CN100513064C - Numerically controlled processing method for plane wing rib beam part - Google Patents
Numerically controlled processing method for plane wing rib beam part Download PDFInfo
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- CN100513064C CN100513064C CNB2007101454073A CN200710145407A CN100513064C CN 100513064 C CN100513064 C CN 100513064C CN B2007101454073 A CNB2007101454073 A CN B2007101454073A CN 200710145407 A CN200710145407 A CN 200710145407A CN 100513064 C CN100513064 C CN 100513064C
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Abstract
The invention discloses a digital control processing method for a rib boom part of the aircraft wing, comprising a rough lumber profile with processing margin and a positioning clamp. The rough lumber profile is a multi-surface structure which is provided with a long-striped web plate and a rim plate, and the web plate and the rim plate are drawn bent and molded and form a certain angle. The positioning clamp is provided with a supporting plane and a positioning pin. The particular processing method is that a stress releasing gap is arranged on the web plate, and processing positioning reference is firstly set up before the extensive processing and intensive processing.
Description
Technical field
The present invention relates to airborne vehicle manufacturing technology field, particularly about the efficient numerically controlled processing method of aircraft wing costal margin bar.
Background technology
The costal margin bar is that the typical case in the aircaft configuration connects stressed part, the ubiquity difficulty of processing is big, the required precision height, the costal margin bar part primary structure characteristics that the present invention relates to are by web and the strip structure formed with the listrium that web forms an angle, the woolen cloth of costal margin bar part adopts stretch wrap forming, section bar cross section less, and the design feature of length overlength, length-width ratio is about 10 times.Such part ubiquity complex structure is processed the characteristics yielding, that the clamping difficulty is big.
Summary of the invention
The objective of the invention is to disclose a kind of numerical-control processing method of aircraft wing costal margin bar part.
The numerical-control processing method of aircraft wing edge strip part, include the woollen section bar and the positioning fixture of allowance, woollen section bar is a multi-plane structure with strip bending forming of web and listrium, and web and listrium are angled, and positioning fixture has supporting plane and alignment pin; Special processing method is at first the web of woollen section bar to be supported on the supporting surface of positioning fixture, on web, process location benchmark and stress release breach respectively, carry out roughing then, 70-80% allowance is removed in roughing, revise the location benchmark after the roughing again, remove the fine finishining that all the other allowance are finished part at last.
The above-mentioned stress release breach edge that is distributed in web at interval, there is the surplus that is not less than 4mm in the final part sideline of notch depth distance.
Above-mentioned location benchmark comprises location datum level, location datum hole, location true edge
Above-mentioned roughing is successively removed allowance by contour, except the web outside profile, and outside the intersection of web and listrium, all only stays the allowance for finish of 3mm-4mm.
The outside in listrium top, the listrium, web, local remaining, web edge profile order processing are pressed in above-mentioned fine finishining.
By the inventor actual production in check, the beneficial effect of the numerical-control processing method of aircraft wing costal margin bar part of the present invention is that the part processing distortion is effectively controlled, the processing and loading clamp location is reliable, process is stable, efficiently, all sizes are qualified after testing, and surface quality of workpieces meets design requirement.
Below in conjunction with the embodiment accompanying drawing this application is further described:
Fig. 1 is edge strip design of part signal on certain aircraft 1 rib
Fig. 2 is the woollen signal of the section bar before Fig. 1 part processing
Fig. 3 is the processing process signal
Fig. 4 is the clamping signal before the part processing
Fig. 5 is the location benchmark signal of processing
Fig. 6 is the stress release breach signal of processing
Fig. 7 is the manufacturing procedure signal
Number description: 1 design of part, 2 section bar woolen cloths, 3 positioning fixtures, 4 webs, 5 listriums, 6 datum levels, 7 true edges, 8 datum holes, 9 stress release breach, 10 part edge lines, 11 roughing surpluses, 12 allowances for finish
Specific embodiment
Edge strip part contour dimension is 2300 * 230 * 220mm on the aircraft shown in Figure 1, the primary structure characteristics are that the web above and below is notched pair of listrium structure, and maximum is closed angle angle 22.6 degree, listrium height 72-95mm, web thickness 5-8mm, listrium thickness 5-8mm.Part processing precision requires: web tolerance+0.2, listrium tolerance+0.2, contour tolerance+0.05/-0.30, flatness total length 0.8, listrium spacing tolerance+0.5/-0.1, machine add surperficial Ra3.2.
