CN109332999B - Method for controlling deformation of left wing and right wing of blowing model - Google Patents
Method for controlling deformation of left wing and right wing of blowing model Download PDFInfo
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- CN109332999B CN109332999B CN201811117139.9A CN201811117139A CN109332999B CN 109332999 B CN109332999 B CN 109332999B CN 201811117139 A CN201811117139 A CN 201811117139A CN 109332999 B CN109332999 B CN 109332999B
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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
Abstract
The invention discloses a method for controlling deformation of left and right wings of a blowing model, which comprises the following steps of (a) processing semi-finished wings according to rough machining allowance; reserving a plurality of first process heads on a first airfoil surface of the semi-finished product of the wing, and reserving a second process head on the connecting end of the semi-finished product of the wing; reserving a plurality of third process heads on the second wing surface of the semi-finished wing, and processing pressure relief holes on the second process heads; reheating treatment, namely putting the semi-finished product in cooling liquid to enable the first airfoil surface of the semi-finished product of the wing to be parallel to the vertical direction, and cooling the semi-finished product in the cooling liquid; (b) according to the semi-finishing allowance, respectively semi-finishing a first airfoil surface and a second airfoil surface of the wing; (c) fine processing; (d) and removing the first process head, the third process head and the second process head at the connecting end of the wing semi-finished product after finish machining to obtain a wing finished product. The deformation in the processing process is controlled, and repeated reshaping semi-finished wings and repeated visible light reference are avoided.
Description
Technical Field
The invention belongs to the technical field of machining, and particularly relates to a method for controlling deformation of left and right wings of a blowing model.
Background
The left wing and the right wing of the blowing model are usually finished by processing a whole plate by machine milling, turning, cutting and the like. In the existing wing model processing technology, in the processes of rough processing and semi-finish processing, the wing has larger deformation and exceeds the requirement of the wing processing size, and because the processing precision requirement of the wing model is higher, in order to ensure the final quality and technical requirement, the repeated semi-finish processing needs to be carried out in the processing process, the repeated correction and visible light reference are passed, so that the processing period of the wing model is long, and the product quality is not easy to control because the deformation is large in each processing.
Disclosure of Invention
The invention aims to: the method for controlling the deformation of the left wing and the right wing of the blowing model solves the defects in the prior art, and the method for processing the wing model can reduce the deformation of the wings in the processing process, save the processing procedures and shorten the processing period of the wing model.
In order to achieve the purpose, the invention adopts the technical scheme that: a method for controlling the deformation of left and right wings of a blowing model comprises the following steps,
(a) rough machining: fixing the plate on a machine tool, and processing a semi-finished product of the wing according to the rough machining allowance; the semi-finished product of the wing is provided with a first wing surface, a second wing surface and a plurality of side surfaces for connecting the first wing surface and the second wing surface, wherein one side surface is a connecting end of the wing and the fuselage; reserving a plurality of first process heads on a first airfoil surface of the semi-finished wing product, and reserving a second process head on the connecting end of the semi-finished wing product; reserving a plurality of third process heads on the second wing surface of the semi-finished wing, and processing pressure relief holes on the second process heads; then carrying out heat treatment on the semi-finished product of the wing, putting the semi-finished product of the wing after heat treatment into cooling liquid, enabling a first wing surface of the semi-finished product of the wing to be parallel to the vertical direction, and cooling in the cooling liquid;
(b) semi-finishing: fixing the semi-finished product of the wing processed in the step (a) on a machine tool, and respectively semi-finishing a first wing surface and a second wing surface of the wing according to semi-finishing allowance; aging the semi-finished wing semi-finished product;
(c) finish machining: fixing the wing semi-finished product subjected to the aging treatment in the step (b) on a machine tool, and respectively finishing the first wing surface and the second wing surface to relevant process standards;
(d) and (c) fixing the semi-finished product of the wing after the fine machining in the step (c) on a machine tool, removing the first process head positioned on the first wing surface, removing the third process head positioned on the second wing surface, and finally removing the second process head positioned on the connecting end to obtain a finished product of the wing.
