CN101695768B - Process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane - Google Patents
Process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane Download PDFInfo
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- CN101695768B CN101695768B CN200910186377XA CN200910186377A CN101695768B CN 101695768 B CN101695768 B CN 101695768B CN 200910186377X A CN200910186377X A CN 200910186377XA CN 200910186377 A CN200910186377 A CN 200910186377A CN 101695768 B CN101695768 B CN 101695768B
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Abstract
The invention relates to the technical field of mechanical machining, in particular to a process for manufacturing a serial, double-seat and integrated cockpit canopy framework of an airplane. The process adopts a five-coordinate high-speed mill to perform process flows of the determination of a crude benchmark, blanking, crude machining, semi-finished machining, finish machining and polishing bya bench worker, adjusts the processing allowance of each working procedure through reasonable process layout, arranges natural time-effect time, optimizes parameters of a machining speed, a feeding mode and the like so that a part can evenly remove allowance to farthest reduce the deformation amount of the part; and the process adopts a half-symmetrical machining and clamping method, solves the problems of clamping and vibration in part machining and ensures the dimension and precision of the part.
Description
Technical field:
The present invention relates to the Machining Technology field, particularly a kind of process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane.
Background technology
Serial two-crew cockpit lid skeleton is a kind of two-seat airplane portable cover skeleton, serial two-crew cockpit lid skeleton in the past all is made up of frontal arc frame, middle arc frame, backarc frame, left side section bar and right side section bar five big parts, five big parts need adopt the tailored version frame to assemble, exchanging the degree of accuracy of coordinating after the part processing is difficult to guarantee, skeleton easily produces distortion, with Transparent Parts assembly relation complexity, its rigidity also can be affected simultaneously.And the employing serial, double-seat and integrated cockpit canopy framework, can reduce the skeleton assembly difficulty and improve the skeleton integral rigidity, can also improve the assembly relation of Transparent Parts and skeleton, framework deformation and erection stress are reduced greatly, improve its service life and maintenance cost, but because serial, double-seat and integrated cockpit canopy framework complex structure, the design of part poor rigidity, yielding, profile tolerance and skeleton flatness be cannot say for sure to demonstrate,prove, the program composition complexity not only will guarantee physical dimension, but also will avoid machine tool chief axis to bump with part or frock in working angles.By looking into the Computerized Numerical Control processing technology of new large forgings serial, double-seat and integrated cockpit canopy framework, domesticly do not see the identical bibliographical information of openly studying.
Process this part following three big difficult points are arranged: 1) design of part complexity, material is LD5, and it is more concentrated to add the man-hour stress ratio, and distortion is difficult to control; 2) part positioning and clamping difficulty adds easily to produce man-hour and shakes; 3) establishment of part process scheme and program, rational cutting way are difficult to customization.
Summary of the invention
The objective of the invention is, propose the technology controlling and process way of a kind of serial, double-seat and integrated cockpit canopy framework processing, with vibration problems in the distortion that solves the one-piece canopy skeleton and the processing.By rational process layout, regulate the allowance of per pass operation, arrange natural aging time, optimize parameters such as process velocity, tool path pattern, make part can remove surplus uniformly, reduce the deflection of part to greatest extent; Adopt and divide hemihedrism processing and loading clamp method, solve clamping and vibration problems in the part processing, guarantee the size and the precision of part.
Technical scheme of the present invention is that a kind of process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane adopts five coordinate High Speed Milling Operation to carry out thick surely benchmark, blanking, roughing, semifinishing, fine finishining and pincers worker polishing, it is characterized in that technological process is as follows:
1) fixed thick benchmark: pincers worker is found out the thick benchmark in skeleton baseplane with the whole model line of skeleton, ties datum level with five coordinate Digit Control Machine Tools, and with the datum level location, finds out X, Y, three direction processing of Z location benchmark with skeleton profile program.
2) blanking: with the location, bottom surface, pressing plate clamping skeleton inboard, processing skeleton outer mold surface is removed most of surplus, obtains the blank of a refinement, and outer mold surface is reserved the 20mm process allowance.