The section bar woolen cloth 2 of manuscript 1 is a kind of stretch wrap forming section bar as shown in Figure 2, and the cross section of section bar is a kind of diesis structure.Process equipment adopts five-coordinate numerally controlled machine tool, according to the specific product architectural feature, satisfies rotating speed, stroke, pivot angle scope, spindle power, requirements such as control system.
Work flow as shown in Figure 3, the section bar woolen cloth is to design a model, general minimum 6mm allowance (the 3mm cementation zone wherein that guarantees, the 3mm process allowance), the inspection of stretch wrap forming section bar woolen cloth comprises that can section bar sectional dimension, stretch wrap forming crooked radian (checking with exterior template), section bar deformation extent (checking) etc. satisfy the following process requirement on platform.
Manufacturing procedure as shown in Figure 7, this figure has showed with section bar woolen cloth 2 and to have removed roughing surplus 11 by milling datum level 6 that allowance for finish 12 backs form the cross sections signal of parts 1.
The woollen clamping of section bar adopts the method for web plane and side location, and wherein side be the location, and purpose is control inspection flexural deformation, compresses a little on the web face, and play pressing plate position when processing web is at last reduced clamping to greatest extent and changed the error that causes.
Because frock One's name is legion, any one deviations will cause part inharmonious, for this reason, we position the datum level inspection in advance on lathe, and the auxiliary examination hole is set on the part web, after first side processes, process check verification holes position before second side, thereby whether gauging fixture is coordinated.
Because characteristics such as complicated wing costal margin bar listrium height, angle are big, complex structures, to the following requirement of having selected for use of cutter: the amount of overhanging more greatly, good rigidly cuts sharp; The cutter wearability is good, satisfies high-speed cutting; Good economy performance.Therefore tool selection clip type (or claiming indexable formula) cutter is main.
Before roughing, at first want correct foundation location benchmark, on the process allowance of the web 4 of section bar woolen cloth, at first process datum hole 8, with datum hole 8 is that initial point is set up machining coordinate system, and process the true edge 7 parallel with Y-axis respectively with X-axis, upper and lower surface with web 4 is processed as datum level 6 simultaneously, to eliminate woollen foozle.
In order fully to discharge stress, the machining deformation of control part, do not influence simultaneously the clamping and the location of web 6, we make some stress release breach 9 before the roughing at the edge of web, the about 40mm of the width of stress release breach 9, the final part sideline 10 of length direction distance is the 4mm surplus at least, and as shown in Figure 5, stress release breach 9 is distributed in the both sides of part web 4.Like this, flexural deformation will discharge after roughing, and through fine finishining, this part distortion is compensated or eliminates.
Roughing stage main purpose is high efficiency removal surplus, discharges distortion to greatest extent.After the roughing,, and close outside the angular position, all only stay the 3-4mm allowance for finish except the web outside profile.
The contour process technology is adopted in roughing among the embodiment, contour processing is promptly removed material according to Z to contour pattern of successively successively decreasing, keep same Z to height at each layer cutter, remove all material, and according to etc. the surplus cutting mode cut, according to angle incision pattern, illustrate between layer and the layer referring to the contour layering processing that the roughing surplus 11 among Fig. 6 is showed.
The advantage of contour processing: the removal of material is to carry out according to the mode of homogenising, and the stress of material can be discharged fully, reduces final distortion; The chipping allowance relative equilibrium, working angles is more steady, and is less to the impact of cutter, lathe; For relatively weaker structure, reduce vibrations as high listrium processing.
