CN104015015B - Aircraft main landing gear urceolus part by numerical control integrated manufacturing method - Google Patents
Aircraft main landing gear urceolus part by numerical control integrated manufacturing method Download PDFInfo
- Publication number
- CN104015015B CN104015015B CN201410283469.0A CN201410283469A CN104015015B CN 104015015 B CN104015015 B CN 104015015B CN 201410283469 A CN201410283469 A CN 201410283469A CN 104015015 B CN104015015 B CN 104015015B
- Authority
- CN
- China
- Prior art keywords
- urceolus
- undercarriage
- numerical control
- boring
- endoporus
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 claims abstract description 40
- 238000012545 processing Methods 0.000 claims abstract description 20
- 238000006243 chemical reaction Methods 0.000 claims abstract description 5
- 238000003801 milling Methods 0.000 claims description 23
- 239000011295 pitch Substances 0.000 claims description 13
- 238000007514 turning Methods 0.000 claims description 9
- 230000007306 turnover Effects 0.000 claims description 8
- 238000005516 engineering process Methods 0.000 claims description 5
- 230000008859 change Effects 0.000 claims description 4
- 238000003556 assay Methods 0.000 claims description 3
- 238000012937 correction Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 3
- 238000010791 quenching Methods 0.000 claims description 3
- 230000000171 quenching effect Effects 0.000 claims description 3
- 238000010079 rubber tapping Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 description 9
- 230000004087 circulation Effects 0.000 description 7
- 241001074085 Scophthalmus aquosus Species 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000012790 confirmation Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012958 reprocessing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
Abstract
The present invention relates to the manufacture field of undercarriage, in particular to a kind of aircraft main landing gear urceolus part by numerical control Integrated-manufacturing Techniques, during its roughing, undercarriage stays technique head, technique head drills centre bore, simultaneously at the bottom of undercarriage urceolus and middle part machining benchmark cylindrical, use new technological datum, when clamping undercarriage in processing, have employed new clamp method, raise the efficiency, stabilised quality, during fine finishining simultaneously, overturn clamping direction, 90 ° of power conversion heads are used, make undercarriage when horizontal, the endoporus of undercarriage urceolus can be processed equally with machine tool, the object of the present invention is to provide a kind of economy, efficiency high, stay-in-grade undercarriage numerical control Integrated-manufacturing Techniques.
Description
Technical field
The present invention relates to the manufacture field of undercarriage, particularly aircraft main landing gear urceolus part by numerical control integrated manufacturing method.
Background technology
Undercarriage is the vitals profoundly affecting overall aircraft safety in airplane component, it is the vital part ensureing aircraft aircraft and personal security sliding, during take-off and landing, undercarriage bears huge impact and repeat load in take-off and landing process, due to the impact by alternate stress and large impact power, quality requirement is high, the quality of its quality just determines the quality of aircraft, safety and reliability, and its production cycle also determines the delivery cycle of aircraft;
In prior art, for large-scale manufacturer, that the large-scale special processing equipment of buying one is processed it, but very expensive, for little manufacturer, that impotentia is bought, so the little general machine tooling in 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 above-mentioned deficiency existing in prior art, a kind of economy, efficiency high, stay-in-grade undercarriage numerical control Integrated-manufacturing Techniques is provided.
