CN104015015A - Numerical control integrated manufacturing technology for parts of outer barrel of main landing gear of airplane - Google Patents

Numerical control integrated manufacturing technology for parts of outer barrel of main landing gear of airplane Download PDF

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Publication number
CN104015015A
CN104015015A CN201410283469.0A CN201410283469A CN104015015A CN 104015015 A CN104015015 A CN 104015015A CN 201410283469 A CN201410283469 A CN 201410283469A CN 104015015 A CN104015015 A CN 104015015A
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CN
China
Prior art keywords
urceolus
undercarriage
numerical control
allowance
benchmark
Prior art date
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CN201410283469.0A
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Chinese (zh)
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CN104015015B (en
Inventor
刘波
罗敏锐
Original Assignee
什邡市明日宇航工业股份有限公司
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Priority to CN201410283469.0A priority Critical patent/CN104015015B/en
Publication of CN104015015A publication Critical patent/CN104015015A/en
Application granted granted Critical
Publication of CN104015015B publication Critical patent/CN104015015B/en

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P2700/00Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/01Aircraft parts
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/02Undercarriages

Abstract

The invention relates to the field of processing of landing gears of airplanes and in particular relates to a numerical control integrated manufacturing technology for parts of an outer barrel of a main landing gear of an airplane. During rough machining, a technological head is reserved on a landing gear, a center hole is drilled in the technological head, a reference excircle is processed at the bottom and the middle part of the outer barrel of the landing gear, new technological datum is applied, a new clamping method is adopted when the landing gear is clamped during processing, efficiency is improved, and quality is stable; and during finish machining, a clamping direction is turned, and a 90-degree power converter is applied, so that an inner hole of the outer barrel of the landing gear can be processed by adopting a general machine tool even the landing gear is horizontal. The invention aims at providing an economic numerical control landing gear integrated manufacturing technology with high efficiency and stable quality.

