CN114160851B - Method for processing tail wing framework of aircraft - Google Patents
Method for processing tail wing framework of aircraft Download PDFInfo
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- CN114160851B CN114160851B CN202111661876.7A CN202111661876A CN114160851B CN 114160851 B CN114160851 B CN 114160851B CN 202111661876 A CN202111661876 A CN 202111661876A CN 114160851 B CN114160851 B CN 114160851B
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- rough
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2220/00—Details of milling processes
- B23C2220/60—Roughing
- B23C2220/605—Roughing and finishing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2222/00—Materials of tools or workpieces composed of metals, alloys or metal matrices
- B23C2222/88—Titanium
Abstract
The invention discloses a processing method of an aircraft tail wing framework. The method is suitable for the technical field of aircrafts, and comprises the steps of marking a allowance line on a blank of a tail wing framework, arranging a plurality of process bosses on the blank, milling two opposite reference surfaces of each process boss according to the allowance line, then finishing the reference surfaces, respectively corresponding the two reference surfaces of each process boss to the two wing surfaces of the blank, determining theoretical center surfaces of the two wing surfaces of the blank by the reference surfaces, combining the allowance line, roughly processing the blank to form a rough workpiece, determining that the theoretical center surfaces are perpendicular to the bottom surface of the rough workpiece by the reference surfaces, finely processing the rough workpiece to form a fine workpiece, and removing all the process bosses. The invention reasonably designs the processing procedure, particularly adopts the reference surface of the process boss for positioning, and improves the processing effect and the quality stability of the parts.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a processing method of an aircraft tail wing framework.
Background
The fin is an important structural member of an aircraft, and mainly plays a role in balance, the skeleton is used as a base member of the fin, the skeleton is formed by precisely casting titanium alloy ZTA15 graphite, the shape of the fin is of a T-shaped large-scale grid-shaped thin-wall structure, the product precision requirement is high, the cast titanium alloy ZTA15 is high in material strength and hardness and low in thermal conductivity, cutting heat generated in the processing process is not easy to dissipate, the residual stress of raw materials is large, deformation is easy to generate in the processing process, meanwhile, the structural member is of a grid-shaped thin-wall structure, a knife-shaking phenomenon is easy to generate in the processing process of the structure, and great difficulties exist in the processing process of the structure.
The existing machining is to mill after leveling airfoil surfaces are aligned by designing an inclined surface tool, then select a rod milling cutter suitable for cutting titanium alloy to directly mill, the quality stability of parts machined by the method is poor, products are easy to deform, in addition, a cutter is easy to shake and even break when the rod milling cutter mills, the cutter cost is high, the surface quality is poor, and the overall performance of the products is finally affected.
Disclosure of Invention
The invention aims to at least solve the technical problem that the existing method for processing the tail wing skeleton of the aircraft is poor in effect to a certain extent. Therefore, the invention provides a processing method of the tail wing framework of the aircraft.
The technical scheme of the invention is as follows:
the invention provides a processing method of an aircraft tail wing framework, which comprises the following steps:
marking a allowance line on a blank piece of the tail wing framework with a plurality of process bosses;
milling two opposite reference surfaces of each process boss according to the allowance lines, and then finishing the reference surfaces, wherein the two reference surfaces of each process boss correspond to two wing surfaces of the blank;
determining theoretical center planes of the two airfoil surfaces of the blank member with the reference plane, and roughing the blank member to form the rough member in combination with the margin line;
determining that the theoretical center plane is perpendicular to the bottom surface of the rough workpiece through the reference plane, and finishing the rough workpiece to form a finished workpiece;
and removing a plurality of process bosses.
Further, the flatness and parallelism of the reference surface are not more than 0.05.
Further, the roughing the blank to form the roughing member includes: the base of the blank is roughly machined, the base of the blank comprises a rough machining R arc surface and a rough machining base which are upwards and downwards sunken, and cutters adopted by the rough machining R arc surface and the rough machining base which are upwards and downwards sunken are respectively
Vibration-damping square shoulder milling cutter.
Further, the rough machining of the blank to form the rough machined part further comprises rough machining airfoils and rough machining airfoil sagging, wherein cutters adopted by the rough machining airfoils and the rough machining airfoil sagging are all as follows
Vibration-damping square shoulder milling cutter.
