be 3/4, and " (19.05mm) hole of time; thickness reaches the multilayer material of 52mm needs to bore for 10 times reaming+4 time hinge (staggered combination)+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge and checks the program process of such complexity.
The slotted liner bushing to the different-diameter specification that the present invention sets up prepares the process in hole just, by being imposed, different-diameter cooperates different bore, cut with scissors instrument specification and number of times combinations, the first hole of preparation meets the demands with the feeler gauge inspection, guaranteed follow-up slotted liner bushing cold extrusion operation needs, and perforate accuracy rate height and high efficiency.
Description of drawings
Fig. 1 is that slotted liner bushing cold extrusion of the present invention prepares the flow chart in hole.
Fig. 2 is the diagram schematic diagram that a kind of slotted liner bushing cold extrusion according to the present invention prepares the flow process in hole, wherein 21-bores hole (first hole drill) just, the 22-hinge is hole (first hole reamer) just, the diameter of 23-inspection opening (built-up gauge), 24-checks plug (plug gauge), 25-is to hole cold extrusion (plug, lining and nose top cap) (comprise 25A, 25B, 25C, 25D and 25E), 25A-is contained in lining on the plug, 25B-injects hole just with plug and lining, 25C-is pressed on nose top cap on the workpiece, the 25D-use is drawn rifle that cold extrusion 25E-is carried out in the hole and is removed and throw away lining, 26-checks the diameter (feeler gauge) in cold extrusion hole, 27-finish reams hole and check cold extrusion, and (have the bottoming reamer of coming year sense rule function, 28-installs securing member.
Fig. 3 is prepared according to the methods of the invention hole just, and it is opened lining cold-stamped schematic diagram, wherein, the trumpet type slotted liner bushing of 1-through lubricating, the 2-plug, the 3-workpiece, 4-nose top cap assembly, 5-draws rifle.
The specific embodiment
Below in conjunction with accompanying drawing characteristics of the present invention are carried out comparatively detailed explanation.
Slotted liner bushing cold extrusion process of the present invention is seen Fig. 1.
As shown in Figure 1, in the slotted liner bushing cold-extrusion technology, comprising: repeatedly bore hole just; Hinge is the hole just; The diameter of inspection opening; Check plug; Cold extrusion is carried out in the hole, wherein, cold extrusion is carried out in the hole comprised successively again: lining is contained on the plug, plug and lining are injected hole just, nose top cap is pressed on the workpiece, use and draw rifle that cold extrusion is carried out in the hole, remove and throw away lining; Check the diameter in cold extrusion hole; Finish ream the hole; Check whole bore dia.And then in the connecting hole that processes, securing member is installed.
Be that slotted liner bushing cold-stamped schematic diagram is carried out in the first hole that processes according to method of the present invention as shown in Figure 3, wherein, 1 expression is through lubricated trumpet type slotted liner bushing, and 2 represent plugs, and 3 represent workpiece, 4 expression nose top cap assemblies, and rifle is drawn in 5 expressions.Specifically slotted liner bushing cold-stamped process is, lining 1 is contained on the plug 2, again plug 2 and lining 1 is injected hole just, and nose top cap 4 is pressed on the workpiece 3, uses and draws rifle 5, and cold extrusion is carried out in the hole, removes and throw away lining 1.
Fig. 2 is the diagram according to a slotted liner bushing cold extrusion process of the present invention.Wherein repeatedly bore hole 21 just with first hole drill, cut with scissors hole 22 just with first hole reamer, carry out the diameter 23 of inspection opening with built-up gauge, check plug 24 with the plug gauge, pass through plug, lining and nose top cap are to hole cold extrusion 25, the cold extrusion in hole comprises again lining is contained in 25A on the plug, plug and lining are injected hole 25B just, nose top cap is pressed on 25C on the workpiece, use draws rifle that cold extrusion 25D is carried out in the hole, removes and throw away lining 25E, checks the diameter 26 in cold extrusion hole with feeler gauge, the bottoming reamer that use has the gauge function finish reams hole and check cold extrusion 27, the last securing member 28 of installing in the hole that processes.