Description

Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques
technical field
The present invention relates to the manufacture field of undercarriage, particularly Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques.
Background technology
Undercarriage is the vitals that profoundly affects overall aircraft safety in airplane component, it is the vital part that ensures aircraft aircraft and personal security sliding, during take-off and landing, undercarriage bears huge impact and repeat load in take-off and landing process, owing to being subject to the impact of alternate stress and large impact power, quality requirement is high, the quality of its quality has just determined quality, safety and the reliability of aircraft, and its production cycle has also determined the delivery cycle of aircraft;
In prior art, for large-scale manufacturer, that a large-scale special processing equipment of buying is processed it, but very expensive, for little manufacturer, that impotentia is bought, so little general machine tooling for production commercial city, but existing method operation circulation number of times, clamping workpiece number of times are more, use frock also more, not only efficiency is low, and quality is unstable.
Summary of the invention
The object of the invention is to overcome existing above-mentioned deficiency in prior art, a kind of economy, high, the stay-in-grade undercarriage numerical control of efficiency Integrated-manufacturing Techniques are provided.
In order to realize foregoing invention object, the invention provides following technical scheme:
A kind of Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques, it comprises:
Step 1, enter the roughing stage, tentatively determine blank shape by scribing by bench worker, then with milling machine to the layout line border to the profile processing that strips off the skin, by the monolateral allowance of maximal projection size, the benchmark cylindrical of general car finish turning undercarriage, this benchmark cylindrical is set as two, a middle part at undercarriage urceolus, a bottom at urceolus, start the thick endoporus that bores urceolus from urceolus bottom, at urceolus top, reserved technique head, drills centre bore thereon;
Step 2, enter the semifinishing stage, undercarriage is clamped on four axle lathes, ensure that lathe Maximum turning radius is greater than the radius of gyration of undercarriage taking urceolus center line as axle, with the benchmark cylindrical of chuck clamping urceolus bottom, withstand the centre bore at the urceolus top processing in described step 1 with tailstock, clamp and support the benchmark cylindrical at urceolus middle part with a bracing frame;
Step 3 is turned over undercarriage each processing profile to dead size on lathe, rough mills fork ear made allowance, and heavy boring is respectively pitched the monolateral made allowance of ear, machine tool tapping, and undercarriage proceeds to quenching heat treatment;
Step 4, enter the fine finishining stage, clamping undercarriage, by lathe correction benchmark, polishing two place's benchmark cylindricals, ensure during this time its axiality, recasting centre bore D, must ensure the axiality of the benchmark cylindrical section of this hole associated in manufacturing process, through after the assay was approved as described in step 2 clamping, automatic turnover finish-milling is pitched ear everywhere, and right boring is respectively pitched earhole to size;
Step 5, undercarriage turns around to install, chuck clamps the technique head at the top of urceolus, bracing frame clamps and supports the benchmark cylindrical at urceolus middle part, change 90 ° of power conversion heads, the endoporus of boring cutter right boring urceolus is installed to size, the monolateral allowance of endoporus, the screw thread of boring and milling endoporus, changes the vertical processing technology chuck of milling head, and finish-milling benchmark cylindrical also connects suitable with the cutter trade of step 3, under undercarriage, lathe is gone round and round a millstone the interior unthreaded portion of bed mill endoporus to requiring to stay honing surplus, monolateral 0.02 mm, after Hole honing, milling machine removes the technique head at urceolus top.
The operation circulation of prior art has 17 times, and clamping workpiece has 23 times, uses frock 20 to overlap, and method of the present invention, operation circulation 12 times, clamping workpiece 12 times, use frock 10 to overlap, operation circulation reduces 5 times, and clamping workpiece reduces 11 times, use frock to save 10 covers, operation circulation reduces improves efficiency, and clamping workpiece reduces is guaranteed its precision, steady quality, use frock is saved, and makes process economy.
As preferred version of the present invention, in described step 1, monolateral allowance 10 mm of maximal projection size, described benchmark cylindrical is ¢ 141, in conjunction with the size of undercarriage urceolus, two benchmark cylindricals is defined as to same size, convenient its axiality of confirmation.
As preferred version of the present invention, in described step 1, slightly bore the endoporus of undercarriage urceolus, for the thick ¢ 106 to ¢ 100 that bores, prior art is slightly to bore ¢ 106 to ¢ 90, and the machining accuracy follow-up due to the inventive method can ensure, so this step can be machined directly into ¢ 100, raises the efficiency.
As preferred version of the present invention, while ensureing that lathe Maximum turning radius is greater than the radius of gyration of undercarriage, under lathe, add according to demand contour adjustment block, according to the undercarriage of the large small swing radius of difference, adjust the size of contour adjustment block.
