US20150299836A1 - Method of manufacturing formed component for aircraft use made of aluminum alloy and formed component for aircraft use - Google Patents

Method of manufacturing formed component for aircraft use made of aluminum alloy and formed component for aircraft use Download PDF

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US20150299836A1
US20150299836A1 US14/647,359 US201314647359A US2015299836A1 US 20150299836 A1 US20150299836 A1 US 20150299836A1 US 201314647359 A US201314647359 A US 201314647359A US 2015299836 A1 US2015299836 A1 US 2015299836A1
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Prior art keywords
formed component
aircraft use
strain
manufacturing
imparted
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Abandoned
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US14/647,359
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Inventor
Hideki Okada
Chikara Ishikawa
Etsuko Yamada
Takumi WADA
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Kawasaki Motors Ltd
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Kawasaki Jukogyo KK
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Assigned to KAWASAKI JUKOGYO KABUSHIKI KAISHA reassignment KAWASAKI JUKOGYO KABUSHIKI KAISHA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WADA, TAKUMI, ISHIKAWA, CHIKARA, YAMADA, ETSUKO, OKADA, HIDEKI
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21B—ROLLING OF METAL
    • B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21B—ROLLING OF METAL
    • B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
    • B21B1/22—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling plates, strips, bands or sheets of indefinite length
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21B—ROLLING OF METAL
    • B21B3/00—Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
    • B21B2003/001—Aluminium or its alloys