Further, milling parameters of the rough machining R arc surface, the rough machining base sinking upwards and downwards, the rough machining airfoil surface and the rough machining airfoil surface sinking are all 1mm in balance, the rotating speed is 1000R/min, the cutting depth is 2mm, and the feeding amount is 150mm/min.
Further, the finishing the rough workpiece to form a finished workpiece includes: the finish machining base is sunk upwards, and a cutter adopted by the finish machining base for sinking upwards is a cutter formed by combining a D16 cylindrical straight shank connecting rod, a square shoulder milling cutter and a cutter blade.
Further, the finishing the rough workpiece to form a finished workpiece further includes: and the cutter adopted by the finish machining airfoil surface is a cutter formed by combining the D16 cylindrical straight shank connecting rod, the square shoulder milling cutter and the blade.
Further, the finishing the rough workpiece to form a finished workpiece further includes: the method comprises the following steps of sinking a finish machining airfoil, wherein a cutter adopted by sinking the finish machining airfoil is a cutter formed by combining a D10 cylindrical straight shank connecting rod, a square shoulder milling cutter and a blade.
Further, milling parameters of the upper sinking of the finish machining base, the finish machining airfoil and the sinking of the finish machining airfoil are all 0mm in balance, 600r/min in rotating speed, 0.3mm in cutting depth and 50-100 mm/min in feeding amount.
Further, the finishing the rough workpiece to form a finished workpiece further includes: finish machining the R arc surface, wherein a cutter adopted by the finish machining of the R arc surface is
Integral cemented carbide profiling milling ball head cutting head.
The embodiment of the invention has at least the following beneficial effects:
the processing method of the aircraft tail wing skeleton provided by the invention adopts the working procedures of allowance line marking, processing of the process boss, rough blank processing, rough workpiece finishing, removing of the process boss and the like, reasonably designs the processing working procedures, particularly adopts the reference surface of the process boss for positioning, and improves the processing effect and the quality stability of parts.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the structure of an aircraft tail skeleton according to an embodiment of the present invention;
FIG. 2 is a schematic view of the mounting of a process boss on a blank according to an embodiment of the present invention;
fig. 3 is a schematic flow chart of a method for processing an aircraft tail skeleton according to an embodiment of the present invention.
Reference numerals:
1-an airfoil; 2-a base; 3-process boss.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Furthermore, the present invention may repeat reference numerals and/or letters in the various examples, which are for the purpose of brevity and clarity, and which do not themselves indicate the relationship between the various embodiments and/or arrangements discussed. In addition, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the application of other processes and/or the use of other materials.
The invention is described below with reference to specific embodiments in conjunction with the accompanying drawings:
fig. 1 is a tail framework of an aircraft according to an embodiment of the present invention, and in combination with fig. 1, the tail framework includes an airfoil 1 and a base 2, the airfoil 1 is disposed on opposite sides of the tail framework, and the base 2 is disposed at the bottom of the tail framework.
The processing method of the tail wing framework of the aircraft provided by the embodiment of the invention comprises the following steps: .
S1: marking allowance lines on a blank piece of the tail wing framework with a plurality of process bosses 3;
s2: milling two opposite reference surfaces of each process boss 3 according to the allowance lines, and then finishing the reference surfaces, wherein the two reference surfaces of each process boss 3 respectively correspond to the two airfoil surfaces 1 of the blank;
s3: determining theoretical central planes of two airfoil surfaces 1 of the blank by using a reference plane, and rough machining the blank by combining a margin line to form a rough machined part;
s4: determining that the theoretical center plane is perpendicular to the bottom surface of the rough workpiece through the reference plane, and finishing the rough workpiece to form a finished workpiece;
s5: the plurality of process bosses 3 are removed.
The processing procedure has reasonable design, and particularly, the reference surface of the process boss 3 is adopted for positioning, so that the processing effect and the quality stability of the tail wing framework can be improved.
Fig. 2 is a schematic view of the installation of the process bosses 3 on the blank, and in combination with fig. 2, the installation schematic view includes an airfoil 1, a base 2 and the process bosses 3, wherein 6 process bosses 3 are provided in total, 2 process bosses 3 are arranged at intervals on the top of the blank, 1 process boss 3 is arranged at one side of the blank, 3 process bosses 3 are arranged at intervals on the bottom of the blank, and of course, the process bosses 3 can also have other arrangement numbers and modes, so long as the required positioning is satisfied, and the embodiment of the invention is not limited thereto.