3) roughing:
A. process outer mold surface: with location, bottom surface, pressing plate clamping skeleton inboard, roughing skeleton outer mold surface, processing back part is reserved the 10mm process allowance, lateral surface patch position, both sides mills out the pressing plate groove, and mills out the directions X benchmark in backarc frame edge, goes out to mill out the Y directional reference at left and right sides section bar;
B. profile in processing: part turn-over, locate with both sides section bar upper surface with 4 high anchor clamps of 600mm, with the part bed hedgehopping, lateral surface pressing plate groove clamping, profile roughing in carrying out, profile is reserved the 10mm process allowance in the part of processing back, and side section bar bottom surface symmetry is reserved six 100 (length) * 80 (wide) * 70 (height) technology patch, mills out the pressing plate groove at the patch medial surface;
C. natrual ageing:＞72 hours;
4) semifinishing:
A. profile in processing: locate with both sides section bar upper surface with 6 high anchor clamps of 600mm, lateral surface pressing plate groove clamping, the directions X benchmark is taken from the edge benchmark of roughing backarc frame, the Y directional reference is taken from the axis of symmetry of skeleton, open the shelves distortion to eliminate skeleton, profile in the semifinishing, skeleton is reserved the 4mm process allowance; Process the back and mill out the directions X benchmark, mill out the Y directional reference six patch both sides in backarc frame patch position;
B. process outer mold surface: with 6 high anchor clamps of 300mm with technology patch bottom surface location, medial surface pressing plate groove clamping, the semifinishing outer mold surface, before, during and after arc frame position increase the supplemental support anchor clamps, skeleton is reserved the 4mm process allowance; Process the back and mill out directions X and Y directional reference again in backarc frame patch position;
C. natrual ageing:＞72 hours;
5) fine finishining: (the thick size 4mm of thin-walled, tolerance-0.1～+ 0.2)
A. process outer mold surface: with technology patch bottom surface location, medial surface pressing plate groove clamping adopts and divides hemihedrism clamping method, prevents to add the vibrations in man-hour with 6 high anchor clamps of 300mm, a fine finishining left side half outer mold surface, before, during and after the right subluxation of arc frame put and increase the supplemental support anchor clamps; Right half outer mold surface of fine finishining then, will before, during and after arc frame supplemental support anchor clamps move to left subluxation and put; Process the back and mill out directions X and Y directional reference in backarc frame patch position;
B. profile in processing; With both sides section bar upper surface location, lateral surface pressing plate groove clamping adopts and divides hemihedrism clamping method, prevents to add the vibrations in man-hour with 6 high anchor clamps of 600mm, profile in the fine finishining left side half, before, during and after the right subluxation of arc frame put and increase the supplemental support anchor clamps; Profile in the fine finishining right half then,
Will before, during and after arc frame supplemental support anchor clamps move to left subluxation and put; Last section bar inboard, clamping both sides,
The technology patch is removed;
6) pincers worker polishing: repair file processing dead angle, the inside and outside surface of polishing.
Described part is a serial, double-seat and integrated cockpit canopy framework of airplane.
Advantage of the present invention is, for this class part provides a kind of technology solution, reduced the deflection of part, solved the difficult problem of parts fixation, location, avoided the seismism in the processing, guaranteed the size and the precision of part.Also used machining simulation software to carry out program verification before reality processing, checked out the mistake of numerical control program and the excess of stroke of lathe effectively, variety of issues such as collision guarantee the correctness of numerical control program to greatest extent.
Description of drawings
Fig. 1 is the schematic diagram of serial, double-seat and integrated cockpit canopy framework of airplane among the present invention
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing 1, and as shown in Figure 1, serial two-crew cockpit lid skeleton is a kind of two-seat airplane portable cover skeleton, and frontal arc frame, middle arc frame, backarc frame, left side section bar and right side section bar five big parts are overall structure.Serial, double-seat and integrated cockpit canopy framework of airplane of the present invention adopts five coordinate High Speed Milling Operation to carry out thick surely benchmark, blanking, roughing, semifinishing, fine finishining and pincers worker polishing, and technological process is as follows:
1) fixed thick benchmark: pincers worker is found out the thick benchmark in skeleton baseplane with the whole model line of skeleton, ties datum level with five coordinate Digit Control Machine Tools, and with the datum level location, finds out X, Y, three direction processing of Z location benchmark with skeleton profile program.
2) blanking: with the location, bottom surface, pressing plate clamping skeleton inboard, processing skeleton outer mold surface is removed most of surplus, obtains the blank of a refinement, and outer mold surface is reserved the 20mm process allowance.
