CN112935707A - Machining method for airplane support type parts - Google Patents
Machining method for airplane support type parts Download PDFInfo
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- CN112935707A CN112935707A CN201911263867.5A CN201911263867A CN112935707A CN 112935707 A CN112935707 A CN 112935707A CN 201911263867 A CN201911263867 A CN 201911263867A CN 112935707 A CN112935707 A CN 112935707A
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- 238000003754 machining Methods 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 36
- 238000003801 milling Methods 0.000 claims abstract description 15
- 238000005553 drilling Methods 0.000 claims abstract description 7
- 238000007689 inspection Methods 0.000 claims abstract description 7
- 230000002093 peripheral effect Effects 0.000 claims abstract description 4
- 238000005498 polishing Methods 0.000 claims abstract description 4
- 238000007514 turning Methods 0.000 claims abstract description 4
- 238000004458 analytical method Methods 0.000 claims abstract description 3
- 239000007787 solid Substances 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 9
- 238000005520 cutting process Methods 0.000 claims description 8
- 238000009966 trimming Methods 0.000 claims description 3
- 238000003672 processing method Methods 0.000 description 5
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
A machining method for airplane support type parts comprises the following steps: performing process analysis on parts, determining the number of parts which can be processed by each blank according to the process characteristics of the support parts, the used equipment, and establishing a three-dimensional entity model after multiple parts are combined after determining the front surface and the back surface which are optimally processed according to the number of parts which can be processed by each blank; milling six surfaces of a part blank, ensuring the requirement of flatness, determining a reference surface, and processing the final height of the part in place; drilling, expanding and reaming 2-phi 18H9 process holes at two ends of the blank; performing light splitting and hardness inspection to meet the requirements of a drawing; performing rough machining from the front side of the blank; clamping after turning over the blank, and roughly and finely machining the other side of the part; and removing the peripheral frame body of the part, and filing, polishing and milling the part which can not be cut. The machining method of the airplane support type part effectively solves the problems of complex machining process and low working efficiency of the airplane support type part, and realizes the simultaneous machining of a plurality of parts.
Description
Technical Field
The invention belongs to the technical field of aviation machining, and particularly relates to a machining method of an airplane support part.
Background
In an airplane operating system, a large number of pull rods are fixed at corresponding positions of an airplane through a support, parts such as shafts, sleeves and pulleys are mounted on the support, meanwhile, the airplane support parts have good stability, the pull rod parts are kept at correct positions and move flexibly, the pull rod parts have prominent positions among a plurality of practical parts, and the processing quality of the pull rod parts has direct influence on the service life, reliability and safety of the airplane operating system. The structural form of the bracket type part changes with different brackets, but has a plurality of common characteristics: the part has a complex structural form, a thin wall thickness and is easy to deform during processing, and the processing precision requirements among all surfaces are not very high, but the coordination requirements are extremely high, so that the part looks simple, but the processing difficulty is generally high, and the number of processes is large. The common material is generally 7050-T7451 type aluminum alloy plate, in the traditional processing process, blanking is usually carried out according to the blank size in the material quota, the whole plate is cut into small blocks of blanks, corresponding allowance is usually reserved for rough machining in order to prevent deformation in the processing process, then finish machining is carried out, the positioning datum is not uniform, the workpiece is clamped and adjusted for multiple times, the positioning datum is found, a large amount of part changing and preparing time is needed, meanwhile, the requirement on skill and experience of a processor is high, the process parameter is improperly controlled, parts are extremely easy to be milled and damaged, and the problems of complex process steps, low working efficiency and the like exist.
Disclosure of Invention
In order to solve the problems, the invention provides a method for machining an airplane bracket part.
A machining method for airplane support type parts comprises the following steps: (1) preparing materials: performing process analysis on parts, determining the number of parts which can be processed by each blank as much as possible according to the process characteristics of the support parts, used equipment, cutters and the like, determining the front and back surfaces which are optimally processed according to the number of parts which can be processed by each blank, and creating a multi-part combined three-dimensional solid model; (2) processing a positioning reference surface: milling six surfaces of a part blank, ensuring the requirement of flatness, determining a reference surface, and processing the final height of the part in place; (3) drilling and reaming a process hole: drilling, expanding and reaming 2-phi 18H9 process holes at two ends of the blank; (4) light splitting and hardness inspection: performing light splitting and hardness inspection to meet the requirements of a drawing; (5) one surface is rough and fine machined: clamping the blank by utilizing the two holes, namely clamping the blank, and performing rough machining and finish machining on the front side of the blank to ensure the size requirement of the part; (6) and (3) rough and finish machining of the other side: clamping the blank after turning over, and roughly and finely machining the other side of the part to ensure the size requirement of the part; (7) trimming: and removing the peripheral frame body of the part, cutting off the connecting blocks between the part and the part, removing all milled burrs, and filing, polishing and milling parts which cannot be milled, wherein all sharp-edge chamfers are R0.5.