In the embodiment of the invention, the flatness and parallelism of the reference surface are not more than 0.05 so as to meet the perpendicularity requirement of the theoretical center surface and the bottom surface of the base 2.
Steps of embodiments of the inventionIn step S3, in the step of performing the rough machining on the blank, the base 2 of the rough machining blank, the rough machining airfoil 1 and the rough machining airfoil dip are included, wherein in the base 2 of the rough machining blank, the tools adopted for the rough machining of the R arc surface and the rough machining base dip are
Vibration-damping square shoulder milling cutter, rough machining airfoil 1 and cutter for sinking rough machining airfoil are all +.>
Vibration-damping square shoulder milling cutter.
Preferably, milling parameters of the rough machining R arc surface, the rough machining base upper sinking, the rough machining airfoil surface 1 and the rough machining airfoil surface sinking are all 1mm, the rotating speed is 1000R/min, the cutting depth is 2mm, and the feeding amount is 150mm/min.
The rough machining of the tail wing framework of the aircraft is realized through the specific procedures.
In step S4 of the embodiment of the present invention, when the rough machined piece is finished to form the finished machined piece, the tool must be selected from a tool structure and a material with good red hardness, high bending strength, good heat conductivity, good anti-adhesion, anti-diffusion, anti-oxidation wear performance, and good vibration resistance, and because the aspect ratio of the machining depth of the part and the diameter of the tool is greater than 4×d, vibration is more serious in the machining process, so that the tool is easy to collapse, the side wall of the internal cavity groove is very thin, the part is easy to deform during machining, and a combined tool of the cemented carbide tool bar, the square shoulder milling cutter and the blade is adopted.
Specifically, in the process of finishing a rough workpiece, the method comprises the steps of finishing the upper dip of a base, finishing the airfoil surface 1, finishing the airfoil surface dip and finishing the R arc surface, wherein a cutter adopted by the upper dip of the finishing base is a cutter formed by combining a D16 cylindrical straight shank connecting rod, a square shoulder milling cutter and a blade, a cutter adopted by the finishing airfoil surface 1 is a cutter formed by combining a D16 cylindrical straight shank connecting rod, a square shoulder milling cutter and a blade, and a cutter adopted by the sinking of the finishing airfoil surfaceThe cutter which is composed of a D10 cylindrical straight shank extension rod, a square shoulder milling cutter and a blade combination is adopted for finishing the R arc surface, and is
Integral cemented carbide profiling milling ball head cutting head.
Preferably, milling parameters of the upper sinking of the finishing base, the finishing wing 1 and the sinking of the finishing wing surface are all 0mm, the rotating speed is 600r/min, the cutting depth is 0.3mm, and the feeding amount is 50-100 mm/min.
The fine machining of the tail wing framework of the aircraft is realized through the specific working procedures.
In the embodiment of the invention, the tail fin framework is formed by precisely casting titanium alloy ZTA15 graphite, wherein pollution and biting welding tendency exist between titanium and a cutter, and the milling of the titanium is more difficult than the turning. The damage of chip burrs generated by the machining front edge to the milling cutter can be reduced to the greatest extent by adopting the forward milling.
After step S5 of the embodiment of the present invention, the finishing work piece is further subjected to working procedures such as trimming and cutting table, deburring, tapping, etc.
In the embodiment of the present invention, the process boss 3 may be welded on the blank, or the process boss 3 may be cast together with the blank when the blank is cast, which is not limited in the embodiment of the present invention.
The processing method of the aircraft tail wing skeleton provided by the invention adopts the working procedures of allowance line marking, processing of the process boss, rough blank processing, rough workpiece finishing, removing of the process boss and the like, reasonably designs the processing working procedures, particularly adopts the reference surface of the process boss for positioning, and improves the processing effect and the quality stability of parts.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" indicate orientations or positional relationships are based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
It should be noted that all the directional indicators in the embodiments of the present invention are only used to explain the relative positional relationship, movement conditions, etc. between the components in a specific posture, and if the specific posture is changed, the directional indicators are correspondingly changed.
In the present invention, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Further, one skilled in the art can engage and combine the different embodiments or examples described in this specification.