The key that whole cold-extrusion technology is finished depends on three critical sizes: first bore dia, and the big footpath of plug, the thickness of lining, back two instrument and standard components that provided by supplier guarantee, are the keys of whole technical process and prepare qualified first Kong Ze.
Because it is limited to implement the wing body docking area domain space that cold extrusion strengthens, can only hand-made hole, reason is that multilayer material combination back drilling must be at erecting yard.The securing member pre-manufactured hole will pass through the material of 4～5 layers of different-thickness, maximum ga(u)ge 52mm, maximum gauge 19.05mm, the hand-made hole difficulty is very big, make the whole hole after the slotted liner bushing cold extrusion satisfy technological requirement, key is to prepare qualified first hole earlier, and is improper if drilling instrument and operation are selected, and then might cause and scrap.
Because lack automatically processing devices such as auto-feed brill, in order to guarantee the drilling quality, must drilling flow process and operation reasonable in design, comprise the reasonable combination of different drilling tools of all size and reamer, and technology is cured.
For making things convenient for the workman to operate, the material that adopts on the simulated aircraft, thickness combination, select instruments such as suitable boring, fraising, gauge, smart strand, pass through engineer testing, designed a rational drilling flow table of cover and a step, divide 3 boring as less hole, bigger hole branch expands more frequently and cuts with scissors, " (19.05mm); thickness reaches the multilayer material of 52mm, need to bore for 10 times reaming+4 time hinge (staggered combination)+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge and check the program process of such complexity and prepare 3/4.
Particularly, during as securing member nominal diameter " (first hole 0.3590 "～0.3620 ") that be 6/16, in system just in the process of hole; bore reaming altogether 3 times; wherein, initial twice boring hole enlargement amount is controlled at each 0.055 "～0.065 ", and last boring hole enlargement amount is controlled at 0.010 "～0.032 "; During as securing member nominal diameter " (first hole 0.4210 "～0.4240 ") that be 7/16, just in the process of hole, bore reaming altogether 4 times in system, the boring hole enlargement amount of the junior three time is each 0.055 "～0.065 ", and last boring hole enlargement amount is controlled at 0.010 "～0.032 "; For another example during securing member nominal diameter " (first hole 0.5370 "～0.5400 ") that be 9/16; just in the process of hole, bore reaming altogether 6 times, wherein; initial 3 times boring hole enlargement amount is controlled at each 0.055 "～0.065 " in system, last twice boring hole enlargement amount is controlled at each 0.010～0.032 "; And for example during securing member nominal diameter " (first hole 0.7180 "～0.7210 ") that be 12/16; just in the process of hole, bore reaming 10 times in system, wherein; initial 3 times boring hole enlargement amount is controlled at each 0.055 "～0.065 ", last three times boring hole enlargement amount is controlled at each 0.010 "～0.032 ".
Preferably, according to the diameter in first hole, determine the big footpath of plug.During as securing member nominal diameter " (first hole 0.3590 "～0.3620 ") that be 6/16, the big footpath of plug is 0.3530 "～0.3540 "; During as securing member nominal diameter " (first hole 0.4210 "～0.4240 ") that be 7/16, the big footpath of plug is 0.4070 "～0.4180 "; During securing member nominal diameter " (first hole 0.5370 "～0.5400 ") that be 9/16, the big footpath of plug is 0.5330 "～0.5340 " for another example; Securing member nominal diameter " (first hole 0.7180 "～0.7210 ") that be 12/16 and for example, the big footpath of plug is 0.7148 "～0.7165 ".
Preferably, according to the diameter in first hole, determine the thickness of lining.As securing member nominal diameter " (first hole 0.3590 "～0.3620 ") that be 6/16, lining thickness is 0.0100 "; As securing member nominal diameter " (first hole 0.4210 "～0.4240 ") that be 7/16, lining thickness is 0.0100 "; Securing member nominal diameter " (first hole 0.5370 "～0.5400 ") that be 9/16 for another example, lining thickness is 0.0120 "; Securing member nominal diameter " (first hole 0.7180 "～0.7210 ") that be 12/16 and for example, lining thickness is 0.0150 ".