In order to realize foregoing invention object, the invention provides following technical scheme:
A kind of aircraft main landing gear urceolus part by numerical control integrated manufacturing method, it comprises:
Step one, enter the roughing stage, tentatively determine blank shape by scribing by bench worker, then profile is stripped off the skin processing border to the layout line with milling machine, 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, from bottom urceolus, the thick endoporus boring urceolus, reserves technique head at urceolus top, 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 that undercarriage is axle with urceolus center line, with the benchmark cylindrical bottom chuck clamping urceolus, withstand the centre bore at the urceolus top of processing in described step one with tailstock, clamp with a bracing frame and support the benchmark cylindrical in the middle part of urceolus;
Step 3, undercarriage is turned over each processing profile to dead size on lathe, and rough mill fork ear made allowance, heavy boring respectively pitches the monolateral made allowance of ear, machine tool tapping, and undercarriage proceeds to quenching heat treatment;
Step 4, enter finishing stage, clamping undercarriage, by lathe correction benchmark, polishing two place benchmark cylindrical, period ensures 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 pitches ear everywhere, and right boring respectively pitches 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 in the middle part of urceolus, 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 go round and round a millstone bed mill endoporus in unthreaded portion to requiring to stay honing surplus, monolateral 0.02mm, 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 circulates 12 times, clamping workpiece 12 times, use frock 10 to overlap, operation circulation minimizing 5 times, clamping workpiece reduces 11 times, frock is used to save 10 covers, operation circulation minimizing makes efficiency improve, and clamping workpiece reduces makes its precision be guaranteed, steady quality, use frock is saved, and makes process economy.
As preferred version of the present invention, in described step one, the monolateral allowance 10mm of maximal projection size, described benchmark cylindrical is φ 141mm, in conjunction with the size of undercarriage urceolus, two benchmark cylindricals is defined as same size, convenient its axiality of confirmation.
As preferred version of the present invention, in described step one, the endoporus of thick brill undercarriage urceolus, for slightly boring φ 10mm6 to φ 100mm, prior art slightly bores φ 106mm to φ 90mm, the machining accuracy follow-up due to the inventive method can ensure, so this step can be machined directly into φ 100mm, raises the efficiency.
As preferred version of the present invention, when ensureing that lathe Maximum turning radius is greater than the radius of gyration of undercarriage, under lathe, add contour adjustment block according to demand, 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 1mm, heavy boring respectively pitches the monolateral made allowance 1mm of ear, in prior art, rough mills fork ear made allowance 1mm, heavy boring respectively pitches the monolateral made allowance 2mm of ear, because method of the present invention employs 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 employs 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.
Accompanying drawing illustrates:
Fig. 1 is the front view of institute's processing undercarriage in the present invention.
Fig. 2 is the sectional 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 that the scope of the above-mentioned theme of the present invention is only limitted to following embodiment, all technology realized based on content of the present invention all belong to scope of the present invention.
embodiment 1
A kind of aircraft main landing gear (its structure is as Fig. 1,2,3,9) urceolus part by numerical control Integrated-manufacturing Techniques, it comprises:
Step one, enter the roughing stage, tentatively blank shape is determined by scribing by bench worker, profile is stripped off the skin processing border to the layout line with milling machine again, 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 φ 141mm, 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, from bottom urceolus 7, the φ 106mm endoporus of thick brill (namely rough turn) urceolus 7 is to φ 100mm, technique head 1 is reserved at urceolus 7 top, drill centre bore 2D(thereon as Fig. 5), the amendment of these several key elements and add mainly for follow-up half essence and fine finishining provide unified technological datum and clip position, 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 because roughing and semifinishing all will carry out milling and turnery processing to profile time in the fabrication process, so benchmark is also cut repeatedly, so will ensure that the accuracy of technological datum needs to ensure each machining precision on the one hand, on the other hand also need repeatedly to verify in the process of centering again and avoid error, the factor of two aspects is accumulated in and very easily causes technological datum to cause the quality accidents such as product dislocation with the actual fiducial error manufacturing benchmark together, in order to effectively stop fiducial error, have changed now the design to technological datum, use machine chuck clamping φ 141mm benchmark cylindrical and ensure that pivot overlaps, centre bore 2D is held out against to determine benchmark bus (see figure 7) again with tailstock 5, this benchmark is once determine can not cut these two places in semifinishing process subsequently and finishing passes again, all the time carry out processing until fine finishining completes (comprising grinding) with this benchmark, just remove technique chuck, ensure technological datum between each operation and the datum coincidence manufactured between benchmark and unifying datum,
