WO2018189471A1 - Aluminium-copper-lithium alloy products - Google Patents
Aluminium-copper-lithium alloy products Download PDFInfo
- Publication number
- WO2018189471A1 WO2018189471A1 PCT/FR2018/050886 FR2018050886W WO2018189471A1 WO 2018189471 A1 WO2018189471 A1 WO 2018189471A1 FR 2018050886 W FR2018050886 W FR 2018050886W WO 2018189471 A1 WO2018189471 A1 WO 2018189471A1
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Classifications
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- 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
- C22C21/16—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
Definitions
- the invention generally relates to wrought products of aluminum-copper-lithium alloys, and more particularly to such products in the form of profiles intended to produce stiffeners in aeronautical construction. State of the art
- Aluminum alloys containing lithium are very interesting in this respect, since lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added.
- their performance must reach that of commonly used alloys, in particular in terms of a compromise between the static mechanical strength properties (elastic limit, breaking strength) and the properties of damage tolerance ( toughness, resistance to the propagation of fatigue cracks), these properties being in general antinomic.
- These alloys must also have sufficient corrosion resistance, be able to be shaped according to the usual methods and have low residual stresses so that they can be machined integrally.
- Several Al-Cu-Li alloys are known for which an addition of silver is made.
- No. 5,032,359 discloses a broad family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, in particular between 0.3 and 0.5 percent by weight, makes it possible to increase the mechanical strength. These alloys are often known under the trade name "Weldalite TM”.
- US Patent 5,198,045 discloses a family of Weldalite TM alloys comprising (in% by weight) (2,4-3,5) Cu (1,35-1,8) Li (0.25-0.65). Mg, (0.25-0.65) Ag, (0.08-0.25) Zr.
- the Wrought products made with these alloys combine a density of less than 2.64 g / cm 3 and a compromise between strength and toughness of interest.
- US Pat. No. 7,229,509 describes a family of Weldalite TM alloys comprising (in% by weight) (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0). Mg, (0.2-0.8) Ag, (0.2-0.8) Mn, (up to 0.4) Zr or other elements such as Cr, Ti, Hf, Se and V. Examples presented have a compromise between mechanical strength and improved toughness but their density is greater than 2.7 g / cm 3 .
- Patent application WO2007 / 080267 discloses a Zirconium-free Weldalite TM alloy for fuselage plates comprising (in% by weight) (2, 1-2.8) Cu, (1, 1-1, 7) Li, (0.2-0.6) Mg, (0.1-0.8) Ag, (0.2-0.6) Mn.
- AA2196 alloy comprising (in% by weight) (2.5-3.3) Cu, (1, 4-2.1) Li, (0.25-0.8) Mg, is also known. , 25-0.6) Ag, (0.04-0.18) Zr and at most 0.35 Mn.
- a first subject of the invention is an aluminum-based alloy product comprising, in% by weight,
- Li 1.6-2.2; preferentially 1.65-1.8;
- Mg 0.4-0.9; preferentially 0.5-0.8;
- Mn 0.2 - 0.6; preferably 0.3-0.6;
- Zn ⁇ 0.4, preferably 0.05-0.4; more preferably 0.2-0.4;
- Hf 0.01 - 0.5; preferably 0.02-0.1;
- V 0.01-0.3, preferably 0.01-0.05;
- a second object of the invention is a method of manufacturing a spun, rolled and / or forged product based on aluminum alloy comprising the steps:
- the income is made so that said product has a conventional yield strength measured at 0.2% elongation in the direction L, R p o, 2 (L), of at least 510 MPa and a tenacity KQ (LT), in the LT direction, of at least 21
- Yet another object of the invention is a structural element incorporating at least one product according to the invention.
- FIG. 1 Shape of the profile W of the example (the term “shape” means the cross section of said profile). The dimensions are given in mm. The samples used for the mechanical characterizations were taken from the area indicated by the dots.
- FIG. 2 Shape of the profile Z of the example (the term “shape” means the cross section of said profile). The dimensions are given in mm. The samples used for the mechanical characterizations were taken from the area indicated by the dots.
- alloys are in accordance with the regulations of The Aluminum Association, known to those skilled in the art.
- the density depends on the composition and is determined by calculation rather than by a method of measuring weight.