In the existing wing machining process, two wing surfaces are machined firstly in a rough machining process, the side face connecting the two wing surfaces is not machined, and a plate connected between the two wing surfaces is taken as an integral process head. In the machining process, redundant plates are removed during rough machining, the side faces are machined, and only the first process head and the second process head which are independent are reserved on the two airfoil surfaces. The first process head and the second process head which are independent from each other enable the deformation amount of the wing semi-finished product during fine processing to be reduced, and due to the fact that the number of the process heads is reduced, when the wing semi-finished product is fixed on a machine tool, the fixing procedures are correspondingly reduced, and the process flow is shortened.
Further, in the step (a), the rough machining allowance is 2-8 mm.
Further, in the step (b), the semi-finishing allowance is 0.1-0.5 mm.
Further, in the step (a), the number of the first process heads is the same as that of the third process heads, and the first process heads and the third process heads are symmetrically arranged.
Further, the number of the first process heads is 5-7.
Further, when the length of the finished wing product is 50cm-100cm, the rough machining allowance is 2mm-5mm, the semi-finishing allowance is 0.1-0.2mm, the number of the first process heads is 5, and the number of the third process heads is 5.
Further, when the length of the finished wing product is 100cm-200cm, the rough machining allowance is 5mm-8mm, the semi-finishing allowance is 0.2mm-0.5mm, the number of the first process heads is 7, and the number of the third process heads is 7.
The number of the first process heads is determined according to the size of the finished product of the wing, when the size is increased, the number of the process heads is increased, and the first process heads can be placed in the machining process, so that the semi-finished product of the wing deforms.
Furthermore, the second process head is provided with a first arm and a second arm which are perpendicular to each other, the first arm and the second arm are respectively connected with the connecting end of the semi-finished wing product, and the pressure relief hole is formed among the first arm, the second arm and the connecting end of the semi-finished wing product. The cross section of the pressure relief hole on a plane parallel to the first airfoil surface is in the shape of a right triangle.
Furthermore, the first airfoil of the semi-finished wing product is provided with a first edge, a second edge, a third edge and a fourth edge which are sequentially connected, the connecting end is located on the first edge, the first process heads are located on the second edge and the fourth edge respectively, and the third process heads located on the second airfoil are symmetrically arranged with the first process heads.
Due to the adoption of the technical scheme, the invention has the beneficial effects that:
according to the invention, a plate is firstly subjected to rough machining, a first airfoil surface and a second airfoil surface are machined on the plate, a plurality of side surfaces for connecting the first airfoil surface and the second airfoil surface are connected, a first process head and a third process head which are mutually independent are reserved on the airfoil surfaces, a second process head is reserved on a connecting end, a pressure relief hole is machined on the second process head, the wings are cooled in the rough machining, semi-finish machining and finish machining processes in a vertical placement mode, after finish machining, the first process head and the third process head are removed, and after the second process head is removed, as the pressure relief hole is also machined on the second process head, when the first process head and the third process head are removed, the pressure relief hole can absorb machining stress, so that the machining deformation of the wings is reduced. In the semi-finishing and finishing processes, the processing stress on the semi-finished product of the wing can be released through the pressure relief hole, so that the deformation of the semi-finished product of the wing is further reduced; because the deformation of the semi-finished product of the wing is small in the later processing process, the processing requirement can be met under fewer processing procedures, and the processing procedures of the wing model are saved. Because only one side of the semi-finished product of the wing is provided with the process head, the semi-finished product of the wing can be prevented from being distorted and deformed in the semi-finishing and finishing processes, the clamping times in the processing process are reduced, and the processing time is saved.
In the invention, when the semi-finished product of the wing is cooled, the semi-finished product of the wing is vertically placed in the cooling liquid, so that the deformation of the semi-finished product of the wing in the cooling process can be effectively reduced. The placing mode in the cooling process, the machining process for removing the process head on one side of the semi-finished product of the wing and the mutual matching of the pressure relief holes enable the deformation of the wing model to be greatly reduced in the machining process, and machining procedures to be saved.
Compared with the processing procedures in the prior art, the method disclosed by the invention has the advantages that the deformation in the processing process is controlled, repeated shape-righting wing semi-finished products and repeated visible light reference are avoided, the operation difficulty in the processing process is reduced, and the processing time cost and the economic cost are reduced.
Drawings
FIG. 1 is a schematic view of a semi-finished airfoil in the process of the present invention
Reference numerals: 1-semi-finished wing, 11-first wing surface, 111-first edge, 112-second edge, 113-third edge, 114-fourth edge, 12-second wing surface, 13-connecting end, 2-first process head, 3-second process head, 31-first arm, 32-second arm, 4-third process head and 5-pressure relief hole.