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 that undercarriage is axle with urceolus 7 center line, when 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, reach application target to be also required to be lathe and to prepare special numerical control language, i.e. rearmounted exploitation, make the lathe code translater required for corresponding Digit Control Machine Tool exactly, diagram form cutter rail on terminal is translated to the simple digital code that lathe can identify, drive lathe to make the actions such as milling, brill, turn-over, tool changing;
With the benchmark cylindrical bottom chuck clamping urceolus 7, withstand the centre bore 2 at urceolus 7 top of processing in described step one with tailstock 5, clamp with a bracing frame 8 and support the benchmark cylindrical in the middle part of urceolus 7, as Fig. 7;
Semifinishing urceolus 7 in the past, pitches earhole by boring machine roughing again owing to using machining center three axis machining profile.Complete Milling Process, must just can complete for several times by twice operation circulation turn-over clamping, product also needs centering repeatedly, not only add labour intensity, reduce production efficiency, and the requirement that improve execute-in-place level and difficulty, the manufacture process of urceolus 7 is made to add many artificial uncertain factors and hidden danger of quality, very easily because execute-in-place error causes the quality accident that part Working position offsets and other maloperations produce, operation circulation is reduced for reaching, shorten the clamping time, reduce labour intensity, enhance productivity, the effect of stabilized product quality, the present invention presss from both sides (chuck) to this one-phase semifinishing and subsequent fine fabrication design four axles one, one top (tailstock 5), the one fast-assembling method supporting (bracing frame 8) (is called 31 clampings, effect is installed and sees Fig. 7), substantially reduce 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 and integrated brill boring machine function, ensure changing lathe into by the key point manually ensured in the past, advantage is created for realizing highly-efficient processing,
Step 3, turns over each processing profile to dead size undercarriage on lathe, and rough mill fork ear made allowance 1mm, heavy boring respectively pitches the monolateral made allowance 1mm of ear, machine tool tapping, and undercarriage proceeds to quenching heat treatment;
Step 4, enter finishing stage, clamping undercarriage, by lathe correction benchmark, polishing two place benchmark cylindrical, period ensures 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 pitches ear everywhere, and right boring respectively pitches 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 in the middle part of urceolus 7, change 90 ° of power conversion 9, φ 100mm endoporus that boring cutter right boring urceolus 7 processed is installed to size φ 106mm(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 milling head vertical processing φ 141 technique chuck, finish-milling benchmark cylindrical also connects suitable with the cutter trade of step 3, under undercarriage lathe go round and round a millstone bed mill endoporus in unthreaded portion to requiring to stay honing surplus, monolateral 0.02mm, after Hole honing, milling machine removes the technique head 1 at urceolus 7 top.
Prior art process, as Figure 10, is analyzed Figure 10, is drawn following data:
1: master operation circulates 17 times
2: use exclusive-used stock removing machine 5 class (car, milling, boring, mill, brill) 11
3: clamping workpiece 23 times (comprise the turn-over between each work step of in-process, turn around)
4: master operation uses special tooling more than 20 to overlap
The inventive method, as Figure 11, is analyzed Figure 11, is drawn following data:
1: master operation circulates 12 times
2: use exclusive-used stock removing machine 3 class (car, milling, mill) 7
3: clamping workpiece 12 times (comprise the turn-over between each work step of in-process, turn around)
4: master operation uses 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, the non-cutting time of so saving should be
Within 120 × 11=1320 minute, close 22 hours, calculate lathe cost with 150 yuan per hour
Both 150 × 22=3300 unit had been saved
B, frock manufacturing cost:
If do not considered Master Cost, need within 6 hours, to machine often to overlap special tooling merely
Calculate, so saving manufacturing cost is 6 × 10 × 150=9000 unit
C, cost reprocessed by workpiece:
Decreasing 5 operation circulations because improving technique, controlling the human factor of key link, reducing probability of makeing mistakes, so seldom occur reprocessing, this part cost is stealthy, guards judgement to save time average out to 8 hours, both cost-saving 8 × 150=1200 unit with previous experiences
To sum up, the application of this technology, conservative estimation can manufacture cost-saving 3300+9000+1200=13500 unit for the undercarriage urceolus 7 of every sortie, and while visible the method is raised the efficiency and ensured the quality of products, its economy is good.