- the values are calculated in accordance with the procedure of The Aluminum Association, which is described pages 2-12 and 2.13 of "Aluminum Standards and Data". The definitions of the metallurgical states are given in the European standard EN 5 15 (2009).
- the static mechanical characteristics in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p o, 2 ("yield strength") and elongation at break A, are determined by a tensile test according to EN 10002-1 (2001), the sampling and the direction of the test being defined by EN 485-1 (2016).
- the stress intensity factor (KQ) is determined according to ASTM E 399 (2012).
- ASTM E 399 (2012) gives paragraphs 9. 1 .3 and 9.1.
- criteria to determine if KQ is a valid Kic value Thus, a Kic value is always a KQ value, the reciprocal being not true.
- the criteria of paragraphs 9.1 .3 and 9. 1 .4 of ASTM E399 (2012) are not always verified, however for a given specimen geometry, the KQ values presented are always comparable with each other, the geometry of the specimen making it possible to obtain a valid value of Kic not being always accessible taking into account the constraints related to the dimensions of the sheets or profiles.
- the thickness of the profiles is defined according to EN 2066: 2001: the cross section is divided into elementary rectangles of dimensions A and B; A being always the largest dimension of the elementary rectangle and B can be considered as the thickness of the elementary rectangle.
- a "structural element” or “structural element” of a mechanical construction is called a mechanical part for which the static and / or dynamic mechanical properties are particularly important for the performance of the structure, and for which a structural calculation is usually prescribed or realized.
- These are typically elements whose failure is likely to endanger the safety of said construction, its users, its users or others.
- these elements of These structures include the elements that make up the fuselage (such as fuselage skin (fuselage skin), stiffeners or stringers, bulkheads, circumferential frames, wings (such as wing skin), stiffeners (stiffeners), ribs (ribs) and spars) and empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the floor beams, the seat tracks and the doors.
- fuselage such as fuselage skin (fuselage skin), stiffeners or stringers, bulkheads, circumferential frames, wings (such as wing skin), stiffeners (stiffeners), ribs (ribs) and spars
- empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the floor beams, the seat tracks and the doors.
- a selected class of aluminum alloys containing specific and critical levels of copper, lithium, magnesium, zinc, manganese and zirconium but essentially free of silver makes it possible to prepare products wrought with an improved compromise between toughness and strength compared to products containing essentially no money.
- the present inventors have found that, surprisingly, it is possible for products to achieve a compromise at least equivalent between the static mechanical strength properties and the damage tolerance properties that that obtained with an aluminum-copper-lithium alloy containing silver, such as alloy AA2196, by carefully selecting the amounts of lithium, copper, magnesium, manganese, zinc and zirconium.
- the copper content of the products according to the invention is between 2.5 and 3.4% by weight. In an advantageous embodiment of the invention, the copper content is at least 2.8 or preferably at least 2.9% by weight and / or at most 3.2 and preferably at most 3.1% by weight. weight.
- the lithium content of the products according to the invention is between 1, 6 and 2.2% by weight.
- the lithium content is between 1.65% and 1.8% by weight.
- the lithium content is at most 1.75% by weight.
- the magnesium content of the products according to the invention is between 0.4 and 0.9% by weight and preferably it is at least 0.5% by weight and more preferably still greater than 0.6%. in weight.
- the magnesium content is from plus 0.8% by weight. The present inventors have found that when the magnesium content is less than 0.30% by weight the advantageous compromise between mechanical strength and damage tolerance is not achieved.
- the manganese content of the products according to the invention is between 0.2 and 0.6% by weight and, preferably, it is at least 0.3% by weight and, more preferably still, at least 0.33% by weight and more preferably at least 0.4% by weight. In another embodiment, the manganese content is between 0.2 and 0.4% by weight, preferably between 0.25 and 0.35% by weight. The present inventors have found that when the manganese content is less than 0.2% by weight, the KQ (LT) toughness, in the LT direction, advantageous according to the invention is not obtained.
- the zirconium content of the products according to the invention is between 0.08 and 0.18% by weight and, preferably, it is 0.12 to 0.16% by weight and more preferably 0% by weight. , 14 to 0.15% by weight. In another embodiment, the zirconium content is advantageously between 0.09 and 0.12% by weight, preferably between 0.09 and 0.11% by weight, and even between 0.09 and 0.10% by weight. in weight.