In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present invention.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. A method of machining an aircraft tail skeleton, the method comprising:
setting 6 process bosses on a blank of a tail wing framework, wherein 2 process bosses are arranged at the top of the blank at intervals, 1 process boss is arranged at one side of the blank, 3 process bosses are arranged at the bottom of the blank at intervals, and marking allowance lines on the blank with 6 process bosses;
milling two opposite reference surfaces of each process boss according to the allowance lines, and then finishing the reference surfaces, wherein the two reference surfaces of each process boss correspond to two wing surfaces of the blank;
determining theoretical center planes of the two airfoil surfaces of the blank with the reference plane, and rough machining the blank to form a rough workpiece in combination with the margin line;
determining that the theoretical center plane is perpendicular to the bottom surface of the rough workpiece through the reference plane, and finishing the rough workpiece to form a finished workpiece;
and 6 process bosses are removed.
2. The method of claim 1, wherein the reference surface has a flatness and parallelism of no greater than 0.05.
3. The method of claim 1, wherein the roughing the blank to form the roughed part comprises: the method comprises the steps of rough machining a base of a blank, wherein the base of the blank comprises a rough machining R arc surface and a rough machining base which is sunken upwards, and cutters adopted for the rough machining R arc surface and the rough machining base which are sunken upwards are phi 25 vibration reduction square shoulder milling cutters.
4. A method of machining an aircraft tail skeleton according to claim 3, wherein the roughing the blank to form the roughing piece further comprises roughing an airfoil and roughing an airfoil dip, the roughing and roughing airfoil dip using a tool that is the phi 25 vibration-reducing square shoulder cutter.
5. The method of claim 4, wherein milling parameters of the rough R arc surface, the rough base dip, the rough airfoil surface and the rough airfoil surface dip are all 1mm, the rotation speed is 1000R/min, the cutting depth is 2mm, and the feed rate is 150mm/min.
6. The method of machining an aircraft tail skeleton of claim 1, wherein the finishing the rough work piece to form a finished work piece comprises: the finish machining base is sunk upwards, and a cutter adopted by the finish machining base for sinking upwards is a cutter formed by combining a D16 cylindrical straight shank connecting rod, a square shoulder milling cutter and a cutter blade.
7. The method of machining an aircraft tail skeleton according to claim 6, wherein the finishing the rough work piece to form a finished work piece further comprises: and the cutter adopted by the finish machining airfoil surface is a cutter formed by combining the D16 cylindrical straight shank connecting rod, the square shoulder milling cutter and the blade.
8. The method of machining an aircraft tail skeleton according to claim 7, wherein the finishing the rough work piece to form a finished work piece further comprises: the method comprises the following steps of sinking a finish machining airfoil, wherein a cutter adopted by sinking the finish machining airfoil is a cutter formed by combining a D10 cylindrical straight shank connecting rod, a square shoulder milling cutter and a blade.
9. The method for machining an aircraft tail skeleton according to claim 8, wherein milling parameters of the upper dip of the finishing base, the finishing airfoil and the dip of the finishing airfoil are all 0mm in balance, 600r/min in rotation speed, 0.3mm in cutting depth and 50-100 mm/min in feeding amount.
10. The method of machining an aircraft tail skeleton according to claim 9, wherein the finishing the rough work piece to form a finished work piece further comprises: and (3) finishing the R arc surface, wherein a cutter adopted for finishing the R arc surface is a phi 6 integral hard alloy profiling milling ball head cutting head.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111661876.7A CN114160851B (en) | 2021-12-30 | 2021-12-30 | Method for processing tail wing framework of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111661876.7A CN114160851B (en) | 2021-12-30 | 2021-12-30 | Method for processing tail wing framework of aircraft |
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| CN114160851A CN114160851A (en) | 2022-03-11 |
| CN114160851B true CN114160851B (en) | 2023-05-16 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9033670B2 (en) * | 2012-04-11 | 2015-05-19 | Honeywell International Inc. | Axially-split radial turbines and methods for the manufacture thereof |
| CN103639655B (en) * | 2013-11-28 | 2016-08-17 | 江西洪都航空工业集团有限责任公司 | A kind of manufacturing process of high-curvature full-profile thin-wall part |
| CN106624632B (en) * | 2016-12-06 | 2018-12-28 | 上海航天精密机械研究所 | The slim polyhedron rudder skeleton of titanium alloy and its processing method |
| CN107695628B (en) * | 2017-10-12 | 2023-10-31 | 西安北方光电科技防务有限公司 | Processing method for deformed bracket part made of aluminum alloy material |
| CN113001125A (en) * | 2021-03-19 | 2021-06-22 | 沈阳万事达机械有限公司 | Process flow of empennage framework |
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