This technology key is to select the proper tools numbering, and is extremely important to technology validity as STDN (numbering STDN, FTI company instrument numbering).In case determine suitable STDN, also determine all required related tools of cold extrusion easily.
Below describe by specific embodiment.
A kind of secondary-line-aircraft wing docking area slotted liner bushing cold extrusion tools selection:
(1) hydraulic pump FT-200 (2662-001 ASSEMBLY, FT-200B PAUMP)
(2) draw rifle LB-25 (2305-004 Assy, LB Puller)
Annotate: be used for the securing member nominal diameter and draw rifle smaller or equal to the slotted liner bushing cold-stamped in 9/16 inch hole.
(3) draw rifle MB-30 (2426-001 Assy, MB Puller)
Annotate: be used for the slotted liner bushing cold-stamped that the securing member nominal diameter equals 3/4 inch hole and draw rifle.
Be to the main flow process in the slotted liner bushing cold-extrusion technology of the first bore dia correspondence of difference shown in the table 1.
Table 1 pair difference is the slotted liner bushing cold-extrusion technology of bore dia correspondence just
| The standard component trade mark | Nominal diameter, in | Whole bore dia, in | First bore dia, in | |
| HST12AP12 | ||||
| 3/8 | 0.3700～ 0.372 | 0.3590～ 0.3620 | No. 3 brills reaming+hinge → check just → cold extrusion → check → finish ream → feeler gauge check | |
| HST12AP14 | 7/16 | 034325～ 0.4345 | 0.4210～ 0.4240 | No. 4 brills reaming+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge check |
| NAS6809A | 9/16 | 0.5570～ 0.56 | 0.5370～ 0.5400 | No. 6 brill reaming+2 time hinge+hinge → feeler gauge check → cold extrusions just → check → finish ream → the feeler |
| NAS6812 | ||||
| 3/4 | 0.7495～ 0.7505 | 0.7180～ 0.7210 | No. 10 brill reaming+4 time hinges (staggered combination)+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge is checked |
Wherein, HST12AP12, HST12AP14, NAS6809A and NAS6812 are the models of the slotted liner bushing of FIT company production.
Wherein, nominal diameter is the external diameter of standard component or securing member.
The high cold extrusion requirement unit that interferes in table 2 aluminium alloy and the mild steel cold-extrusion technology: inch
Annotate:
(1) tolerance+is 0.0005 inch.
(2) manufacturing tolerance ± 0.0002 inch.
(3) minimum diameter of Yun Xuing, plug gauge diameter+0.0002/-0.0001 inch.
(4) inspection before lubricant uses, tolerance is+the 0.0004/-0.0002 inch.
(5)
Hole gauge at the beginning of A represents " by " diameter; Tolerance is+the 0.0000/-0.0002 inch.
B represents that just the hole gauge " does not pass through " diameter; Tolerance is+the 0.0002/-0.0000 inch.
C represents that cold extrusion checking diameter is applicable to bottoming reamer guide rod (tolerance is+the 0.0000/-0.0005 inch), is positioned over tram (tolerance is+the 0.0002/-0.0000 inch) with the cold extrusion purchase inspection gauge.
The drilling of Que Dinging at last, fraising, smart strand, measurement, slotted liner bushing cold-stamped flow process see Table 3.
In the table 3, nominal diameter is meant the external diameter of standard component.Whole bore dia is meant the final aperture that the slotted liner bushing cold extrusion is later, and first bore dia is meant the last aperture before the slotted liner bushing cold extrusion.
According to test situation, first hole eventually before the cold extrusion of to the last determining from initial locating hole, for testing employed 7050-T7451 aluminum alloy materials, preceding 2～5 each boring hole enlargement amounts generally are controlled at 0.055～0.065 " about, last 1～3 each boring hole enlargement amount generally is controlled at 0.010～0.032 " about.
