CN112122887B - Method for processing airplane plate rib structural member - Google Patents
Method for processing airplane plate rib structural member Download PDFInfo
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- CN112122887B CN112122887B CN202011009188.8A CN202011009188A CN112122887B CN 112122887 B CN112122887 B CN 112122887B CN 202011009188 A CN202011009188 A CN 202011009188A CN 112122887 B CN112122887 B CN 112122887B
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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
- 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
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Abstract
The invention provides a processing method of an aircraft plate rib structural member, which can be used for conveniently processing the aircraft plate rib structural member with a complex structure and a thin wall, has high processing efficiency, and can also reduce the clamping deformation of parts and ensure the dimensional precision. Which comprises the following steps: blank specification; cutting the shape by wire; roughly milling a back surface molded surface; roughly milling a front profile; stress relief heat treatment; trimming a benchmark; semi-finish milling a front profile; semi-finish milling a back profile; stress relief heat treatment; trimming a benchmark; finely milling a front molded surface; finely milling a back surface molded surface; milling a first process boss and a second process boss; wire cutting; deburring and cleaning the workpiece; and (5) final inspection.
Description
Technical Field
The invention relates to the technical field of casing processing, in particular to a processing method of an airplane plate rib structural member.
Background
In the new generation of aircraft, there are many structural members, most of which are designed to meet functional requirements, have irregular structural shapes, are thin and difficult to machine, and although they do not belong to core components, such structural members also have a crucial influence on the functionality and safety of the aircraft.
Fig. 1 is a schematic diagram of an aircraft reinforcing plate structural member, in which a front surface is provided with a plurality of thin-wall grids, and a back surface is relatively flat, the structure of the structural member is complex, the wall is thin and difficult to machine, a common machining method is difficult to implement, the structural member is easy to deform and unstable in quality due to improper clamping and machining methods in a machining process, so that a machining period is too long, the cost is too high, and the problem becomes a machining problem of the current aircraft structural member.
Disclosure of Invention
The invention provides a processing method of an airplane plate rib structural member, which aims at solving the problems that the structural member is easy to deform and unstable in quality because no proper clamping and processing method is available in the processing of the airplane plate rib structural member with a complex structure and a thin wall.
The technical scheme is as follows: the processing method of the airplane plate rib structural member is characterized by comprising the following steps: step one, blank specification: performing size square calibration on a forging blank;
step two, wire-electrode cutting of the shape: removing partial allowance of the blank profile, and reducing the allowance of rough milling profile removal;
step three, rough milling of the back surface molded surface: roughly milling a back surface profile, keeping a millimeter allowance along the profile, milling n first process bosses on the back surface profile, wherein n is larger than 1, processing and forming threaded holes on each first process boss, wherein the first process bosses are at least positioned on the periphery and the middle of the back surface profile, and processing and forming positioning holes on the m first process bosses, wherein m is larger than 1 and is not larger than n;
step four, rough milling of the front molded surface: fixing a workpiece by using a clamp, wherein the clamp is provided with a threaded hole corresponding to the position of the threaded hole on the back of the workpiece, the clamp is provided with a positioning hole corresponding to the position of the positioning hole on the back of the workpiece, the back of the workpiece is positioned with the clamp through the positioning hole of the first process boss and is fixed with the clamp through the threaded hole of the first process boss, a millimeter allowance is reserved along the front surface by roughly milling the front surface profile, meanwhile, a second process boss corresponding to the position of the first process boss is milled on the front surface profile, the second process boss is provided with the threaded hole, and the corresponding second process boss is provided with the positioning hole;
step five, stress relief heat treatment;
step six, repairing a standard: correcting the flatness of the back surface and the position of the positioning hole;
step seven, semi-finish milling the front molded surface: positioning and fixing a workpiece by matching a clamp and a process boss I, semi-finish milling a front profile of the part, and reserving b mm allowance along the profile, wherein b is less than a;
step eight, semi-finish milling a back surface profile, positioning and fixing a workpiece by matching a clamp and a process boss II, and reserving b mm allowance along the profile for semi-finish milling the back surface profile of the part, wherein b is less than a;
step nine, stress relief heat treatment;
step ten, repairing a standard: correcting the flatness of the back surface and the position of the positioning hole;
step eleven, finish milling the front molded surface: positioning and fixing of the workpiece are realized through the matching of the clamp and the process boss I, and the front profile of the part is finely milled;
step twelve, finish milling the back surface molded surface: positioning and fixing of the workpiece are realized through the matching of the clamp and the process boss II, and the molded surface of the back of the part is finely milled;
step thirteen, milling off a first process boss and a second process boss;
fourteen, wire cutting;
fifteen, deburring and cleaning the workpiece;
sixthly, final inspection.