After roughing is finished, material stress is fully discharged, and if part generation maximum distortion is according to original benchmark positioning and clamping, do not have the purpose that reduces to be out of shape, therefore, before fine finishining, part keeps the nature clamping, the gap of part web face and positioning fixture (milling tool) locating surface uses aluminium foil to level up, datum level, true edge are revised again, eliminated the fiducial error that the roughing distortion causes, thereby offset distortion by allowance.
The fine finishining stage mainly is to satisfy dimensional accuracy and surface quality requirement, controls residually, and some special structure divisions that are difficult to guarantee are taked technical measures, guarantees working (machining) efficiency.The fine finishining processing sequence is listrium top, listrium inboard (theoretical profile), the listrium outside (guaranteeing the listrium wall thickness), listrium machines back reprocessing web and other local remaining position, after one side machines the part turn-over is processed second side by same order, process web edge profile (unloading clout) at last.
After fine finishining is finished, can carry out refine to the machined burrs of part by pincers worker, the measurement of testing at last.
The breach of listrium 5 is special positions, and two listrium spacings are critical size.Main processing difficulties is a little less than this structural rigidity, easy cutter relieving, the cutter that quivers, and physical dimension and surface roughness be cannot say for sure to demonstrate,prove.
Take in the roughing stage for the gap portions Processing Strategies of listrium 5, increase allowance, and study in France, to increase the rigidity of privileged sites when the fine finishining by staged.The one-sided surplus 4-5.5mm of roughing; In the fine finishining stage, breach listrium profile processing in advance puts in place.
Because these positions are when fine finishining, the easier cutter that quivers that causes, therefore,, when rigidity strong processing big in surplus can not cause vibration, guarantee the physical dimension and the surface roughness of part easily.
By this project implementation, the part processing distortion is effectively controlled, and the processing and loading clamp location is reliable, and process is stable, and is efficient.All sizes are qualified after testing, and surface quality of workpieces meets design requirement.
Claims (3)
1, the numerical-control processing method of aircraft wing edge strip part, include the woollen section bar and the positioning fixture of allowance, woollen section bar is the stretch wrap forming section bar that a cross section with web and listrium is the diesis structure, positioning fixture has supporting plane and alignment pin, special processing method is at first the web of woollen section bar to be supported on the supporting plane of positioning fixture, on web, process location datum level, true edge, datum hole respectively, and make some stress release breach at the edge of web; Next carries out roughing, and roughing adopts the contour process technology evenly to remove 70-80% allowance; Revise the location benchmark after the roughing again, part keeps the nature clamping, and datum level, true edge are revised again, eliminates the fiducial error that the roughing distortion causes; Carry out fine finishining at last, fine finishining is processed by the outside-web in listrium top-listrium-local remnants-web edge profile order.
2, the numerical-control processing method of aircraft wing edge strip part according to claim 1 is characterized in that the described stress release breach both sides of the edge that are distributed in web at interval.
3, the numerical-control processing method of aircraft wing edge strip part according to claim 1, it is characterized in that described roughing successively removes allowance by contour, except the web outside profile, and outside the intersection of web and listrium, all only stay the allowance for finish of 3mm-4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101454073A CN100513064C (en) | 2007-09-11 | 2007-09-11 | Numerically controlled processing method for plane wing rib beam part |
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| Application Number | Priority Date | Filing Date | Title |
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| CNB2007101454073A CN100513064C (en) | 2007-09-11 | 2007-09-11 | Numerically controlled processing method for plane wing rib beam part |
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| CN101104242A CN101104242A (en) | 2008-01-16 |
| CN100513064C true CN100513064C (en) | 2009-07-15 |
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Owner name: XI AN AIRCRAFT INTERNATIONAL CORPORATION Free format text: FORMER OWNER: XI AN AIRCRAFT INDUSTRY (GROUP) COMPANY LIMITED Effective date: 20121113 |
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Effective date of registration: 20121113 Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: Xi'an aircraft, international aviation manufacturing, Limited by Share Ltd, Xi'an aircraft branch Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: Xi'an Aircraft Industry Group Co., Ltd. |