- the zinc content is less than 0.4% by weight, preferably it is 0.05 and 0.35% by weight.
- the zinc content is 0.2 to 0.3% by weight, which can contribute to achieving the desired compromise between toughness and strength.
- the silver content is less than 0.15% by weight, preferably less than 0.10% by weight and more preferably less than 0.05% by weight.
- the present inventors have found that the advantageous compromise between known mechanical strength and damage tolerance for alloys typically containing 0.2 to 0.4% by weight of silver can be obtained for alloys containing essentially no silver. with the composition selection made.
- the sum of the iron content and the silicon content is at most 0.20% by weight.
- the iron and silicon contents are each at most 0.08% by weight.
- the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
- the alloy also contains at least one element that can contribute to controlling the grain size selected from Ti, Se, Cr, Hf and V, the content of the element, if selected, being from 0.01 to 0 15% by weight, preferably 0.01 to 0.05% by weight for Ti; from 0.01 to 0.15% by weight, preferably 0.02 to 0.1% by weight for Se; 0.01 to 0.5% by weight, preferably 0.02 to 0.1% by weight for Hf and from 0.01 to 0.3% by weight, preferably from 0.02 to 0.1% by weight for Cr and from 0.01 to 0.3% by weight, preferably 0.01 to 0.05% by weight for V.
- the alloy according to the invention is particularly intended for the manufacture of rolled, spun and / or forged products and, more particularly, spun products.
- the products according to the invention have a compromise between mechanical strength and particularly advantageous toughness.
- the products according to the invention have a spun, solution, quenched, triturated and tempered state, especially for thicknesses up to 50 mm or between 8 and 50 mm, or even between 15 and 35 mm.
- test pieces used for KQ measurements are CT type 20mm thick and 50mm wide.
- the manufacturing process of the products according to the invention comprises stages of production, casting, rolling, extrusion and / or forging, dissolving, quenching, stripping and tempering.
- a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
- the liquid metal bath is then cast in a crude form typically a rolling plate, an extrusion billet or a forging blank.
- the crude form is then homogenized at a temperature between 450 ° C and 550 ° and preferably between 520 ° C and 530 ° C for a period of between 6 and 15 hours.
- the raw form is optionally cooled to room temperature before being preheated to be hot deformed.
- the hot deformation is carried out by rolling, extruding and / or forging so as to obtain a rolled product, spun and / or forged, preferably a spun product.
- the product thus obtained is then dissolved by heat treatment at 490-550 ° C for 15 minutes to 8 hours, and then typically quenched with water at room temperature.
- the product then undergoes controlled stress relief, preferably by traction, with a permanent deformation of 1 to 15% and preferably 2 to 4%.
- the spun product exhibits at the end of the above-described process steps a thickness of up to 50 mm or between 8 and 50 mm, or even between 15 and 35 mm.
- An income is achieved comprising heating at a temperature between 140 and 170 ° C for 5 to 70 hours so that said product has a conventional yield strength measured at 0.2% elongation in the L direction, R p o, 2 (L), of at least 510 MPa and a tenacity KQ (LT), in the LT direction, of at least 21 MPaVm and such that KQ (L-T)> -0.2667 * R p o, 2 (L) + 169.
- the present inventors have found that the compromise between mechanical strength and toughness can be improved by producing the temperature at a temperature of between 150 and 165 ° C. for a time equivalent to t at 160 ° C. between 15 and 28h, preferably between 20 and 27h, 3 ⁇ 4 being defined by the formula: f exp (-16400 / T) dt
- T in Kelvin
- T re f is a reference temperature set at 433 K.
- the spun product advantageously has a thickness, up to 50 mm or between 8 and 50 mm, or even between 15 and 35 mm.
- an object of the invention is a structural element incorporating at least one product according to the invention or a product manufactured from a method according to the invention.
- a structural element incorporating at least one product according to the invention or manufactured from such a product is advantageous, in particular for aeronautical construction.
- the products according to the invention are particularly advantageous for the production of structural elements such as stiffeners or frames for the manufacture of intrados or extrados elements of aircraft wings, preferably stiffeners, longitudinal members and ribs, or also floor beams and seat rails.