It is further characterized in that:
the process boss on the front surface of the workpiece is positioned in the workpiece grid;
the positioning holes and the threaded holes on the first process boss and the second process boss are blind holes; the distance between the bottom of the positioning hole on the first process boss and the bottom of the corresponding positioning hole on the second process boss is larger than the thickness of the corresponding position of the workpiece; the distance between the bottom of the threaded hole in the first process boss and the bottom of the corresponding threaded hole in the second process boss is larger than the thickness of the corresponding position of the workpiece.
The invention has the beneficial effects that: the clamping of the workpiece is completed by matching the design process boss with the clamp and tensioning the workpiece on the reverse side, so that the clamping is convenient, the processing time is shortened, meanwhile, the clamping mode reduces the clamping deformation of the part, and the clamp has a simple structure, is convenient to produce and reduces the processing cost; the method adopts rough milling, semi-finish milling and finish milling, and carries out stress relief heat treatment and benchmark correction between the two rough milling and the semi-finish milling and between the semi-finish milling and the finish milling respectively, thereby effectively ensuring the dimensional accuracy of the thin-walled aircraft plate rib structural member.
Drawings
FIG. 1 is a schematic view of an aircraft stud structure;
FIG. 2 is a schematic view of a clamp structure;
FIG. 3 is a schematic front view of a workpiece with a process boss;
FIG. 4 is a schematic view of the back of a workpiece with a process boss;
FIG. 5 is a schematic view of the clamping of the back of the workpiece with the fixture.
Detailed Description
Referring to fig. 1 to 5, a method for processing an aircraft reinforcement structure includes the following steps: step one, blank specification: and (4) performing size specification on the forging blank to ensure that the standard meets the rough machining requirement.
Step two, wire-electrode cutting of the shape: most of allowance of the blank profile is removed through wire cutting, and the allowance of rough milling profile removal is reduced.
Step three, rough milling of the back surface molded surface: roughly milling a back surface profile, reserving 5 mm allowance along the profile, milling 8 process bosses I1 on the back surface profile as positioning support surfaces, processing and forming threaded holes 2 on each process boss I1, wherein the process bosses I1 are at least positioned on the periphery and the middle of the back surface profile, and processing and forming positioning holes 3 on two process bosses I1 which are far away. Because the back of the workpiece is flat, the rough milling back profile can be clamped and processed by a conventional clamp.
Step four, rough milling of the front molded surface: fixing a workpiece by using a clamp shown in FIG. 2 through a bolt, wherein the clamp is provided with a threaded hole 2 corresponding to the threaded hole 2 on the back of the workpiece, the clamp is provided with a positioning hole 3 corresponding to the positioning hole 3 on the back of the workpiece, the back of the workpiece is positioned by using a positioning pin for the clamp through the positioning hole 3 of a first process boss 1, the back of the workpiece is fixed by using the bolt with the clamp through the threaded hole 2 of the first process boss 1, a front face profile is roughly milled, a 5 mm allowance is reserved along the profile, a second process boss 4 corresponding to the position of the first process boss 1 is milled on the front face profile, the second process boss 4 is positioned in a workpiece grid, the second process boss 4 is provided with the threaded hole 2, and the corresponding second process boss 4 is provided with the positioning hole 3.
