CN111122315B - Aging performance assessment method for eliminating residual stress of aviation metal part - Google Patents
Aging performance assessment method for eliminating residual stress of aviation metal part Download PDFInfo
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- CN111122315B CN111122315B CN201911282340.7A CN201911282340A CN111122315B CN 111122315 B CN111122315 B CN 111122315B CN 201911282340 A CN201911282340 A CN 201911282340A CN 111122315 B CN111122315 B CN 111122315B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/26—Methods of annealing
- C21D1/30—Stress-relieving
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/74—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material
- C21D1/773—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material under reduced pressure or vacuum
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0047—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to residual stresses
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/24—Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing forces
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/20—Recycling
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Abstract
The invention provides an aging performance assessment method for eliminating residual stress of an aviation metal part, which comprises the following steps: preparing a test device; machining the metal part for testing to form a plate with a preset curvature; a plate with a preset curvature is covered with a vacuum bag film (5) and placed on the flat plate die (1); putting the flat plate mould (1) with the metal parts for testing into a vacuum autoclave (6); in a vacuum autoclave (6), carrying out an aging process for eliminating residual stress on the metal parts for test, and pressing the metal parts for test into a planar plate by using a vacuum bag film (5); performing static or shear examination on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter; and confirming the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be checked. The method is accurate and reliable, and the mechanical property of the metal part to be checked cannot be damaged.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a method for evaluating aging performance of eliminating residual stress of aviation metal parts.
Background
The aerospace industry uses metal materials in large quantities for the manufacture of large parts with complex cross-sections, where residual stresses that are difficult to eliminate are generated during the manufacturing process, resulting in part deformation. In order to eliminate the residual stress in the manufacturing process of the large-sized complex-section part, the aging can be carried out in an autoclave, meanwhile, the pressure is introduced in the process to lead the part to creep, and finally, the residual stress is eliminated while the part achieves the target performance.
However, after aging for residual stress relief in an autoclave, the parts generally exhibit a final morphology with curvature, and the parts with curvature cannot undergo static or shear test commonly used in engineering.
Disclosure of Invention
In view of the above, in order to solve at least one technical problem in the prior art, the present invention provides a testing method for onboard display control software. The method comprises the following steps:
the technical scheme of the invention is as follows:
a method for evaluating the aging performance of eliminating the residual stress of aviation metal parts, wherein the metal parts to be evaluated are plates with preset curvature after the aging process of eliminating the residual stress, comprises the following steps:
s1, preparing a test device comprising: dull and stereotyped mould (1), fixed platform (2), bolt (3), wherein: the flat plate die (1) is arranged above the fixed platform (2) and is connected with the fixed platform (2) through a bolt (3);
S2, machining the metal part for testing to form a plate with a preset curvature, wherein the metal part for testing is the plate with the preset curvature formed by machining; s2, covering a plate with a preset curvature with a vacuum bag film (5), and placing the plate on a flat plate die (1);
s3, placing the flat plate mould (1) with the metal parts for testing into a vacuum autoclave (6);
s4, in the vacuum autoclave (6), the aging process for eliminating residual stress is carried out on the metal parts for testing, and the metal parts for testing are pressed into a plane plate by using the vacuum bag film (5);
s5, performing a static or shear examination test on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter;
and S6, confirming the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be checked.
The advantages of the invention may be:
the properties of the metal part to be examined are determined by testing the properties of the metal part 4. The test metal part 4 is first a plate material with a predetermined curvature formed by machining. The test metal parts 4 were pressed into flat test pieces after aging for residual stress relief in order to test the final performance level. And performing static or shear examination on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter, and confirming the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be examined. The device is not only accurate and reliable, but also can not damage the mechanical property of the metal part to be checked.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic diagram of an apparatus for aging performance assessment for eliminating residual stress of an aviation metal part according to an embodiment of the invention;
FIG. 2 is an isometric view of an apparatus for aging performance assessment to relieve residual stress in an aerospace metal part according to an embodiment of the invention;
FIG. 3 is an isometric view of an apparatus for aging performance assessment to relieve residual stress in an aerospace metal part according to another embodiment of the invention;
FIG. 4 is a side view of a test piece tooling for aging relieving residual metal stress in accordance with an embodiment of the present invention.