- Example 1 In this example, several billets (384 mm in diameter) of Al-Cu-Li alloy whose composition is given in Table 1 were cast (alloys 67, 74 a and b, 66, 68 and 69). The composition of two alloys of the prior art AA2196 has also been given in Table 1 below.
- alloys 67, 74a and b, 66, 68 and 69 Fe and Si ⁇ 0.20% by weight and other elements less than 0.05% by weight each, o.i5% by total weight.
- the alloy billets 67, 74a and b, 66, 68 and 69 were then homogenized from 8 to 10h at 524 ° C.
- the billet alloy 2 was homogenized 8h at 500 ° C and 24h at 527 ° C while the alloy 5 was homogenized 8h at 520 ° C.
- the billets were heated to 450 ° C. +/- 40 ° C. and then hot-spun to obtain profiles W according to FIG. 1 for the alloys 2, 67, 74 a and b, 66, 68 and 69 and Z according to Figure 2 for the alloys 5.
- the profiles thus obtained were dissolved at 524 ° C, quenched and tractionned with a permanent elongation of between 2 and 5%.
- the profiles were subjected to an income as indicated in Table 2: 30h at 152 ° C, 48h at 152 ° C, 30h at 160 ° C.
- the income was made for 48h to 152 ° C.
- the equivalent times t; at 160 ° C were calculated taking into account the rise time up to the income level and considering a rise speed of 20 ° C / h.
- Samples taken at the end of the profile were tested to determine their static mechanical properties as well as their toughness (KQ).
- the location of the samples is indicated in dashed lines in FIGS. 1 and 2.
- the reverts used for the measurement of the static properties were of diameter 10 mm and taken in such a way that the direction of the axis of the specimen corresponds to the direction of spinning (L direction).
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Abstract
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Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112019021170-5A BR112019021170B1 (en) | 2017-04-10 | 2018-04-09 | PRODUCT MADE OF ALUMINUM ALLOY CONTAINING, METHOD FOR MANUFACTURING EXTRUDED, ROLLED AND/OR FORGED PRODUCT CONTAINING ALUMINUM ALLOY, PRODUCT AND STRUCTURAL ELEMENT |
US16/603,604 US20210087665A1 (en) | 2017-04-10 | 2018-04-09 | Aluminum-copper-lithium alloy products |
CA3058021A CA3058021A1 (en) | 2017-04-10 | 2018-04-09 | Aluminium-copper-lithium alloy products |
EP18724941.2A EP3610047B1 (en) | 2017-04-10 | 2018-04-09 | Aluminium-copper-lithium alloy products |
CN201880024374.3A CN110536972B (en) | 2017-04-10 | 2018-04-09 | Aluminum-copper-lithium alloy product |
DE18724941.2T DE18724941T1 (en) | 2017-04-10 | 2018-04-09 | Aluminum-copper-lithium alloy products |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR1753133A FR3065011B1 (en) | 2017-04-10 | 2017-04-10 | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCTS |
FR17/53133 | 2017-04-10 |
Publications (1)
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WO2018189471A1 true WO2018189471A1 (en) | 2018-10-18 |
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ID=59811392
Family Applications (1)
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PCT/FR2018/050886 WO2018189471A1 (en) | 2017-04-10 | 2018-04-09 | Aluminium-copper-lithium alloy products |
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US (1) | US20210087665A1 (en) |
EP (1) | EP3610047B1 (en) |
CN (1) | CN110536972B (en) |
BR (1) | BR112019021170B1 (en) |
CA (1) | CA3058021A1 (en) |
DE (1) | DE18724941T1 (en) |
FR (1) | FR3065011B1 (en) |
WO (1) | WO2018189471A1 (en) |
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CN113249665A (en) * | 2021-07-02 | 2021-08-13 | 中国航发北京航空材料研究院 | Forming method of aluminum alloy component |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5032359A (en) | 1987-08-10 | 1991-07-16 | Martin Marietta Corporation | Ultra high strength weldable aluminum-lithium alloys |