The positioning holes 3 and the threaded holes 2 on the first process boss 1 and the second process boss 4 are blind holes; the distance between the bottom of the positioning hole 3 on the first process boss 1 and the bottom of the corresponding positioning hole 3 on the second process boss 4 is larger than the thickness of the corresponding position of the workpiece; the distance between the bottom of the threaded hole 2 on the process boss I1 and the bottom of the corresponding threaded hole 2 on the process boss II 4 is larger than the thickness of the corresponding position of the workpiece, so that when the process boss I1 and the process boss II 4 are milled, no hole residue exists on the workpiece; in addition, the clamp can be provided with corresponding avoidance holes 5 according to the shape of the front surface of the workpiece.
And fifthly, stress relief heat treatment.
Step six, repairing a standard: the back flatness and the position of the positioning hole 3 are corrected again to eliminate the influence of stress, and the correction of the positioning hole 3 can be realized by drilling and enlarging the diameter of the hole.
Step seven, semi-finish milling the front molded surface: the fixture is matched with the process boss I1 to realize the positioning and fixing of the workpiece, the front surface of the part is semi-finish milled, and 2 mm allowance is reserved along the surface.
And step eight, semi-finish milling the back surface molded surface, positioning and fixing the workpiece by matching the clamp with the process boss II 4, and semi-finish milling the back surface molded surface of the part, wherein 2 mm allowance is reserved along the molded surface.
And step nine, stress relief heat treatment, and heat treatment again to relieve mechanical stress.
Step ten, repairing a standard: again, the back flatness and the position of the positioning hole 3 are corrected.
Step eleven, finish milling the front molded surface: the fixture is matched with the process boss I1 to realize the positioning and fixing of the workpiece, and the front molded surface of the part is finely milled.
Step twelve, finish milling the back surface molded surface: the fixture is matched with the second process boss 4 to realize the positioning and fixing of the workpiece, and the molded surface of the back of the part is finely milled.
And step thirteen, clamping and milling the process boss I1 and the process boss II 4 by using a conventional clamp.
And step fourteen, wire cutting, wherein the positions which can not be processed are added on the part where the wire cutting is finished.
And fifthly, deburring and cleaning the workpiece.
Sixthly, final inspection is carried out, three-coordinate detection is carried out on the part, and whether the design requirement of the casing is completely met is judged.
The clamping method designed by the invention has universality for the plate rib structural member, is suitable for rough machining, semi-finish machining and finish machining, the process boss is simple and practical in design, the appropriate process bosses are designed on the front and back surfaces of the part respectively, the clamping can be finished at one time during machining, the machining time is shortened, the design and manufacturing cost of the clamp can be saved, and the machining can be finished by one set of clamp. After one-time clamping, the rough machining, semi-finish machining or finish machining process of all molded surfaces of the part can be completed, the clamping deformation of the part is reduced, and the size precision is ensured.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (2)
1. A processing method of an aircraft plate rib structural member is characterized in that the processing method is used for processing the aircraft plate rib structural member with a plurality of thin-wall grids on the front surface and a flat back surface, and comprises the following steps: step one, blank specification: performing size square calibration on a forging blank;
step two, wire-electrode cutting of the shape: removing partial allowance of the blank profile, and reducing the allowance of rough milling profile removal;
step three, rough milling of the back surface molded surface: roughly milling a back surface profile, keeping a millimeter allowance along the profile, milling n first process bosses on the back surface profile, wherein n is larger than 1, processing and forming threaded holes on each first process boss, wherein the first process bosses are at least positioned on the periphery and the middle of the back surface profile, and processing and forming positioning holes on the m first process bosses, wherein m is larger than 1 and is not larger than n;
step four, rough milling of the front molded surface: fixing a workpiece by using a clamp, wherein the clamp is provided with a threaded hole corresponding to the position of the threaded hole on the back of the workpiece, the clamp is provided with a positioning hole corresponding to the position of the positioning hole on the back of the workpiece, the back of the workpiece is positioned with the clamp through the positioning hole of the first process boss and is fixed with the clamp through the threaded hole of the first process boss, a millimeter allowance is reserved along the front surface by roughly milling the front surface profile, meanwhile, a second process boss corresponding to the position of the first process boss is milled on the front surface profile, the second process boss is provided with the threaded hole, and the corresponding second process boss is provided with the positioning hole; the process boss on the front surface of the workpiece is positioned in the workpiece grid;
step five, stress relief heat treatment;
step six, repairing a standard: correcting the flatness of the back surface and the position of the positioning hole;
step seven, semi-finish milling the front molded surface: positioning and fixing a workpiece by matching a clamp and a process boss I, semi-finish milling a front profile of the part, and reserving b mm allowance along the profile, wherein b is less than a;
step eight, semi-finish milling a back surface profile, positioning and fixing a workpiece by matching a clamp and a process boss II, and reserving b mm allowance along the profile for semi-finish milling the back surface profile of the part, wherein b is less than a;
step nine, stress relief heat treatment;
step ten, repairing a standard: correcting the flatness of the back surface and the position of the positioning hole;
step eleven, finish milling the front molded surface: positioning and fixing of the workpiece are realized through the matching of the clamp and the process boss I, and the front profile of the part is finely milled;
step twelve, finish milling the back surface molded surface: positioning and fixing of the workpiece are realized through the matching of the clamp and the process boss II, and the molded surface of the back of the part is finely milled;
step thirteen, milling off a first process boss and a second process boss;
fourteen, wire cutting;
fifteen, deburring and cleaning the workpiece;
sixthly, final inspection.