Claims (6)
1. an aircraft main landing gear urceolus part by numerical control integrated manufacturing method, it comprises:
Step one, enter the roughing stage, tentatively determine blank shape by scribing by bench worker, then profile is stripped off the skin processing border to the layout line with milling machine, 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, from bottom urceolus, the thick endoporus boring urceolus, reserves technique head at urceolus top, 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 that undercarriage is axle with urceolus center line, with the benchmark cylindrical bottom chuck clamping urceolus, withstand the centre bore at the urceolus top of processing in described step one with tailstock, clamp with a bracing frame and support the benchmark cylindrical in the middle part of urceolus;
Step 3, undercarriage is turned over each processing profile to dead size on lathe, and rough mill fork ear made allowance, heavy boring respectively pitches the monolateral made allowance of ear, machine tool tapping, and undercarriage proceeds to quenching heat treatment;
Step 4, enter finishing stage, clamping undercarriage, by lathe correction benchmark, polishing two place benchmark cylindrical, period ensures its axiality, to remake described centre bore, the axiality of the benchmark cylindrical section of this hole associated in manufacturing process, must be ensured, through after the assay was approved as described in step 2 clamping, automatic turnover finish-milling pitches ear everywhere, and right boring respectively pitches 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 in the middle part of urceolus, change 90 ° of power conversion heads, the endoporus of boring cutter right boring urceolus is installed to requiring size, the monolateral allowance of endoporus, the screw thread of boring and milling endoporus, changes the vertical processing technology chuck of milling head, finish-milling benchmark cylindrical also connects suitable with the cutter trade of step 3, under undercarriage, lathe is gone round and round a millstone bed, and in mill endoporus, unthreaded portion is to requiring to stay honing surplus, monolateral 0.02mm, after Hole honing, milling machine removes the technique head at urceolus top.
2. aircraft main landing gear urceolus part by numerical control integrated manufacturing method according to claim 1, is characterized in that, in described step one, the monolateral allowance 10mm of maximal projection size, described benchmark cylindrical is φ 141mm.
3. aircraft main landing gear urceolus part by numerical control integrated manufacturing method according to claim 2, is characterized in that, in described step one, the thick endoporus boring undercarriage urceolus, for slightly boring φ 106mm to φ 100mm.
4. aircraft main landing gear urceolus part by numerical control integrated manufacturing method according to claim 3, is characterized in that, when ensureing that lathe Maximum turning radius is greater than the radius of gyration of undercarriage, adds contour adjustment block according to demand under lathe.
5. aircraft main landing gear urceolus part by numerical control integrated manufacturing method according to claim 4, is characterized in that, in step 3, rough mill fork ear made allowance 1mm, heavy boring respectively pitches the monolateral made allowance 1mm of ear.