As preferred version of the present invention, in step 3, rough mill fork ear made allowance 1 mm, heavy boring is respectively pitched monolateral made allowance 1 mm of ear, in prior art, rough mills fork ear made allowance 1 mm, heavy boring is respectively pitched the monolateral made allowance 2mm of ear, because method of the present invention has been used reliable technological datum, so the allowance of this step can suitably reduce now, to improve fine finishining efficiency.
As preferred version of the present invention, in step 5, the monolateral allowance 0.2mm of endoporus, the monolateral allowance of prior art endoporus is 0.5mm, because method of the present invention has been used reliable technological datum, so the monolateral allowance of the endoporus of this step can suitably reduce now, to improve honing efficiency.
compared with prior art, beneficial effect of the present invention:
Economy, efficiency are high, steady quality.
Brief description of the drawings:
Fig. 1 is the front view of institute's processing undercarriage in the present invention.
Fig. 2 is the cutaway view of the side-looking of institute's processing undercarriage in the present invention.
Fig. 3 is the axonometric drawing of institute's processing undercarriage in the present invention.
Fig. 4 is the first machining sketch chart of the present invention.
Fig. 5 is the second machining sketch chart of the present invention.
Fig. 6 is the 3rd machining sketch chart of the present invention.
Fig. 7 is the 4th machining sketch chart of the present invention.
Fig. 8 is the 5th machining sketch chart of the present invention.
Fig. 9 is the A place partial enlarged drawing in Fig. 2.
Figure 10 is prior art process figure.
Figure 11 is the inventive method process figure.
Figure 12 is prior art and Data Comparison figure of the present invention.
Mark in figure: 1-technique head, 2-centre bore, 3-benchmark cylindrical B, 4-benchmark cylindrical C, 5-tailstock, the contour adjustment block of 6-, 7-urceolus, 8-bracing frame, 9-90 ° of power conversion head, 10-boring cutter bar, 11-boring blade, 12-boring tool holder.
Detailed description of the invention
Below in conjunction with embodiment and detailed description of the invention, the present invention is described in further detail.But this should be interpreted as to the scope of the above-mentioned theme of the present invention only limits to following embodiment, all technology realizing based on content of the present invention all belong to scope of the present invention.
embodiment 1
A kind of Aircraft Main undercarriage (its structure is as Fig. 1,2,3,9) urceolus part by numerical control Integrated-manufacturing Techniques, it comprises:
Step 1, enter the roughing stage, tentatively determine blank shape by scribing by bench worker, again with milling machine to the layout line border to the profile processing that strips off the skin, by the monolateral allowance 10mm of maximal projection size, the benchmark cylindrical of general car finish turning undercarriage, this benchmark cylindrical is set as two, be ¢ 141, a middle part at undercarriage urceolus 7, as Fig. 4, for benchmark cylindrical B3, a bottom at urceolus 7, as Fig. 4, for benchmark cylindrical C4, start ¢ 106 endoporus of thick brill (rough turn) urceolus 7 from urceolus 7 bottoms to ¢ 100, the reserved technique head 1 at urceolus 7 tops, drill centre bore 2D(thereon as Fig. 5), the amendment of these several key elements and to add be mainly to provide unified technological datum and clip position for follow-up half essence and fine finishining, to realize number of times and the time effectively avoiding fiducial error phenomenon and reduce clamping centering, technological datum in the past carries out using product design as benchmark, and in manufacture process time because roughing and semifinishing all will be carried out milling and turning processing to profile, benchmark is also cut repeatedly so, so ensure that the accuracy of technological datum need to ensure each machining precision on the one hand, in the process of centering again, also need repeatedly to verify on the other hand and avoid error, the factor of two aspects is accumulated in and very easily causes together technological datum and the actual fiducial error of manufacturing benchmark to cause the quality accidents such as product dislocation, in order effectively to stop fiducial error, change now the design to technological datum, use machine chuck clamping ¢ 141 benchmark cylindricals and ensure that pivot overlaps, hold out against centre bore 2D to determine benchmark bus (see figure 7) with tailstock 5 again, once determining in semifinishing process subsequently and fine finishining process, will can not cut these two places again this benchmark, all the time process with this benchmark until fine finishining completes (comprising grinding), just remove technique chuck, ensure the technological datum between each operation and manufacture datum coincidence and the unifying datum between benchmark,
Step 2, enter the semifinishing stage, undercarriage is clamped on four axle lathes, ensure that lathe Maximum turning radius is greater than the radius of gyration of undercarriage taking urceolus 7 center lines as axle, in the time that lathe Maximum turning radius does not meet the demands, under lathe, add contour adjustment block 6, as Fig. 6, make lathe reach instructions for use; After machine reformation completes, reaching application target is also required to be lathe and prepares special numerical control language, i.e. rearmounted exploitation, make exactly the needed lathe code translater of corresponding Digit Control Machine Tool, diagram form cutter rail on terminal is translated to the simple digital code that lathe can be identified, drive lathe to make the actions such as milling, brill, turn-over, tool changing;