In the table 3, embodiment 1 is a preparation normative reference part 3/8, and " hole (9.52mm), thickness reaches the multilayer material of 36.3mm, needs to bore for 3 times reaming+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge and checks.Its standard component trade mark is HST12AP12.
Embodiment 2 is preparation normative reference parts 7/16, and " hole (11.1mm), thickness reaches the multilayer material of 42.3mm, needs to bore for 4 times reaming+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge and checks.Its standard component trade mark is HST12AP14.
Embodiment 4 is preparations 3/4, and " (19.05mm) hole, thickness reach the multilayer material of 52mm, need to bore for 10 times reaming+4 time hinge (staggered combination)+hinge → feeler gauge check → cold extrusion just → check → finish ream → feeler gauge and check.Its standard component trade mark is NAS6812.
In the table 3,012,017,019,005,006,007,008 etc. is that commercially available international English system is bored expansion instrument number, and as in 012 (0.2490 * 0.1900) first digit be big area of bed, second digit is little area of bed.
In the table 3, the model that " CBSR " or " CBR " takes the lead is represented the STDN series standard reamer instrument of FTI company as " CBSR-12-O-N-1 ", " CBR-12-O-N-1-0.3700 " etc.
Adopt the above chambering process scheme of boring, have several advantages:
(a) adopt flow process drilling in the table, made things convenient for workman's operation, step and flow process are reasonable, saved the non-cutting time that the workman joins cutter voluntarily and spent, improve work efficiency, the workman only needs can satisfy the drilling requirement according to No.1 the operation according to the order of sequence with the reamer specification of listed brill in the table, has avoided obtaining operator's favorable comment because of the people takes the probability that cutter causes quality problems by mistake.
(b) adopt technological process operation in the table, can satisfy the manual preparation quality requirement in hole just, improved production efficiency.
(c) technological process is reasonable, has guaranteed follow-up cold extrusion and finish reamed operation to carry out smoothly, and this flow process and step have guaranteed slotted liner bushing cold extrusion process good for delivery in five parts development batch stages of ARJ21 series secondary-line-aircraft.
ZPS03670-08000 is replenished and improved to the parameter that engineer testing obtains.
This process and result of the test prove, can satisfy the requirement of technological specification, for company's slotted liner bushing cold extrusion manufacturing process provides the technological parameter of satisfying the demand.
More than by specific embodiment method of the present invention is had been described in detail; but be not limited only to these embodiment; without departing from the inventive concept of the premise; more other variations or improved embodiment can also be arranged, and these changes and improvements all should belong to the claimed scope of claim.
Claims (17)
1. the method for a slotted liner bushing cold extrusion machining hole comprises: bore hole just, the first hole of hinge, cold extrusion is carried out in the hole, finish reamed the hole, and check whole bore dia, it is characterized in that, finish brill hole just through repeatedly boring reaming, and the each boring of control hole enlargement amount is no more than 0.065 ".
2. the method for slotted liner bushing cold extrusion machining hole as claimed in claim 1 is characterized in that, bores the reaming number of times and is at least three times.
3. the method for slotted liner bushing cold extrusion machining hole as claimed in claim 1 or 2 is characterized in that, the boring hole enlargement amount of initial 1 time, twice or 3 times is controlled at each 0.055 "～0.065 "; The boring hole enlargement amount of last 1 time, twice or 3 times is controlled at each 0.010 "～0.032 ".
4. as the method for the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～3, it is characterized in that the boring hole enlargement amount between initial 1 time, twice or 3 times and last 1 time, twice or 3 times is controlled at each 0.032 "～0.055 ".