Detailed Description
Embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Example 1: processing wing model with length of 80cm
(a) Rough machining: processing a semi-finished product 1 of the wing according to the rough machining allowance of 2 mm; semi-manufactured goods 1 of wing has relative first airfoil 11, second airfoil 12 and connects a plurality of sides of first airfoil 11 and second airfoil 12, first airfoil 11 and second airfoil 12 are the biggest two faces of area on the semi-manufactured goods 1 of wing to first airfoil 11 and second airfoil 12 are in relative position, and link 13 is the side end of semi-manufactured goods 1 of wing, is equipped with the connector that is used for connecting wing and fuselage at this link 13. The specific way of processing the semi-finished product 1 of the wing is as follows: firstly, fixedly jacking a plate on a machine tool, reserving 5 mutually independent first process heads 2 on a first airfoil 11 of a semi-finished wing 1 while processing one surface of the plate by a milling cutter, wherein the position of the first process head 2 is the position of fixedly jacking the plate on the machine tool; reserving a second process head 3 at the connecting end 13 of the wing semi-finished product 1; the thickness of the second process head 3 is the same as that of the plate; after the rough machining of the first airfoil 11 of the semi-finished product 1 of the wing is finished, a second airfoil 12 of the semi-finished product 1 of the wing is machined on the other surface of the plate, the machining allowance of the second airfoil is 2mm, 5 third process heads 4 are reserved on the second airfoil 12 during machining, pressure relief holes 5 are machined in the second process heads 3 during machining of the second airfoil 12, the depth of the pressure relief holes 5 is the same as the thickness of the plate, finally, redundant plates on the side surfaces are removed, the side surfaces of the wing are milled, and the semi-finished product 1 of the wing is finally obtained; carrying out heat treatment on the obtained semi-finished product 1 of the wing, wherein the heat treatment temperature is higher than 700 ℃, placing the semi-finished product 1 of the wing after heat treatment in a cooling tank filled with cooling water, and enabling a first wing surface 11 of the semi-finished product 1 of the wing to be parallel to the vertical direction during placement, namely enabling the width direction of an original plate to be parallel to the vertical direction, enabling the semi-finished product 1 of the wing to be vertically placed in the cooling tank, and cooling the semi-finished product 1 of the wing in the cooling water at normal temperature;
(b) semi-finishing: fixing the cooled semi-finished product 1 of the wing on a machine tool, respectively semi-finishing a first wing surface 11 and a second wing surface 12 of the wing according to a semi-finishing allowance of 0.2mm, and placing the semi-finished product 1 of the wing at room temperature for 3 days for aging treatment;
(c) finish machining: fixing the wing semi-finished product 1 subjected to the failure treatment in the step (b) on a machine tool, and respectively performing finish machining on a first wing surface 11 and a second wing surface 12 until the requirement on the machining of the wing surfaces is met;
(d) and fixing the semi-finished product of the wing which is finished to reach the standard on a machine tool, firstly removing the first process head 2 positioned on the first airfoil 11, then removing the third process head 4 positioned on the second airfoil 12, and finally removing the second process head 3 positioned on the connecting end 13 to obtain the finished product of the wing.
Because in the rough machining process, the thickness of panel is thicker when beginning to add man-hour, can absorb the stress that processing produced, along with processing is constantly gone on, the same absorbable machining stress of the same of more rough machining surplus that reserves reduces the deflection in the rough machining process, and after pressure release hole 5 processing was accomplished, at semi-finishing and finish machining in-process, pressure release hole 5 can absorb machining stress, reduces the deflection of wing semi-manufactured goods 1. When the deformation in the machining process is reduced, the corresponding machining precision is easier to obtain, and the machining procedures are reduced.
It should be noted that the length of the wing model in this embodiment refers to the longest dimension of the wing model.
In other embodiments of the present invention, in step (d), the third process head 4 may be removed first, and then the first process head 2 may be removed.
Example 2: processing wing model with length of 110cm
The present embodiment is different from the embodiment in that, in the present embodiment, the rough machining allowance is 6mm, the semi-finishing allowance is further 0.5mm, and the number of the first process head 2 and the second process head 3 is 7.