Definitions

  • the present invention relates to a method of manufacturing a formed component for aircraft use made of an aluminum alloy, and to the formed component for aircraft use manufactured by the manufacturing method.
  • a typical material used in formed components for aircraft use is an aluminum alloy.
  • a lithium-containing aluminum alloy hereinafter, simply referred to as an “aluminum-lithium alloy”
  • aluminum-lithium alloy has a lower density than the other aluminum alloys, and in addition, has excellent strength. Therefore, replacing formed components made of aluminum by formed components made of an aluminum-lithium alloy has been discussed aiming to realize, for example, further reduction of the weight of aircrafts.
  • the formed component for aircraft use is manufactured in such a manner that the material fabricated from a sheet material, a plate material, or an extrusion-molded member is mechanically machined into an intended shape, or even if forming of the material is performed, the forming to be performed is significantly limited.
  • Patent Literature 1 discloses a method of manufacturing a roll-formed component for aircraft use, the method including: performing a rolling process on a sheet-shaped coil material made of an aluminum alloy; then subjecting the material to solution heat treatment; and thereafter subjecting the material to three-staged aging treatment. By controlling the temperature in the aging treatment, both high strength and excellent corrosion resistance are realized.
  • Patent Literature 1 The aluminum alloy adopted in Patent Literature 1 is 7000 series (7xxx series) in the International Alloy Designation System for aluminum alloys. Patent Literature 1 makes no reference to whether or not the aluminum alloy, whose primary alloy components are zinc and magnesium, contains lithium. In addition, the temper of the roll-formed component for aircraft use obtained by the manufacturing method disclosed in Patent Literature 1 is T7. Therefore, it is substantially difficult to apply the manufacturing method disclosed in Patent Literature 1 to manufacturing of a formed component for aircraft use made of an aluminum-lithium alloy and adjust the temper of the formed component to T8. The same is true for the other aluminum alloys.
  • An object of the present invention is to provide a technique that makes it possible to manufacture a formed component for aircraft use made of an aluminum alloy at a lower cost than conventional art.
  • a method of manufacturing a formed component for aircraft use according to the present invention is a method of manufacturing a formed component for aircraft use made of an aluminum alloy, the method including: subjecting a material made of an aluminum alloy to solution heat treatment; then forming the material into a predetermined shape under cold working conditions; and thereafter subjecting the material to artificial age-hardening treatment. Under the cold working, the material is formed into the predetermined shape while a strain corresponding to a temper T8 is being imparted to the material by a roll forming apparatus.
  • the roll forming apparatus may be configured as a multi-stage roll forming apparatus.
  • a clearance of at least some of rolls of the multi-stage roll forming apparatus may be adjusted to be less than a thickness of the material to impart a compressive strain to the material.
  • the strain imparted to the material when the forming of the material is performed may be a compressive strain or a tensile strain.
  • the aluminum alloy may be an aluminum-lithium alloy containing lithium.
  • the formed component for aircraft use may be a frame or a stringer.
  • the present invention also includes a formed component for aircraft use made of an aluminum alloy, the formed component being obtained by the above-described method of manufacturing a formed component for aircraft use.
  • the present invention is configured as described above, and has an advantage of making it possible to manufacture a formed component for aircraft use made of an aluminum alloy at a lower cost than conventional art.
  • FIG. 1 is a flowchart showing one example of a method of manufacturing a formed component for aircraft use made of an aluminum-lithium alloy according to one embodiment of the present invention.
  • FIG. 2 is a timing diagram showing temperature changes in the manufacturing method shown in FIG. 1 .
  • FIG. 3 is a graph showing results of representative reference examples of the present invention and showing a relationship between a tensile strength and a strain amount for each test piece to which a compressive strain was imparted and each test piece to which a tensile strain was imparted.
  • FIG. 4 is a graph showing results of representative working examples of the present invention and showing a relationship between a tensile strength and a strain amount for each test piece to which a compressive strain was imparted and each test piece to which a tensile strain was imparted.
  • a formed component for aircraft use according to the present invention is made of an aluminum alloy.
  • the formed component is not limited to a particular type, so long as the formed component is for aircraft use.
  • Examples of typical formed components for aircraft use include frames and stringers used as aircraft structural members. In general, these structural members are manufactured by a rolling process using a roll forming apparatus (a roller forming apparatus). Therefore, in the present invention, the formed component for aircraft use is preferably a roll-formed component.
  • An aluminum alloy used as the material of the formed component for aircraft use according to the present invention is not limited to a particular kind.
  • a lithium-containing aluminum alloy i.e., an aluminum-lithium alloy
  • the aluminum-lithium alloy is not limited to a particular kind
  • typical aluminum-lithium alloys include, among 8xxx series (8000 series) in the International Alloy Designation System for aluminum alloys, those containing lithium as a primary alloy component, and among 2xxx series (2000 series) in the International Alloy Designation System, those containing lithium as a secondary alloy component.
  • the aluminum alloys in 8xxx series are different from those in 1xxx series to 7xxx series.
  • one example of aluminum alloy containing lithium as a primary alloy component i.e., Al—Li based alloy
  • the aluminum alloys in 2xxx series contain copper as a primary alloy component.
  • those containing lithium as a secondary alloy component i.e., Al—Cu—Li based alloys
  • 2050 and 2090 those containing lithium as a secondary alloy component