5. as the method for the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～4, it is characterized in that, nominal diameter is 3/8 " time; carry out boring for three times reaming altogether and finish brill hole just; wherein; initial twice boring hole enlargement amount is controlled at each 0.055 "～0.065 ", last boring hole enlargement amount is controlled at 0.010 "～0.032 "; Or
Nominal diameter is 7/16 " time, for first hole, carry out boring for four times reaming altogether and finish and bore hole just, wherein, the boring hole enlargement amount of the junior three time is controlled at each 0.055 "～0.065 ", and last boring hole enlargement amount is controlled at 0.010 "～0.032 "; Or
Nominal diameter is 9/16 " time, carry out boring for six times reaming altogether and finish and bore hole just, wherein, the boring hole enlargement amount of the junior three time is controlled at each 0.055 "～0.065 ", and last twice each boring hole enlargement amount is controlled at 0.010 "～0.032 "; Or
Nominal diameter is 12/16 " time, carry out boring for ten times reaming altogether and finish and bore hole just, wherein, the boring hole enlargement amount of the junior three time is controlled at each 0.055 "～0.065 ", and last three times boring hole enlargement amount is controlled at each 0.010 "～0.032 ".
6. as the method for the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～5, it is characterized in that hinge just also comprises the diameter of inspection opening and check plug behind the hole, cold extrusion is carried out in the hole after, also comprise the diameter of checking the cold extrusion hole.
7. as the method for the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～6, it is characterized in that described slotted liner bushing cold extrusion comprises:
Lining is contained on the plug;
Plug and lining are injected hole just;
Nose top cap is pressed on the workpiece;
Use draws rifle that cold extrusion is carried out in the hole;
Shift out lining.
8. as the method for the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～7, it is characterized in that,, also comprise fraising when the number of times that bores reaming during more than four times.
9. the method for slotted liner bushing cold extrusion machining hole as claimed in claim 8 is characterized in that, after brill reaming four times, bores reaming and fraising and hockets.
10. the method for slotted liner bushing cold extrusion machining hole as claimed in claim 8 or 9 is characterized in that, the amount of each fraising is 0.010～0.032 ".
11. the method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～10 is characterized in that, bores in the first hole, bit diameter is 0.1935 first ".
12. method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～11, it is characterized in that, when nominal diameter is 3/8 inch, the boring flow process comprises: first brill 0.1935 "; brill diffuses into 0.2490 for the first time ", bore for the second time and diffuse into 0.3120 ", expand Shen to 0.3437 for the third time ", and finish ream 0.3700 ".
13. method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～11, it is characterized in that, when nominal diameter is 7/16 inch, the boring flow process comprises: head brill 0.1935 "; brill diffuses into 0.2490 for the first time ", brill diffuses into 0.3120 for the second time ", brill diffuses into 0.3740 for the third time ", expand Shen to 0.4062 the 4th time ", finish ream 0.4325 ".
14. the method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～11 is characterized in that, when nominal diameter is 9/16 inch, the boring flow process comprises: head brill 0.1935 "; brill diffuses into 0.2490 for the first time ", brill diffuses into 0.3120 for the second time ", brill diffuses into 0.3740 for the third time ", No. the 4th time brill diffuses into 0.4219 "; cut with scissors 0.4370 for the first time ", No. the 5th time brill diffuses into 0.4688 ", cut with scissors 0.4995 for the second time ", expand Shen to 0.5156 the 6th time ", and finish ream 0.5570 ".
15. method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 1～11, it is characterized in that, when nominal diameter is 3/4 inch, the flow process of holing is comprising: first brill 0.1935 "; brill diffuses into 0.2490 for the first time ", bore for the second time and diffuse into 0.3120 "; brill diffuses into 0.3740 for the third time ", No. the 4th time brill diffuses into 0.4219 ", cut with scissors 0.4370 for the first time ", No. the 5th time brill diffuses into 0.4688 "; cut with scissors 0.4995 for the second time ", No. the 6th time brill diffuses into 0.5312 ", cut with scissors 0.5620 for the third time ", No. the 7th time brill diffuses into 0.5938 "; cut with scissors 0.6245 for the third time ", the 8th expansion Shen to 0.6445 ", the 9th expansion Shen to 0.6645 ", expand Shen to 0.6875 the tenth time ", and finish ream 0.7495 ".