3) roughing:
A. process outer mold surface: with location, bottom surface, pressing plate clamping skeleton inboard, roughing skeleton outer mold surface, processing back part is reserved the 10mm process allowance, lateral surface patch position, both sides mills out the pressing plate groove, and mills out the directions X benchmark in backarc frame edge, goes out to mill out the Y directional reference at left and right sides section bar;
B. profile in processing: part turn-over, locate with both sides section bar upper surface with 4 high anchor clamps of 600mm, with the part bed hedgehopping, lateral surface pressing plate groove clamping, profile roughing in carrying out, profile is reserved the 10mm process allowance in the part of processing back, and side section bar bottom surface symmetry is reserved six 100 (length) * 80 (wide) * 70 (height) technology patch, mills out the pressing plate groove at the patch medial surface;
C. natrual ageing:＞72 hours;
4) semifinishing:
A. profile in processing: locate with both sides section bar upper surface with 6 high anchor clamps of 600mm, lateral surface pressing plate groove clamping, the directions X benchmark is taken from the edge benchmark of roughing backarc frame, the Y directional reference is taken from the axis of symmetry of skeleton, open the shelves distortion to eliminate skeleton, profile in the semifinishing, skeleton is reserved the 4mm process allowance; Process the back and mill out the directions X benchmark, mill out the Y directional reference six patch both sides in backarc frame patch position;
B. process outer mold surface: with 6 high anchor clamps of 300mm with technology patch bottom surface location, medial surface pressing plate groove clamping, the semifinishing outer mold surface, before, during and after arc frame position increase the supplemental support anchor clamps, prevent to add the flutter in man-hour, skeleton is reserved the 4mm process allowance; Process the back and mill out directions X and Y directional reference again in backarc frame patch position;
C. natrual ageing:＞72 hours;
5) fine finishining: (the thick size 4mm of thin-walled, tolerance-0.1～+ 0.2)
A. process outer mold surface: with technology patch bottom surface location, medial surface pressing plate groove clamping adopts and divides hemihedrism clamping method, prevents to add the vibrations in man-hour with 6 high anchor clamps of 300mm, a fine finishining left side half outer mold surface, before, during and after the right subluxation of arc frame put and increase the supplemental support anchor clamps; Right half outer mold surface of fine finishining then, will before, during and after arc frame supplemental support anchor clamps move to left subluxation and put; Process the back and mill out directions X and Y directional reference in backarc frame patch position;
B. profile in processing; With both sides section bar upper surface location, lateral surface pressing plate groove clamping adopts and divides hemihedrism clamping method, prevents to add the vibrations in man-hour with 6 high anchor clamps of 600mm, profile in the fine finishining left side half, before, during and after the right subluxation of arc frame put and increase the supplemental support anchor clamps; Profile in the fine finishining right half then, will before, during and after arc frame supplemental support anchor clamps move to left subluxation and put; The technology patch is removed in last section bar inboard, clamping both sides;
6) pincers worker polishing: repair file processing dead angle, the inside and outside surface of polishing;
Described part is a serial, double-seat and integrated cockpit canopy framework of airplane.
Concrete machined parameters is as follows:
1) fixed thick benchmark
Use lathe: five coordinate high-speed numeric control milling machines;
Use cutter: φ 32R3 indexable insert tip, throw away tip slotting cutter;
Machined parameters: cutting-in 2～3mm; Cut wide 20mm; Part made allowance 20mm;
Lathe rotating speed: 16000rpm;
Cutting speed: 8000mmpm.
2) roughing
Use lathe: five coordinate high-speed numeric control milling machines;
Use cutter: φ 20R3 solid carbide end mill;
Machined parameters: cutting-in 2～3mm; Cut wide 10mm; Part made allowance 10mm;
Lathe rotating speed: 14000～16000rpm;
Cutting speed: 8000～10000mmpm.
3) semifinishing
Use lathe: five coordinate high-speed numeric control milling machines;
Use cutter: φ 20R3 solid carbide end mill;
Machined parameters: cutting-in 2mm; Cut wide 8mm; Part made allowance 4mm;
Lathe rotating speed: 14000～16000rpm;
Cutting speed: 8000～10000mmpm.
4) fine finishining
Use lathe: five coordinate high-speed numeric control milling machines;
Use cutter: φ 16R3 solid carbide end mill;
Machined parameters: cutting-in 1～1.5mm; Cut wide 2～4mm;
Lathe rotating speed: 14000～16000rpm;
Cutting speed: 6000～8000mmpm.
Above processing technology is used to process serial, double-seat and integrated cockpit canopy framework of airplane class heavy parts, can effectively control part deformation, guarantees wall thickness dimension.