Example 3: on the basis of this embodiment 1, in this embodiment, the second process head 3 has a first arm 31 and a second arm 32 that are perpendicular to each other, the first arm 31 is a wide side of the original plate, the second side 112 is a long side of the original plate, the first arm 31 and the second arm 32 are respectively connected to the connection end 13 of the wing semi-finished product 1, and the pressure relief hole 5 is formed between the first arm 31, the second arm 32 and the connection end 13 of the wing semi-finished product 1. The cross-sectional shape of the pressure relief hole 5 in a plane parallel to the first airfoil 11 is a right triangle.
The first airfoil 11 of the wing semi-finished product 1 has a first edge 111, a second edge 112, a third edge 113 and a fourth edge 114 connected in sequence, the connecting end 13 is located on the first edge 111, the first craft heads 2 are respectively located on the second edge 112 and the fourth edge 114, that is, 2 first craft heads 2 are located on the second edge 112, and 3 first craft heads 2 are located on the fourth edge 114, as shown in the attached drawings. And 5 at the second airfoil surface 12 the third technology head 4 is arranged symmetrically to the 5 first technology heads 2 arranged on the first airfoil surface 11.
The control method of the invention is used for processing the wing model, controlling the deformation in the processing process, avoiding repeated reshaping of the semi-finished product of the wing and repeated visible light reference, reducing the operation difficulty in the processing process and reducing the time cost and the economic cost of processing.
Claims (10)
1. A method for controlling deformation of left and right wings of a blowing model is characterized in that: comprises the following steps of (a) carrying out,
(a) rough machining: fixing the plate on a machine tool, and processing a semi-finished product (1) of the wing according to the rough machining allowance; the semi-finished wing (1) is provided with a first wing surface (11), a second wing surface (12) and a plurality of side surfaces for connecting the first wing surface (11) and the second wing surface (12), wherein one side surface is a connecting end (13) of the wing and the fuselage; a plurality of first process heads (2) are reserved on a first airfoil (11) of the semi-finished wing (1), and a second process head (3) is reserved on a connecting end (13) of the semi-finished wing (1); reserving a plurality of third process heads (4) on a second airfoil surface (12) of the semi-finished wing (1), and processing pressure relief holes (5) on the second process heads (3); then carrying out heat treatment on the semi-finished product (1) of the wing, placing the semi-finished product (1) of the wing after heat treatment in cooling liquid, enabling a first wing surface (11) of the semi-finished product (1) of the wing to be parallel to the vertical direction, and cooling in the cooling liquid;
(b) semi-finishing: fixing the wing semi-finished product (1) processed in the step (a) on a machine tool, and respectively semi-finishing a first wing surface (11) and a second wing surface (12) of the wing according to semi-finishing allowance; aging the semi-finished wing semi-finished product (1);
(c) finish machining: fixing the wing semi-finished product (1) subjected to the aging treatment in the step (b) on a machine tool, and respectively finishing a first wing surface (11) and a second wing surface (12);
(d) and (c) fixing the semi-finished product (1) of the wing after finish machining in the step (c) on a machine tool, firstly removing the first process head (2) positioned on the first wing surface (11), then removing the third process head (4) positioned on the second wing surface (12), and finally removing the second process head (3) positioned on the connecting end (13) to obtain a finished product of the wing.
2. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 1, wherein: in the step (a), the rough machining allowance is 2-8 mm.
3. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 1, wherein: in the step (b), the semi-finishing allowance is 0.1-0.5 mm.
4. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 1, wherein: in the step (a), the number of the first process heads (2) is the same as that of the third process heads (4), and the first process heads (2) and the third process heads (4) are symmetrically arranged.
5. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 4, wherein: the number of the first process heads (2) is 5-7.
6. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 1, wherein: when the length of the wing finished product is 50cm-100cm, the rough machining allowance is 2mm-5mm, the semi-finishing allowance is 0.1-0.2mm, the number of the first process heads (2) is 5, and the number of the third process heads (4) is 5.
7. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 1, wherein: when the length of the finished wing product is 100-200 cm, the rough machining allowance is 5-8 mm, the semi-finishing allowance is 0.2-0.5 mm, the number of the first process heads (2) is 7, and the number of the third process heads (4) is 7.
8. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 1, wherein: the second process head (3) is provided with a first arm (31) and a second arm (32) which are perpendicular to each other, the first arm (31) and the second arm (32) are respectively connected with a connecting end (13) of the semi-finished wing product (1), and the pressure relief hole (5) is formed among the first arm (31), the second arm (32) and the connecting end (13) of the semi-finished wing product (1).
9. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 8, wherein: the cross section of the pressure relief hole (5) on a plane parallel to the first airfoil surface (11) is in the shape of a right triangle.
10. The method for controlling the deformation of the left wing and the right wing of the blowing model according to claim 8, wherein: first airfoil (11) of wing semi-manufactured goods (1) have consecutive first limit (111), second limit (112), third limit (113) and fourth edge (114), link (13) are located first limit (111), it is a plurality of first technology head (2) are located respectively second limit (112) with fourth edge (114), are located a plurality of second airfoil (12) third technology head (4) with first technology head (2) symmetry sets up.
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111251021B (en) * | 2020-03-05 | 2021-11-30 | 成都飞机工业（集团）有限责任公司 | Dislocation connection process boss tool and workpiece machining method |
| CN111872722B (en) * | 2020-07-27 | 2022-06-17 | 成都凯迪精工科技有限责任公司 | Method for removing auxiliary process head arranged on molded surface |
| CN111872641A (en) * | 2020-07-31 | 2020-11-03 | 成都凯迪精工科技有限责任公司 | Machining method for solving wing deformation |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6098260A (en) * | 1996-12-13 | 2000-08-08 | Mcdonnell Douglas Corporation | Rivet fastening system for radial fuselage joints |
| CN103551816A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method for controlling processing deformation of titanium-aluminum alloy thin-wall case |
| CN103639655A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Manufacturing process for high-curvature full-profile thin-wall part |
| CN104015015A (en) * | 2014-06-23 | 2014-09-03 | 什邡市明日宇航工业股份有限公司 | Numerical control integrated manufacturing technology for parts of outer barrel of main landing gear of airplane |
| 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 |
| CN104259774A (en) * | 2014-09-09 | 2015-01-07 | 黄河科技学院 | Plane wing titanium alloy thin-wall web efficient numerical control machining technology |
| CN104889462A (en) * | 2015-06-17 | 2015-09-09 | 沈阳飞机工业（集团）有限公司 | Method for reducing deformation of numerical control machining plate type titanium alloy parts |
| CN105328411A (en) * | 2015-11-06 | 2016-02-17 | 西北工业大学明德学院 | Numerical control machining method of airplane model |
| CN106399882A (en) * | 2016-11-30 | 2017-02-15 | 中国直升机设计研究所 | Heat treatment method for machining deformation prevention of 7055 aluminium alloy thin-walled structure |
| CN107052715A (en) * | 2017-03-30 | 2017-08-18 | 陕西飞机工业（集团）有限公司 | A kind of large-scale Integral Wing Panel numerical-control processing method |
-
2018
- 2018-09-25 CN CN201811117139.9A patent/CN109332999B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6098260A (en) * | 1996-12-13 | 2000-08-08 | Mcdonnell Douglas Corporation | Rivet fastening system for radial fuselage joints |
| CN103551816A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method for controlling processing deformation of titanium-aluminum alloy thin-wall case |
| CN103639655A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Manufacturing process for high-curvature full-profile thin-wall part |
| CN104015015A (en) * | 2014-06-23 | 2014-09-03 | 什邡市明日宇航工业股份有限公司 | Numerical control integrated manufacturing technology for parts of outer barrel of main landing gear of airplane |
| 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 |
| CN104259774A (en) * | 2014-09-09 | 2015-01-07 | 黄河科技学院 | Plane wing titanium alloy thin-wall web efficient numerical control machining technology |
| CN104889462A (en) * | 2015-06-17 | 2015-09-09 | 沈阳飞机工业（集团）有限公司 | Method for reducing deformation of numerical control machining plate type titanium alloy parts |
| CN105328411A (en) * | 2015-11-06 | 2016-02-17 | 西北工业大学明德学院 | Numerical control machining method of airplane model |
| CN106399882A (en) * | 2016-11-30 | 2017-02-15 | 中国直升机设计研究所 | Heat treatment method for machining deformation prevention of 7055 aluminium alloy thin-walled structure |
| CN107052715A (en) * | 2017-03-30 | 2017-08-18 | 陕西飞机工业（集团）有限公司 | A kind of large-scale Integral Wing Panel numerical-control processing method |
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