US5198045A (en) | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
US7229509B2 (en) | 2003-05-28 | 2007-06-12 | Alcan Rolled Products Ravenswood, Llc | Al-Cu-Li-Mg-Ag-Mn-Zr alloy for use as structural members requiring high strength and high fracture toughness |
WO2007080267A1 (en) | 2005-12-20 | 2007-07-19 | Alcan Rhenalu | Sheet made of high-toughness aluminium alloy containing copper and lithium for an aircraft fuselage |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2938553B1 (en) * | 2008-11-14 | 2010-12-31 | Alcan Rhenalu | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCTS |
FR3004464B1 (en) * | 2013-04-12 | 2015-03-27 | Constellium France | PROCESS FOR TRANSFORMING AL-CU-LI ALLOY SHEETS ENHANCING FORMABILITY AND RESISTANCE TO CORROSION |
FR3014448B1 (en) * | 2013-12-05 | 2016-04-15 | Constellium France | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCT FOR INTRADOS ELEMENT WITH IMPROVED PROPERTIES |
FR3014905B1 (en) * | 2013-12-13 | 2015-12-11 | Constellium France | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCTS WITH IMPROVED FATIGUE PROPERTIES |
FR3014904B1 (en) * | 2013-12-13 | 2016-05-06 | Constellium France | PRODUCTS FILES FOR PLASTER FLOORS IN LITHIUM COPPER ALLOY |
CN106521270B (en) * | 2016-12-07 | 2018-08-03 | 中国航空工业集团公司北京航空材料研究院 | A kind of heat treatment process improving aluminium lithium alloy corrosion resistance |
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2017
- 2017-04-10 FR FR1753133A patent/FR3065011B1/en active Active
-
2018
- 2018-04-09 US US16/603,604 patent/US20210087665A1/en not_active Abandoned
- 2018-04-09 DE DE18724941.2T patent/DE18724941T1/en active Pending
- 2018-04-09 EP EP18724941.2A patent/EP3610047B1/en active Active
- 2018-04-09 WO PCT/FR2018/050886 patent/WO2018189471A1/en unknown
- 2018-04-09 BR BR112019021170-5A patent/BR112019021170B1/en active IP Right Grant
- 2018-04-09 CN CN201880024374.3A patent/CN110536972B/en active Active
- 2018-04-09 CA CA3058021A patent/CA3058021A1/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5032359A (en) | 1987-08-10 | 1991-07-16 | Martin Marietta Corporation | Ultra high strength weldable aluminum-lithium alloys |
US5198045A (en) | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
US7229509B2 (en) | 2003-05-28 | 2007-06-12 | Alcan Rolled Products Ravenswood, Llc | Al-Cu-Li-Mg-Ag-Mn-Zr alloy for use as structural members requiring high strength and high fracture toughness |
WO2007080267A1 (en) | 2005-12-20 | 2007-07-19 | Alcan Rhenalu | Sheet made of high-toughness aluminium alloy containing copper and lithium for an aircraft fuselage |
Non-Patent Citations (3)
Title |
---|
"Aluminum Standards and Data", THE ALUMINIUM ASSOCIATION, pages: 2.12,2.13 |
SUN BAO LONG ET AL: "Evolution of Microstructure and Properties of 2196 Al-Li Alloy Induced by Shot Peening", PROCEDIA ENGINEERING, ELSEVIER, AMSTERDAM, NL, vol. 81, 15 October 2014 (2014-10-15), pages 1043 - 1048, XP029078338, ISSN: 1877-7058, DOI: 10.1016/J.PROENG.2014.10.138 * |
TCHITEMBO GOMA FRANCK ARMEL ET AL: "Effect of extrusion aspect ratio and test temperatures on fatigue crack growth behavior of a 2099-T83 Al-Li a", INTERNATIONAL JOURNAL OF FATIGUE, vol. 59, 24 August 2013 (2013-08-24), pages 244 - 253, XP028771179, ISSN: 0142-1123, DOI: 10.1016/J.IJFATIGUE.2013.08.013 * |
Also Published As
Publication number | Publication date |
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CN110536972A (en) | 2019-12-03 |
FR3065011A1 (en) | 2018-10-12 |
BR112019021170B1 (en) | 2023-05-09 |
EP3610047A1 (en) | 2020-02-19 |
BR112019021170A2 (en) | 2020-04-28 |
CN110536972B (en) | 2022-01-25 |
US20210087665A1 (en) | 2021-03-25 |
EP3610047B1 (en) | 2023-08-23 |
DE18724941T1 (en) | 2020-06-04 |
FR3065011B1 (en) | 2019-04-12 |
CA3058021A1 (en) | 2018-10-18 |
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