Claims (1)
1. a process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane adopts five coordinate High Speed Milling Operation to carry out thick surely benchmark, blanking, roughing, semifinishing, fine finishining and pincers worker polishing, it is characterized in that technological process is as follows:
1) fixed thick benchmark: pincers worker is found out the thick benchmark in skeleton baseplane with the whole model line of skeleton, ties datum level with five coordinate Digit Control Machine Tools, and with the datum level location, finds out X, Y, three direction processing of Z location benchmark with skeleton profile program;
2) blanking: with the location, bottom surface, pressing plate clamping skeleton inboard, processing skeleton outer mold surface is removed most of surplus, obtains the blank of a refinement, and outer mold surface is reserved the 20mm process allowance;
3) roughing:
A. process outer mold surface: with location, bottom surface, pressing plate clamping skeleton inboard, roughing skeleton outer mold surface, processing back part is reserved the 10mm process allowance, lateral surface patch position, both sides mills out the pressing plate groove, and mills out the directions X benchmark in backarc frame edge, and the place mills out the Y directional reference at left and right sides section bar;
B. profile in processing: part turn-over, locate with both sides section bar upper surface with 4 high anchor clamps of 600mm, with the part bed hedgehopping, lateral surface pressing plate groove clamping, profile roughing in carrying out, profile is reserved the 10mm process allowance in the part of processing back, and side section bar bottom surface symmetry is reserved six 100mm * 80mm * 70mm technology patch, mills out the pressing plate groove at the patch medial surface;
C. natrual ageing:＞72 hours;
4) semifinishing:
A. profile in processing: locate with both sides section bar upper surface with 6 high anchor clamps of 600mm, lateral surface pressing plate groove clamping, the directions X benchmark is taken from the edge benchmark of roughing backarc frame, the Y directional reference is taken from the axis of symmetry of skeleton, open the shelves distortion to eliminate skeleton, profile in the semifinishing, skeleton is reserved the 4mm process allowance; Process the back and mill out the directions X benchmark, mill out the Y directional reference six patch both sides in backarc frame patch position;
B. process outer mold surface: with 6 high anchor clamps of 300mm with technology patch bottom surface location, medial surface pressing plate groove clamping, the semifinishing outer mold surface, before, during and after arc frame position increase the supplemental support anchor clamps, skeleton is reserved the 4mm process allowance; Process the back and mill out directions X and Y directional reference again in backarc frame patch position;
C. natrual ageing:＞72 hours;
5) fine finishining:
A. process outer mold surface: with technology patch bottom surface location, medial surface pressing plate groove clamping adopts and divides hemihedrism clamping method, prevents to add the vibrations in man-hour with 6 high anchor clamps of 300mm, a fine finishining left side half outer mold surface, before, during and after the right subluxation of arc frame put and increase the supplemental support anchor clamps; Right half outer mold surface of fine finishining then, will before, during and after arc frame supplemental support anchor clamps move to left subluxation and put; Process the back and mill out directions X and Y directional reference in backarc frame patch position;
B. profile in processing; With both sides section bar upper surface location, lateral surface pressing plate groove clamping adopts and divides hemihedrism clamping method, prevents to add the vibrations in man-hour with 6 high anchor clamps of 600mm, profile in the fine finishining left side half, before, during and after the right subluxation of arc frame put and increase the supplemental support anchor clamps; Profile in the fine finishining right half then, will before, during and after arc frame supplemental support anchor clamps move to left subluxation and put; The technology patch is removed in last section bar inboard, clamping both sides;
6) pincers worker polishing: repair file processing dead angle, the inside and outside surface of polishing.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910186377XA CN101695768B (en) | 2009-10-29 | 2009-10-29 | Process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN200910186377XA CN101695768B (en) | 2009-10-29 | 2009-10-29 | Process for manufacturing serial, double-seat and integrated cockpit canopy framework of airplane |
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| CN101695768B true CN101695768B (en) | 2011-01-26 |
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| CN101856799A (en) * | 2010-05-13 | 2010-10-13 | 苏州利盾航空材料有限公司 | Method utilizing mirror-polishing process to manufacture aviation organic glass window |
| CN103737081A (en) * | 2013-12-20 | 2014-04-23 | 柳州正菱集团有限公司 | Technique for milling intermediate convex plane of bearing support of automobile intermediate shaft |
| CN103995920A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Edge connection degumming analysis method for flexible connection structure |
| CN105834698B (en) * | 2016-05-25 | 2018-01-30 | 江西洪都航空工业集团有限责任公司 | A kind of solid solution steel hinge milling method using rotatable disc clamping |
| CN107377941B (en) * | 2017-08-03 | 2019-02-19 | 上汽大众汽车有限公司 | The manufacturing method of data control model part |
| CN111890326A (en) * | 2020-08-05 | 2020-11-06 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Three-coordinate positioning machining reference marking method |
| CN113001125A (en) * | 2021-03-19 | 2021-06-22 | 沈阳万事达机械有限公司 | Process flow of empennage framework |
| CN113977200A (en) * | 2021-11-05 | 2022-01-28 | 上海机电工程研究所 | Guide rail processing method and special boring bar |
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