16. the method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 12～15 is characterized in that, also comprises hinge just before finish reaming, check and cold extrusion.
17. the method as the arbitrary described slotted liner bushing cold extrusion machining hole of claim 12～16 is characterized in that, also comprises the feeler gauge check after finish reaming.
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| CN2010101374117A CN102205488A (en) | 2010-03-31 | 2010-03-31 | Method for processing hole in split-sleeve cold extrusion manner |
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| CN2010101374117A CN102205488A (en) | 2010-03-31 | 2010-03-31 | Method for processing hole in split-sleeve cold extrusion manner |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103212900A (en) * | 2012-01-19 | 2013-07-24 | 昆山思拓机器有限公司 | Integral type bushing structure applicable to bracket cutting equipment and machining process of integral type bushing structure |
| CN103302120A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Cold extrusion strengthening treatment process for butt joint holes of single-bug and double-bug joints |
| CN103952651A (en) * | 2014-05-13 | 2014-07-30 | 中国航空工业集团公司北京航空制造工程研究所 | Combined strengthening method of alloy structural hole |
| CN104368617A (en) * | 2014-11-06 | 2015-02-25 | 邯郸新兴特种管材有限公司 | Crossed pore expanding method |
| CN105666036A (en) * | 2014-11-17 | 2016-06-15 | 昌河飞机工业（集团）有限责任公司 | Assembly method capable of achieving hole and bush extrusion strengthening twice |
| CN105855791A (en) * | 2015-01-19 | 2016-08-17 | 中国科学院沈阳自动化研究所 | Friction extrusion strengthening method of structural member connecting hole |
| CN105855790A (en) * | 2015-01-19 | 2016-08-17 | 中国科学院沈阳自动化研究所 | Tool and method for strengthening friction extrusion of structural member connecting hole |
| CN106584357A (en) * | 2016-12-14 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Double-acting hydraulic expander |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0131648A2 (en) * | 1983-07-11 | 1985-01-23 | Fatigue Technology, Inc. | Method of cold expanding and sizing fastener holes |
| US5127254A (en) * | 1991-07-10 | 1992-07-07 | Fatigue Technology, Inc. | Method and apparatus for split sleeve cold expansion of openings in structural members |
| CN1843690A (en) * | 2006-04-17 | 2006-10-11 | 江苏华阳金属管件有限公司 | Method for forming pipe fittings by cold extrusion |
| EP1803526A1 (en) * | 2005-12-28 | 2007-07-04 | Fatigue Technology, Inc. | Mandrel assembly and method of using the same |
| CN101648227A (en) * | 2009-08-27 | 2010-02-17 | 浙江拓进五金工具有限公司 | Multi-station cold extrusion molding method for sleeve |
-
2010
- 2010-03-31 CN CN2010101374117A patent/CN102205488A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0131648A2 (en) * | 1983-07-11 | 1985-01-23 | Fatigue Technology, Inc. | Method of cold expanding and sizing fastener holes |
| US5127254A (en) * | 1991-07-10 | 1992-07-07 | Fatigue Technology, Inc. | Method and apparatus for split sleeve cold expansion of openings in structural members |
| EP1803526A1 (en) * | 2005-12-28 | 2007-07-04 | Fatigue Technology, Inc. | Mandrel assembly and method of using the same |
| CN1843690A (en) * | 2006-04-17 | 2006-10-11 | 江苏华阳金属管件有限公司 | Method for forming pipe fittings by cold extrusion |
| CN101648227A (en) * | 2009-08-27 | 2010-02-17 | 浙江拓进五金工具有限公司 | Multi-station cold extrusion molding method for sleeve |
Non-Patent Citations (3)
| Title |
|---|
| 刘华东: "紧固件孔衬套冷挤压强化技术", 《航空工程与维修》 * |
| 张建超: "开缝衬套挤压技术在飞机维修中的应用", 《民用飞机设计与研究》 * |
| 陈明等: "带切缝衬套冷挤压强化工艺研究", 《新技术新工艺》 * |
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