Further, the length and the width of the blank prepared in the step (1) of the processing method of the airplane support type parts are respectively more than 120mm larger than that of the three-dimensional solid model of the assembly, and the length and the width of the blank are symmetrically distributed on two sides so as to keep a clamping position with a single side not less than 20mm and have enough space for the diameter of a milling cutter.
Furthermore, in the step (6) of the processing method of the airplane support type parts, when the other surface is processed, connecting blocks with the thickness of 0.5mm are reserved between the parts and the frame body, so that the processing rigidity of the parts is kept, and the parts are prevented from being milled and damaged.
Further, the method for machining the airplane support type part comprises the step (1) of creating a multi-piece combined three-dimensional solid model and keeping a tool to have enough machining space.
The processing method of the airplane support type part has the advantages that the problems of complex processing technology and low working efficiency of the airplane support type part are effectively solved, the number of parts which can be processed by each blank is determined as much as possible according to the process characteristics of the support type part, used equipment, cutters and the like, the simultaneous processing of a plurality of parts is realized through the clamping and positioning mode of one surface of two holes, the processing and positioning reference of the front surface and the reverse surface is uniform, and the processing quality of the parts is obviously improved; meanwhile, the number of parts processed by the same plate material is doubled, so that the cost of raw materials is saved; a plurality of parts are processed at the same time by one-time clamping, so that the preparation and replacement time for manufacturing the parts is saved; the machining stroke of the numerical control equipment is fully utilized, the failure rate caused by serious local abrasion of the equipment is avoided, the technical improvement cost and the maintenance cost can be indirectly reduced, and the effective cutting rate of the cutter is improved. In conclusion, the manufacturing cost is obviously saved, and the processing efficiency and the processing quality are improved.
Drawings
FIG. 1: is a front view of the airplane support type part of the invention.
Detailed Description
Embodiments of the present invention will be described in more detail below with reference to the accompanying drawings.
FIG. 1 is a front view of a typical aircraft support-type part having a maximum profile of 100mm 80.5mm 61.5 mm; the part material is 7050-T7451; the heat treatment is carried out until the sigma b is more than or equal to 370 MPa; the thinnest wall thickness dimension is 1.5 mm.
The key point of the processing method of the airplane bracket parts is as follows: according to the technical characteristics of the parts, the used equipment, cutters and the like, the number of the parts which can be machined by each plate is determined as much as possible, a three-dimensional solid model combined by the parts 1 is created, and the front surface and the back surface of the parts which are optimally machined are found after the positioning reference surface for clamping the parts is determined. And (2) performing rough machining and finish machining on the three-dimensional solid model recreated by the part 1 by adopting a three-axis low-speed numerical control milling machine, wherein the specific process flow comprises the following steps:
(1) preparing materials: the rough material is selected to be 7050-T7451-delta 70 multiplied by 720mm multiplied by 270mm, and according to the process characteristics of the part, the used equipment, a cutter and the like, the number of the parts which can be processed by each rough material can be determined to be 20, namely, a three-dimensional solid model is created through arrangement, and the front surface and the back surface of the part which are processed optimally are determined.
(2) Processing a positioning reference surface: milling six surfaces of a part blank, ensuring the requirement of flatness, determining a positioning reference surface, and keeping the thickness of the blank to be 61.5 mm;
(3) drilling and reaming a process hole: drilling, expanding and reaming 2-phi 18H9 process holes at two ends of the blank, and keeping the edge distance of the minimum hole at 15 mm;
(4) light splitting and hardness inspection: and (4) performing light splitting and hardness inspection on one end of the blank to meet the requirements of a drawing.
(5) One surface is rough and fine machined: clamping the blank by utilizing the two positioning holes and the bottom plane, and performing rough machining and finish machining from the front side of the blank to a designed size to ensure the size requirement of the part;
(6) and (3) rough and finish machining of the other side: clamping after turning over the blank, roughly and finely machining the other side of the part to the designed size, and keeping connecting blocks with the thickness of 0.5mm between the part and the frame body, so as to ensure the size requirement of the part;
(7) trimming: and removing a peripheral frame body (namely blanking) of the part, cutting off a connecting block between the part and the part, removing all burrs after milling, and filing, polishing and milling parts which cannot be reached, wherein all sharp-edge chamfers are R0.5.