2. The method for processing the aircraft lath structure according to the claim 1, wherein the method comprises the following steps: the positioning holes and the threaded holes on the first process boss and the second process boss are blind holes; the distance between the bottom of the positioning hole on the first process boss and the bottom of the corresponding positioning hole on the second process boss is larger than the thickness of the corresponding position of the workpiece; the distance between the bottom of the threaded hole in the first process boss and the bottom of the corresponding threaded hole in the second process boss is larger than the thickness of the corresponding position of the workpiece.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011009188.8A CN112122887B (en) | 2020-09-23 | 2020-09-23 | Method for processing airplane plate rib structural member |
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| CN202011009188.8A CN112122887B (en) | 2020-09-23 | 2020-09-23 | Method for processing airplane plate rib structural member |
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| CN112122887A CN112122887A (en) | 2020-12-25 |
| CN112122887B true CN112122887B (en) | 2022-04-29 |
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| CN113070649A (en) * | 2021-05-17 | 2021-07-06 | 哈尔滨汽轮机厂有限责任公司 | Method for processing air inlet fairing of heavy gas turbine compressor |
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| KR101315361B1 (en) * | 2012-05-12 | 2013-10-07 | (주)엠프로텍 | Shaft manufacturing method |
| CN104097033A (en) * | 2014-06-30 | 2014-10-15 | 什邡市明日宇航工业股份有限公司 | Manufacturing process for integral irregular welding box section of advanced training machine |
| CN106312462A (en) * | 2016-11-02 | 2017-01-11 | 贵州航飞精密制造有限公司 | Machining technology of extra-long thin-walled parts |
| CN107717030A (en) * | 2017-11-24 | 2018-02-23 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of processing method of the long boss of Titanium alloy TA15 thin-walled |
| CN110497162A (en) * | 2019-09-23 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of processing method of aero-engine casing |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4659847B2 (en) * | 2008-02-29 | 2011-03-30 | 三菱電機株式会社 | Screw rotor processing method and processing apparatus, and screw compressor manufacturing method |
| CN105252224B (en) * | 2015-11-19 | 2017-09-22 | 华中科技大学无锡研究院 | A kind of aero-engine outer duct outlet guide vanes processing method |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101315361B1 (en) * | 2012-05-12 | 2013-10-07 | (주)엠프로텍 | Shaft manufacturing method |
| CN104097033A (en) * | 2014-06-30 | 2014-10-15 | 什邡市明日宇航工业股份有限公司 | Manufacturing process for integral irregular welding box section of advanced training machine |
| CN106312462A (en) * | 2016-11-02 | 2017-01-11 | 贵州航飞精密制造有限公司 | Machining technology of extra-long thin-walled parts |
| CN107717030A (en) * | 2017-11-24 | 2018-02-23 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of processing method of the long boss of Titanium alloy TA15 thin-walled |
| CN110497162A (en) * | 2019-09-23 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of processing method of aero-engine casing |
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