The device comprises a flat plate die 1, a fixed platform 2, a bolt 3, a metal part 4 for testing, a vacuum bag film 5 and a vacuum autoclave 6.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of the invention and illustrative embodiments will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement or method set forth below, but rather covers any improvements, substitutions or modifications in structure, method or apparatus without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
It should be noted that, in the case of conflict, the embodiments and features of the embodiments of the present invention may be combined with each other, and the respective embodiments may be mutually referred to and cited. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic diagram of an aging performance assessment device for eliminating residual stress of an aviation metal part according to an embodiment of the invention; FIG. 2 is an isometric view of an apparatus for aging performance assessment to relieve residual stress in an aerospace metal part according to an embodiment of the invention; FIG. 3 is an isometric view of an apparatus for aging performance assessment to relieve residual stress in an aerospace metal part according to another embodiment of the invention; FIG. 4 is a side view of a test piece tooling for aging relieving residual metal stress in accordance with an embodiment of the present invention.
Referring to fig. 1 to 4, a method for evaluating aging performance of eliminating residual stress of an aviation metal part, wherein the metal part to be evaluated is a plate with a preset curvature after an aging process for eliminating residual stress, the method comprising the following steps:
s1, preparing a test device, the test device comprising: dull and stereotyped mould (1), fixed platform (2), bolt (3), wherein: the flat plate die (1) is arranged above the fixed platform (2) and is connected with the fixed platform (2) through a bolt (3);
s2, machining the metal part for testing to form a plate with a preset curvature, wherein the metal part for testing is the plate with the preset curvature formed by machining; s2, covering a plate with a preset curvature with a vacuum bag film (5), and placing the plate on a flat plate die (1);
s3, placing the flat plate mould (1) with the metal parts for testing into a vacuum autoclave (6);
s4, in the vacuum autoclave (6), the aging process for eliminating residual stress is carried out on the metal parts for testing, and the metal parts for testing are pressed into a plane plate by using the vacuum bag film (5);
s5, performing a static or shear examination test on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter;
And S6, confirming the failure strength parameters of the plate pressed into the plane as the failure strength parameters of the metal parts to be checked.
In some embodiments, the concave surface of the sheet material with the predetermined curvature is ribbed.
In some embodiments, the metal part (4) for testing has the same curvature as the metal part to be checked.
In some embodiments, the flat mold (1) has grooves corresponding to the ribs.
In some embodiments, the aging process determines a preset pressure, a preset temperature, to be applied to the metal part to be verified.
In some embodiments, the flat mold (1) is sealed at the connection with the flat mold (1).
In some embodiments, the method further comprises: the test metal part (4) coated with the vacuum bag film (5) and carried on the flat plate die (1) is subjected to an aging process for eliminating residual stress by using a vacuum autoclave (6), and the test metal part (4) is creep-formed into a planar plate.
In some embodiments, the method further comprises: taking out the plate which creeps into a plane from the vacuum autoclave (6), carrying out static or shearing examination on the plate which is pressed into the plane by using a static test platform to obtain a failure strength parameter, and confirming the failure strength parameter of the plate which is pressed into the plane as the failure strength parameter of the metal part to be examined.
The assessment verification test design method for eliminating the residual stress of the metal by aging, which meets the requirements of common static or shear assessment tests in the aerospace industry, of the embodiment of the invention follows the following principle:
principle 1 flat test piece:
in order to carry out static or shearing examination and verification tests commonly used in the aerospace industry, the examination test piece for carrying out the tests must be a flat test piece, and the curvature of the examination test piece cannot be ensured.
to carry out an examination and verification test on the aging process for eliminating the residual stress, the process characteristics used for manufacturing the examination test piece and the aging process characteristics for eliminating the residual stress are completely consistent. The process is characterized by comprising the following steps: temperature, pressure, time, and part deformation. Therefore, the metal examination and verification test piece is machined into the test piece with the same curvature as the part, the same residual stress eliminating aging process is carried out on the test piece with the curvature by using the same residual stress eliminating aging process characteristic, and finally the test piece is subjected to creep deformation to the flat plate examination and verification test piece.
after a flat plate examination verification test piece capable of completely reproducing the aging process characteristic of eliminating the residual stress is manufactured according to the principle, a static force or shear examination test commonly used in the aerospace industry needs to be carried out, and the test result has the comparability with other tests at home and abroad.