The specific processing parameters are as follows:
(1) rough and finish machining one side
Using a machine tool: a three-coordinate low-speed numerical control milling machine;
using a cutter: phi 12R3 solid alloy end mill;
processing parameters are as follows: cutting to the depth of 2mm and the width of 5 mm;
the rotating speed of the machine tool: 1000rpm to 2000 rpm;
cutting speed: 500-1000 mmpm.
(2) Rough and finish machining of the other side
Using a machine tool: a three-coordinate low-speed numerical control milling machine;
using a cutter: phi 12R3 solid alloy end mill;
processing parameters are as follows: cutting to a depth of 1-2 mm and a width of 2-5 mm;
the rotating speed of the machine tool: 1000rpm to 2000 rpm;
cutting speed: 500-1000 mmpm.
The protection scope of the invention is not limited to the technical solutions of the specific examples disclosed in the detailed description section, and all the processing methods for realizing simultaneous processing of a plurality of parts by creating a three-dimensional solid model to improve the processing efficiency of the bracket parts should be considered as the protection scope of the invention.
Claims (4)
1. A machining method for airplane support type parts is characterized by comprising the following steps: the method comprises the following steps:
(1) preparing materials: performing process analysis on parts, determining the number of parts which can be processed by each blank according to the process characteristics of the support parts, the used equipment and the tool, determining the front surface and the back surface which are optimally processed according to the number of parts which can be processed by each blank, and creating a multi-part combined three-dimensional solid model;
(2) processing a positioning reference surface: milling six surfaces of a part blank, ensuring the requirement of flatness, determining a reference surface, and processing the final height of the part in place;
(3) drilling and reaming a process hole: drilling, expanding and reaming 2-phi 18H9 process holes at two ends of the blank;
(4) light splitting and hardness inspection: performing light splitting and hardness inspection to meet the requirements of a drawing;
(5) one surface is rough and fine machined: clamping the blank by utilizing the two holes, namely clamping the blank, and performing rough machining and finish machining on the front side of the blank to ensure the size requirement of the part;
(6) and (3) rough and finish machining of the other side: clamping the blank after turning over, and roughly and finely machining the other side of the part to ensure the size requirement of the part;
(7) trimming: and removing the peripheral frame body of the part, cutting off the connecting blocks between the part and the part, removing all milled burrs, and filing, polishing and milling parts which cannot be milled, wherein all sharp-edge chamfers are R0.5.
2. The method for machining an aircraft support part according to claim 1, wherein the method comprises the following steps: the length and the width of the blank prepared in the step (1) are respectively more than 120mm larger than the three-dimensional solid model of the assembly, and the length and the width are symmetrically distributed on two sides so as to keep a clamping position with a single side not less than 20mm and have enough space for avoiding the diameter of the milling cutter.
3. A method of machining an aircraft support like part according to claim 1 or 2, characterised in that: and (6) when the other surface is processed, keeping the connecting blocks with the thickness of 0.5mm between the parts and the frame body so as to keep the processing rigidity of the parts and avoid milling the parts.
4. The method for machining an aircraft support part according to claim 3, wherein the method comprises the following steps: the step (1) creates a multi-piece combined three-dimensional solid model and keeps the tool to have enough processing space.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911263867.5A CN112935707A (en) | 2019-12-10 | 2019-12-10 | Machining method for airplane support type parts |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911263867.5A CN112935707A (en) | 2019-12-10 | 2019-12-10 | Machining method for airplane support type parts |
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| CN112935707A true CN112935707A (en) | 2021-06-11 |
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| CN201911263867.5A Pending CN112935707A (en) | 2019-12-10 | 2019-12-10 | Machining method for airplane support type parts |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114102068A (en) * | 2021-12-17 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Method and die for machining support arm part with special-shaped structure |
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| US5369870A (en) * | 1990-05-24 | 1994-12-06 | Mitsubishi Denki Kabushiki Kaisha | Method for deciding procedure of machining |
| CN102489950A (en) * | 2011-12-01 | 2012-06-13 | 中国重汽集团济南动力有限公司 | Machining process of automotive front suspension combination bracket assembly |
| JP2012206539A (en) * | 2011-03-29 | 2012-10-25 | Aisin Takaoka Ltd | Method of manufacturing partially heated molded product |
| CN105414903A (en) * | 2015-12-23 | 2016-03-23 | 常熟市淼泉压缩机配件有限公司 | Improved technology for processing small-sized thin plate type part |
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2019
- 2019-12-10 CN CN201911263867.5A patent/CN112935707A/en active Pending
Patent Citations (8)
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| 詹华西等: "综合数控加工及工艺应用", 西安电子科技大学出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114102068A (en) * | 2021-12-17 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Method and die for machining support arm part with special-shaped structure |
| 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 |
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Application publication date: 20210611 |
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