  • aluminum-lithium alloys that contain copper and magnesium as alloy components (i.e., Al—Li—Cu—Mg based alloys), such as 2091 and 8091.
  • These known aluminum-lithium alloys may each be used as the material of the formed component for aircraft use according to the present invention.
  • the temper of the aluminum-lithium alloy needs to be T8 (equivalent to JIS H0001).
  • T8 an aluminum alloy with the temper T8 is defined as “one that has been subjected to solution heat treatment, then subjected to cold working, and further subjected to artificial age-hardening treatment” or “one that has been subjected to solution heat treatment, then subjected to cold working for increasing strength, and further subjected to artificial age-hardening treatment”.
  • the T8 state of an aluminum alloy is a state where the aluminum alloy has been subjected to solution heat treatment, then imparted with a strain by several percent in a thermally refined intermediate state, and further subjected to artificial age-hardening treatment.
  • the aluminum-lithium alloy is in the T8 state, its physical properties such as fracture toughness, strength, and corrosion resistance are excellent, and the aluminum-lithium alloy can be suitably used in the field of aircrafts.
  • a method of manufacturing a formed component for aircraft use according to the present invention includes: subjecting a material made of an aluminum alloy, such as an aluminum-lithium alloy, to solution heat treatment; then subjecting the material to cold working to form the material into a predetermined shape; and thereafter subjecting the material to artificial age-hardening treatment. At the time of forming of the material by the cold working, the material is imparted with a strain corresponding to the temper T8.
  • a sheet (plate) material made of an aluminum-lithium alloy is prepared, and the sheet material is subjected to solution heat treatment (step S 01 ).
  • the temper of the sheet material is initially “O” (JIS H0001), and the sheet material is in a softened state owing to annealing.
  • the temper of the sheet material becomes “W” (JIS H0001), i.e., becomes harder than before the solution heat treatment.
  • the sheet material in the W state is subjected to a cold working process (step S 02 ).
  • the cold working process the sheet material is stretched not in a general manner by a roll forming apparatus but in a manner using a multi-stage roll forming apparatus (a multi-stage roller forming apparatus), such that the sheet material is formed in the shape of the frame. Therefore, the cold working process in the present invention can be considered as a frame-forming process (or a component shape forming process).
  • a compressive strain is imparted to the sheet material by first-stage rolls of the multi-stage roll forming apparatus (step S 21 , first roll compression process).
  • the clearance of the first-stage rolls is adjusted to be less than the thickness of the sheet material, and thereby the compressive strain is imparted to the sheet material.
  • the amount of compressive strain imparted at the time is substantially equivalent to a dislocation density necessary for realizing the T8 state.
  • the compressive strain is imparted by the first-stage rolls, the present invention is not thus limited.
  • the compressive strain may be imparted by other rolls at the second or subsequent stage.
  • step S 22 forming of the sheet material, to which the compressive strain has been imparted, is performed by section rolls at the second or subsequent stage, such that a desired cross-sectional shape is imparted to the sheet material
  • step S 23 curving roll forming process
  • the frame is subjected to a post-forming process (step S 03 ).
  • the post-forming process include rough trimming and strain straightening (strain relieving).
  • the post-forming process is not limited to a particular process.
  • the frame sheet material is subjected to artificial age-hardening treatment (aging treatment) (step S 04 ).
  • aging treatment age-hardening treatment
  • the temper of the aluminum-lithium alloy forming the frame becomes T8. In this manner, the frame suitable for aircraft use made of the aluminum-lithium alloy can be obtained.
  • FIG. 2 illustrates the above-described manufacturing method in the form of a timing diagram showing temperature changes.
  • the cold working process of the present invention not simple stretching but both stretching and frame forming (component forming) are performed at the same time.
  • the manufacturing process of the present invention is compared with a general manufacturing process, although the processes and treatments performed on the aluminum-lithium alloy are fundamentally the same between these manufacturing processes, there is a difference in terms of the manner of imparting the strain before the forming.
  • the compressive strain which is substantially equivalent to a tensile strain for realizing the T8 state, is imparted to the sheet material made of the aluminum-lithium alloy after the solution heat treatment.
  • the formed component for aircraft use made of the aluminum-lithium alloy in the T8 state can be manufactured substantially by a rolling process. This consequently makes it possible to manufacture the formed component for aircraft use made of the aluminum-lithium alloy at a lower cost than conventional art.
  • natural age-hardening treatment may be performed between the solution heat treatment (step S 01 ) and the cold working process (step S 02 ).
  • the strength of the manufactured formed component for aircraft use can be further improved.
  • solution heat treatment and the cold working process may be performed as part of the process of manufacturing the formed component for aircraft use.
  • the material that has been subjected to the solution heat treatment and the cold working process in advance may be used to manufacture the formed component for aircraft use.
  • the solution heat treatment and the cold working process may be performed by the manufacturer of the material, or may be performed by the manufacturer of the formed component for aircraft use.
  • the sheet material is, after being subjected to the solution heat treatment, passed through the multi-stage roll forming apparatus, and thereby a compressive strain is imparted to the sheet material.
  • the present invention is not thus limited. Not a compressive strain but a tensile strain may be imparted to the sheet material. That is, in the present invention, the manner of imparting a strain to the sheet material is not particularly limited, so long as a strain for realizing the T8 state can be imparted to the sheet material in the cold working process.