In some embodiments, a method for designing an examination and verification test piece for eliminating residual stress of metal by aging comprises the following steps:
step 1, manufacturing a wall plate part with curvature from a metal material by using a machining method;
step 7, taking the flat plate part in the step 6 out of the autoclave;
and 8, testing according to a common static or shear assessment test method for aerospace.
It should be noted that the above-mentioned flow operations may be combined and applied in different degrees, and for simplicity, implementation manners of various combinations are not described again, and those skilled in the art may flexibly adjust the sequence of the above-mentioned operation steps according to actual needs, or flexibly combine the above-mentioned steps, and the like.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (7)
1. A method for evaluating the residual stress of aviation metal parts by eliminating the aging performance of the residual stress, wherein the metal parts to be evaluated are plates with preset curvature after the aging process for eliminating the residual stress, the metal parts for testing are plates which are taken out from a vacuum autoclave (6) and creep into a plane, a static test platform is used for carrying out static or shearing evaluation tests on the plates pressed into the plane to obtain failure strength parameters, and the failure strength parameters of the plates pressed into the plane are confirmed as the failure strength parameters of the metal parts to be evaluated, and the method is characterized by comprising the following steps:
s1, preparing a test device, the test device comprising: dull and stereotyped mould (1), fixed platform (2), bolt (3), wherein: the flat plate die (1) is arranged above the fixed platform (2) and is connected with the fixed platform (2) through a bolt (3);
s2, machining the metal part for testing to form a plate with a preset curvature, wherein the metal part for testing is the plate with the preset curvature formed by machining; s2, covering a plate with a preset curvature with a vacuum bag film (5) and placing the plate on a flat plate mould (1);
s3, placing the flat plate mould (1) with the metal parts for testing into a vacuum autoclave (6);
S4, in the vacuum autoclave (6), the aging process for eliminating residual stress is carried out on the metal parts for testing, and the metal parts for testing are pressed into a plane plate by using the vacuum bag film (5);
s5, performing a static or shear examination test on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter;
and S6, confirming the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be checked.
2. The method of claim 1, wherein:
the concave surface of the plate with the preset curvature is provided with ribs.
3. The method of claim 1, wherein:
the test metal part (4) has the same curvature as the metal part to be examined.
4. The method of claim 1, wherein:
the flat plate die (1) is provided with grooves corresponding to the ribs.
5. The method of claim 1, wherein:
the aging process determines a preset pressure and a preset temperature applied to the metal part to be verified.
6. The method of claim 1, wherein:
the joint of the flat plate mould (1) and the flat plate mould (1) is sealed.
7. The method of any one of claims 1-6, further comprising:
the aging process for eliminating residual stress is carried out on the test metal part (4) coated with the vacuum bag film (5) and carried on the flat mold (1) by utilizing a vacuum autoclave (6), and the test metal part (4) is creeping into a plane plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911282340.7A CN111122315B (en) | 2019-12-13 | 2019-12-13 | Aging performance assessment method for eliminating residual stress of aviation metal part |
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| CN201911282340.7A CN111122315B (en) | 2019-12-13 | 2019-12-13 | Aging performance assessment method for eliminating residual stress of aviation metal part |
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| Publication Number | Publication Date |
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| CN111122315A CN111122315A (en) | 2020-05-08 |
| CN111122315B true CN111122315B (en) | 2022-06-28 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS60135839A (en) * | 1983-12-26 | 1985-07-19 | Natl House Ind Co Ltd | Panel support apparatus for shear tester |
| JP2004132739A (en) * | 2002-10-08 | 2004-04-30 | Honda Motor Co Ltd | Shear testing device of curved panel |
| CN103691793B (en) * | 2013-12-20 | 2015-12-30 | 中南大学 | One-step forming method of aging-strengthening aluminum alloy integral wall plate based on autoclave |
| CN207051108U (en) * | 2017-08-02 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bent plate shear stability test fixture |
| CN207423701U (en) * | 2017-11-10 | 2018-05-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of stiffened panel shearing test part component and stiffened panel shearing test system |
| CN209513479U (en) * | 2018-12-14 | 2019-10-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of shear fatigue test part |
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