6. aircraft main landing gear urceolus part by numerical control integrated manufacturing method according to claim 5, is characterized in that, in step 5, and the monolateral allowance 0.2mm of endoporus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410283469.0A CN104015015B (en) | 2014-06-23 | 2014-06-23 | Aircraft main landing gear urceolus part by numerical control integrated manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410283469.0A CN104015015B (en) | 2014-06-23 | 2014-06-23 | Aircraft main landing gear urceolus part by numerical control integrated manufacturing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104015015A CN104015015A (en) | 2014-09-03 |
| CN104015015B true CN104015015B (en) | 2016-04-06 |
Family
ID=51432169
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410283469.0A Active CN104015015B (en) | 2014-06-23 | 2014-06-23 | Aircraft main landing gear urceolus part by numerical control integrated manufacturing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104015015B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107350754A (en) * | 2017-09-12 | 2017-11-17 | 中航飞机起落架有限责任公司 | Processing method with oblique ring shaped slot outer barrel |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105414900B (en) * | 2015-12-11 | 2017-10-10 | 江西昌河航空工业有限公司 | A kind of Excircle machining method of column joint |
| 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 |
| CN111015079B (en) * | 2019-10-17 | 2021-06-22 | 武汉船用机械有限责任公司 | Processing method of fork joint |
| CN110757094B (en) * | 2019-10-31 | 2020-11-24 | 中航飞机起落架有限责任公司 | Turning method of cylindrical stepped thin-wall part |
| CN114102068B (en) * | 2021-12-17 | 2023-10-03 | 江西洪都航空工业集团有限责任公司 | Processing method and die for support arm part with special-shaped structure |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2902358B1 (en) * | 2006-06-20 | 2008-08-01 | Protac | METHOD FOR MANUFACTURING A MECHANICAL ROD TREE |
| DE102007019052A1 (en) * | 2007-03-19 | 2008-09-25 | Liebherr-Aerospace Lindenberg Gmbh | aircraft landing gear |
| CN102581620B (en) * | 2012-03-14 | 2013-11-06 | 北京航空航天大学 | Method for turning and milling to realize typical characteristics of aircraft landing gear |
-
2014
- 2014-06-23 CN CN201410283469.0A patent/CN104015015B/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107350754A (en) * | 2017-09-12 | 2017-11-17 | 中航飞机起落架有限责任公司 | Processing method with oblique ring shaped slot outer barrel |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104015015A (en) | 2014-09-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104015015B (en) | Aircraft main landing gear urceolus part by numerical control integrated manufacturing method | |
| CN203061947U (en) | High-efficiency face milling cutter of machining center | |
| CN105328207B (en) | A kind of clamped one time processing method of double-end face end cap | |
| CN108000071A (en) | A kind of processing technology of axis | |
| CN104801935A (en) | Method for processing aircraft aluminum alloy special-shaped cabin | |
| CN103506816A (en) | Processing technique of planet carrier of coal cutter | |
| CN105583581A (en) | Machining method and device for bearing standard block | |
| CN106078252B (en) | A kind of clamp for machining and processing method with fiberglass cambered surface and ladder hole type parts | |
| CN203197566U (en) | Multi-station automatic indexing combination numerically-controlled machine tool | |
| CN203875650U (en) | Y-shaped rocker arm molded face milling and positioning fixture | |
| CN104400475B (en) | A kind of positioning and clamping instrument and method | |
| CN104646948A (en) | Machining method of high-precision gear shaft | |
| CN104259778A (en) | Machining method of bearing shell of turbocharger | |
| CN102848152A (en) | Processing method of manipulators | |
| CN104439896B (en) | The processing method that eccentric excircle has the section tube of flange arrangement with boss two ends | |
| CN204171426U (en) | A kind of facing cutter being applicable to connecting rod Double Milling lathe | |
| CN103084809A (en) | Machining method for triquetrum hole | |
| CN202726089U (en) | Combined turning tool | |
| CN106312463B (en) | The processing method of the Large Hydropower Station not isometrical bearing body of pintongs | |
| CN104924022A (en) | Simple and rapid machining method for part with perpendicularly intersecting hole | |
| CN106541306A (en) | Double-station numerical control face grinding machine device | |
| CN103447559B (en) | Flat seal O RunddichtringO draw-in groove process tool | |
| CN203197410U (en) | Gear hobbing fixture | |
| CN106346213A (en) | Mechanical processing method of large connection rod | |
| CN202169506U (en) | Lathe clamp |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3 Applicant after: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. Address before: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3 Applicant before: Shifang City Mingri Space Navigation Industry Co.,Ltd. |
|
| COR | Change of bibliographic data | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 618400 No. 3, Lantian Avenue, Shifang Economic Development Zone (North District), Deyang City, Sichuan Province Patentee after: Sichuan Xinhang Titanium Technology Co.,Ltd. Address before: 618400 No. 3, Lantian Avenue, Shifang Economic Development Zone (North District), Deyang City, Sichuan Province Patentee before: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. |