With the benchmark cylindrical of chuck clamping urceolus 7 bottoms, withstand the centre bore 2 at urceolus 7 tops that process in described step 1 with tailstock 5, clamp and support the benchmark cylindrical at urceolus 7 middle parts with a bracing frame 8, as Fig. 7;
Semifinishing urceolus 7 is in the past that machining center three axle processing profiles are again by boring machine roughing fork earhole due to what use.Complete Milling Process, must just can complete for several times by twice operation circulation turn-over clamping, product also needs centering repeatedly, not only increase labour intensity, reduce production efficiency, and improve requirement and the difficulty to execute-in-place level, make the manufacture process of urceolus 7 increase many artificial uncertain factors and hidden danger of quality, the quality accident that very easily causes the skew of part Working position and other maloperations to produce because of execute-in-place error, reduce operation circulation for reaching, shorten the clamping time, reduce labour intensity, enhance productivity, the effect of stabilized product quality, the present invention give this one-phase semifinishing and subsequent fine fabrication design four axles one press from both sides (chuck), one top (tailstock 5), the one fast-assembling method that supports (bracing frame 8) (is called 31 clampings, effect is installed and sees Fig. 7), greatly shorten the set-up time, the installation of bracing frame 8 also provides more stable condition of work to machining, not only solve a difficult problem for clamping centering, and allow the function of lathe be expanded, full use four axle turntable functions, achieve automatic turnover integrated brill boring machine function, ensure change lathe into by the key point manually ensureing in the past, create advantage for realizing highly-efficient processing,
Step 3 is turned over undercarriage each processing profile to dead size on lathe, rough mills fork ear made allowance 1mm, and heavy boring is respectively pitched the monolateral made allowance 1mm of ear, machine tool tapping, and undercarriage proceeds to quenching heat treatment;
Step 4, enter the fine finishining stage, clamping undercarriage, by lathe correction benchmark, polishing two place's benchmark cylindricals, ensure during this time its axiality, recasting centre bore 2D, must ensure the axiality of the benchmark cylindrical section of this hole associated in manufacturing process, through after the assay was approved as described in step 2 clamping, automatic turnover finish-milling is pitched ear everywhere, and right boring is respectively pitched earhole to size;
Step 5, as Fig. 8, undercarriage turns around to install, chuck clamps the technique head 1 at the top of urceolus 7, bracing frame 8 clamps and supports the benchmark cylindrical at urceolus 7 middle parts, change 90 ° of power conversion 9, install ¢ 100 endoporus that boring cutter right boring urceolus 7 processed to size ¢ 106(as Fig. 8, 9), boring cutter comprises boring cutter bar 10, boring blade 11, boring tool holder 12, the monolateral allowance 0.2mm of endoporus, the screw thread (as Fig. 9) of boring and milling endoporus M116, change the vertical processing of milling head ¢ 141 technique chucks, finish-milling benchmark cylindrical also connects suitable with the cutter trade of step 3, under undercarriage, lathe is gone round and round a millstone the interior unthreaded portion of bed mill endoporus to requiring to stay honing surplus, monolateral 0.02 mm, after Hole honing, milling machine removes the technique head 1 at urceolus 7 tops.
Prior art process, as Figure 10, is analyzed Figure 10, draws following data:
1: master operation circulation 17 times
2: use exclusive-used stock removing machine 5 classes (car, milling, boring, mill, brill) 11
3: clamping workpiece 23 times (comprise turn-over between the each work step of in-process, turn around)
4: master operation is used special tooling more than 20 covers
The inventive method, as Figure 11, is analyzed Figure 11, draws following data:
1: master operation circulation 12 times
2: use exclusive-used stock removing machine 3 classes (car, milling, mill) 7
3: clamping workpiece 12 times (comprise turn-over between the each work step of in-process, turn around)
4: master operation is used special tooling 10 to overlap
Contrast Figure 10, Tu11Hou, can draw the data of Figure 12, assess the cost:
A, clamping time cost:
Within 120 minutes consuming time, calculate with each clamping, should be the non-cutting time of saving so
Within 120 × 11=1320 minute, close 22 hours, calculate lathe cost with 150 yuan per hour
Both saved 150 × 22=3300 unit
B, frock manufacturing cost:
If do not considered Master Cost, need within 6 hours, to machine with every cover special tooling merely
Calculate, saving so manufacturing cost is 6 × 10 × 150=9000 unit
C, workpiece is reprocessed cost:
Reduce by 5 operation circulations because having improved technique, controlled the human factor of key link, reduced the probability of makeing mistakes, so seldom occur reprocessing, this part cost is stealthy, judges with previous experiences is conservative the average out to 8 hours of saving time, both cost-saving 8 × 150=1200 unit
To sum up, the application of this technology, conservative estimation can be manufactured cost-saving 3300+9000+1200=13500 unit for the undercarriage urceolus 7 of every sortie, and visible the method is raised the efficiency when ensuring the quality of products, and its economy is good.