  • the multi-stage roll forming apparatus including the section rolls and curving rolls is used as an apparatus for performing the cold working process.
  • the present invention is not thus limited. Any known forming apparatus capable of imparting a strain such as a compressive strain to a sheet-shaped aluminum material may be suitably used as the apparatus for performing the cold working process.
  • Specific examples of the forming apparatus using multi-stage rolls include a stretcher leveler and a roller leveler.
  • the clearance of the first-stage rolls is adjusted to be less than the thickness of the sheet material (i.e., less than the original thickness of the sheet material), and thereby a compressive strain is imparted to the sheet material.
  • the degree of the clearance adjustment is not particularly limited.
  • the clearance may be suitably set based on conditions, such as the kind of the aluminum-lithium alloy, the thickness of the sheet material, and a necessary degree of strain for realizing the T8 state.
  • the formed component for aircraft use is a frame.
  • the present invention is of course not limited to this.
  • a different formed component for aircraft use such as a stringer, can be manufactured by the present invention.
  • a suitable roll-forming process is performed in accordance with the type of the component to be manufactured.
  • the material to which the strain is imparted after being subjected to the solution heat treatment is a sheet material
  • the present invention is of course not limited to this.
  • a material different from the sheet material i.e., a material with a different shape, may be suitably used, so long as a strain for realizing the T8 state can be imparted to the material.
  • a sheet material made of an aluminum-lithium alloy whose temper is O is subjected to solution heat treatment, and thereby the temper of the sheet material is adjusted to W.
  • the sheet material with the temper W is formed into a predetermined shape.
  • the temper of the resultant sheet material (formed sheet material) is T3 or substantially T3.
  • the formed sheet material whose temper is T3 or substantially T3 is subjected to artificial age-hardening treatment, and thereby the formed sheet material with a temper T8 is obtained.
  • test piece An aluminum-lithium alloy 2198 available from Constellium was used to obtain a strip-shaped test piece whose temper was adjusted to substantially T3 by thermal refining.
  • the test piece is hereinafter referred to as a “pre-forming test piece” for the sake of convenience of the description.
  • the test piece was rolled by a rolling mill (trade name: two-stage rolling mill DBR 150 available from daito seisakuzyo inc.) at least once. In this manner, a compressive strain was imparted to the test piece.
  • the test piece to which the compressive strain has been imparted is hereinafter referred to as a “strain-imparted test piece” for the sake of convenience of the description.
  • test pieces were subjected to artificial age-hardening treatment, and thereby test pieces of Reference Example 1 were obtained.
  • Each of the obtained test pieces is hereinafter referred to as a “post-forming test piece” for the sake of convenience of the description.
  • a test piece for use in a tensile test was obtained from each post-forming test piece.
  • a tensile testing machine (universal testing machine 1001N available from Instron) was used to perform the tensile test on the test piece in accordance with ASTM B557. Through the tensile test, data of the tensile strength, yield strength, Young's modulus, and the breaking elongation of each post-forming test piece were obtained. These data were compared with results obtained from Reference Example 2 described below and with the data of a “reference T8 material” having a temper T8, which was provided from a material manufacturer.
  • the tensile strength was chosen as representative data, and a relationship between the tensile strength and the strain amount was plotted on a graph. Results of the plotting are indicated by black circular symbols in FIG. 3 .
  • each post-fanning test piece was measured by using an X-ray diffraction apparatus (trade name: fully automatic multipurpose X-ray diffraction apparatus PW3050 available from Spectris Co., Ltd.).
  • X-ray diffraction apparatus trade name: fully automatic multipurpose X-ray diffraction apparatus PW3050 available from Spectris Co., Ltd.
  • Each post-forming test piece was also observed by a transmission electron microscope (TEM), and thereby a T1 phase deposited through the artificial age-hardening treatment was evaluated.
  • TEM transmission electron microscope
  • the tensile strength was chosen as representative data, and a relationship between the tensile strength and the strain amount was plotted on a graph. Results of the plotting are indicated by white outlined diamond-shaped symbols in FIG. 3. Further, similar to Reference Example 1, the dislocation density of each post-forming test piece was measured, and the Ti phase deposited thereon was evaluated.
  • both the post-forming test pieces of Reference Example 1 and the post-forming test pieces of Reference Example 2 exhibited substantially the same or better results compared to the reference T8 material although specific data are not given herein. Further, it was found that substantially the same degree of dislocation was introduced into each of the post-forming test pieces of Reference Example 1 and the post-forming test pieces of Reference Example 2. Thus, it is understood that, by imparting the strain under cold working conditions, whether the imparted strain is a compressive strain or a tensile strain, substantially the same strength can be obtained, and in addition, the T8 state can be realized.
  • a pre-forming test piece with a temper W was obtained in the same manner as in Working Example 1.
  • a strain-imparted test piece imparted with a tensile strain and a post-forming test piece resulting from subjecting the strain-imparted test piece to artificial age-hardening treatment were obtained.
  • three target amounts of tensile strains of 2%, 5%, and 8% were imparted.
  • the present invention is widely and suitably applicable in the field of manufacturing a formed component for aircraft use made of an aluminum alloy.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Bending Of Plates, Rods, And Pipes (AREA)
  • Metal Rolling (AREA)
US14/647,359 2012-12-21 2013-12-19 Method of manufacturing formed component for aircraft use made of aluminum alloy and formed component for aircraft use Abandoned US20150299836A1 (en)