Claims (6)

1. an Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques, it comprises:
Step 1, enter the roughing stage, tentatively determine blank shape by scribing by bench worker, then with milling machine to the layout line border to the profile processing that strips off the skin, by the monolateral allowance of maximal projection size, the benchmark cylindrical of general car finish turning undercarriage, this benchmark cylindrical is set as two, a middle part at undercarriage urceolus, a bottom at urceolus, start the thick endoporus that bores urceolus from urceolus bottom, at urceolus top, reserved technique head, drills centre bore thereon;
Step 2, enter the semifinishing stage, undercarriage is clamped on four axle lathes, ensure that lathe Maximum turning radius is greater than the radius of gyration of undercarriage taking urceolus center line as axle, with the benchmark cylindrical of chuck clamping urceolus bottom, withstand the centre bore at the urceolus top processing in described step 1 with tailstock, clamp and support the benchmark cylindrical at urceolus middle part with a bracing frame;
Step 3 is turned over undercarriage each processing profile to dead size on lathe, rough mills fork ear made allowance, and heavy boring is respectively pitched the monolateral made allowance of ear, machine tool tapping, and undercarriage proceeds to quenching heat treatment;
Step 4, enter the fine finishining stage, clamping undercarriage, by lathe correction benchmark, polishing two place's benchmark cylindricals, ensure during this time its axiality, recasting centre bore D, must ensure the axiality of the benchmark cylindrical section of this hole associated in manufacturing process, through after the assay was approved as described in step 2 clamping, automatic turnover finish-milling is pitched ear everywhere, and right boring is respectively pitched earhole to size;
Step 5, undercarriage turns around to install, chuck clamps the technique head at the top of urceolus, bracing frame clamps and supports the benchmark cylindrical at urceolus middle part, change 90 ° of power conversion heads, the endoporus of boring cutter right boring urceolus is installed to size, the monolateral allowance of endoporus, the screw thread of boring and milling endoporus, changes the vertical processing technology chuck of milling head, and finish-milling benchmark cylindrical also connects suitable with the cutter trade of step 3, under undercarriage, lathe is gone round and round a millstone the interior unthreaded portion of bed mill endoporus to requiring to stay honing surplus, monolateral 0.02 mm, after Hole honing, milling machine removes the technique head at urceolus top.
2. Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques according to claim 1, is characterized in that, in described step 1, and monolateral allowance 10 mm of maximal projection size, described benchmark cylindrical is ¢ 141.
3. Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques according to claim 2, is characterized in that, in described step 1, slightly bores the endoporus of undercarriage urceolus, is the thick ¢ 106 to ¢ 100 that bores.
4. Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques according to claim 3, is characterized in that, while ensureing that lathe Maximum turning radius is greater than the radius of gyration of undercarriage, adds according to demand contour adjustment block under lathe.
5. Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques according to claim 4, is characterized in that, in step 3, rough mills fork ear made allowance 1 mm, and heavy boring is respectively pitched monolateral made allowance 1 mm of ear.
6. Aircraft Main undercarriage urceolus part by numerical control Integrated-manufacturing Techniques according to claim 5, is characterized in that, in step 5, and the monolateral allowance 0.2mm of endoporus.
CN201410283469.0A 2014-06-23 2014-06-23 Aircraft main landing gear urceolus part by numerical control integrated manufacturing method CN104015015B (en)

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CN104015015B CN104015015B (en) 2016-04-06

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105414900A (en) * 2015-12-11 2016-03-23 江西昌河航空工业有限公司 Cylinder joint excircle processing method
CN109332999A (en) * 2018-09-25 2019-02-15 成都凯迪精工科技有限责任公司 A method of control blowing model or so wing deflection
CN110757094A (en) * 2019-10-31 2020-02-07 中航飞机起落架有限责任公司 Turning method of cylindrical stepped thin-wall part
CN111015079A (en) * 2019-10-17 2020-04-17 武汉船用机械有限责任公司 Processing method of fork joint
CN111604640A (en) * 2019-02-26 2020-09-01 江苏宏宝工具有限公司 Integrated machining process for metal workpiece

Families Citing this family (1)

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Publication number Priority date Publication date Assignee Title
CN107350754B (en) * 2017-09-12 2020-03-31 中航飞机起落架有限责任公司 Processing method of outer barrel with inclined annular groove

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EP1870196A1 (en) * 2006-06-20 2007-12-26 Protac Method of manufacturing a shaft of a mechanical connecting arm
US20080230650A1 (en) * 2007-03-19 2008-09-25 Jorg Meyer Aircraft landing gear
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105414900A (en) * 2015-12-11 2016-03-23 江西昌河航空工业有限公司 Cylinder joint excircle processing method
CN109332999A (en) * 2018-09-25 2019-02-15 成都凯迪精工科技有限责任公司 A method of control blowing model or so wing deflection
CN109332999B (en) * 2018-09-25 2020-08-04 成都凯迪精工科技有限责任公司 Method for controlling deformation of left wing and right wing of blowing model
CN111604640A (en) * 2019-02-26 2020-09-01 江苏宏宝工具有限公司 Integrated machining process for metal workpiece
CN111015079A (en) * 2019-10-17 2020-04-17 武汉船用机械有限责任公司 Processing method of fork joint
CN110757094A (en) * 2019-10-31 2020-02-07 中航飞机起落架有限责任公司 Turning method of cylindrical stepped thin-wall part

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