Applications Claiming Priority (3)

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JP2012279796 2012-12-21
JP2012-279796 2012-12-21
PCT/JP2013/007463 WO2014097631A1 (ja) 2012-12-21 2013-12-19 アルミニウム合金製航空機用成形部品の製造方法および航空機用成形部品

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EP (1) EP2937435B1 (ja)
JP (1) JP6480733B2 (ja)
BR (1) BR112015013992A2 (ja)
CA (1) CA2890535C (ja)
WO (1) WO2014097631A1 (ja)

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JP6403515B2 (ja) * 2014-09-24 2018-10-10 三菱重工業株式会社 接合部処理方法及びドーム部材
CN105215124B (zh) * 2015-10-12 2018-06-05 中国航空工业集团公司北京航空材料研究院 一种人工时效态铝合金薄板的成形方法
CN105344780A (zh) * 2015-10-12 2016-02-24 中国航空工业集团公司北京航空材料研究院 一种人工时效态铝合金薄板的成形方法
CN105215123B (zh) * 2015-10-12 2018-06-05 中国航空工业集团公司北京航空材料研究院 一种自然时效态铝锂合金薄板的成形方法
CN105344779A (zh) * 2015-10-12 2016-02-24 中国航空工业集团公司北京航空材料研究院 一种人工时效态铝合金薄板的成形方法
CN105215125A (zh) * 2015-10-12 2016-01-06 中国航空工业集团公司北京航空材料研究院 一种自然时效态铝合金薄板的成形方法
CN105215121A (zh) * 2015-10-12 2016-01-06 中国航空工业集团公司北京航空材料研究院 一种人工时效态铝合金薄板的成形方法
CN105215122A (zh) * 2015-10-12 2016-01-06 中国航空工业集团公司北京航空材料研究院 一种自然时效态铝合金薄板的成形方法
CN105344786A (zh) * 2015-10-12 2016-02-24 中国航空工业集团公司北京航空材料研究院 一种人工时效态铝合金薄板的成形方法
JP7118688B2 (ja) * 2018-03-28 2022-08-16 三菱重工業株式会社 被加工物の加工方法及び加工装置
KR102494830B1 (ko) * 2022-03-22 2023-02-06 국방과학연구소 다단 시효처리를 이용한 Al-Li 합금의 제조방법

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WO2014097631A1 (ja) 2014-06-26
JP6480733B2 (ja) 2019-03-13
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BR112015013992A2 (pt) 2017-07-11
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