EP4071258B1 - Manufacturing method of aircraft member - Google Patents

Manufacturing method of aircraft member Download PDF

Info

Publication number
EP4071258B1
EP4071258B1 EP21209865.1A EP21209865A EP4071258B1 EP 4071258 B1 EP4071258 B1 EP 4071258B1 EP 21209865 A EP21209865 A EP 21209865A EP 4071258 B1 EP4071258 B1 EP 4071258B1
Authority
EP
European Patent Office
Prior art keywords
extrusion
equal
atom
billet
temperature
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP21209865.1A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP4071258A1 (en
Inventor
Takayuki Takahashi
Hiroki Mori
Yoshihito Kawamura
Michiaki Yamasaki
Minami Sasaki
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Kumamoto University NUC
Original Assignee
Mitsubishi Heavy Industries Ltd
Kumamoto University NUC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd, Kumamoto University NUC filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP4071258A1 publication Critical patent/EP4071258A1/en
Application granted granted Critical
Publication of EP4071258B1 publication Critical patent/EP4071258B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C23/00—Alloys based on magnesium
    • C22C23/02—Alloys based on magnesium with aluminium as the next major constituent
    • 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
    • C22F1/06—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of magnesium or alloys based thereon

Definitions

  • the present disclosure relates to a manufacturing method of an aircraft member, in particular, a manufacturing method of a secondary structure member of an aircraft.
  • the magnesium alloy needs substantially the same manufacturing cost as an aluminum alloy and has specific strength greater than or equal to the aluminum alloy (see Japanese Patent Laid-Open No. 2008-536013 , Japanese Patent Laid-Open No. 2010-209452 ).
  • a magnesium alloy is an active metal and thus requires anti-corrosion treatment.
  • Japanese Patent Laid-Open No. 2008-536013 a non-chromate conversion coating is formed on the surface of the magnesium alloy to improve corrosion resistance.
  • Japanese Patent Laid-Open No. 2010-209452 discloses a magnesium alloy member having high corrosion resistance that does not require anti-corrosion treatment by defining the number and the size of fine precipitates containing both Mg and Al that are present in a surface layer region.
  • Japanese Patent Application Laid-Open No. 2008-536013 and Japanese Patent Application Laid-Open No. 2010-209452 are examples of the related art.
  • a material applied to an aircraft member is required to balance strength (tensile strength) and ductility (elongation).
  • Magnesium alloys have lower strength than aluminum alloys. Thus, it is required to improve the strength, but the strength of magnesium alloy is in a trade-off relationship with ductility, and it is difficult to balance the strength and the ductility.
  • a magnesium alloy member is manufactured by using a billet casted by using an ingot made of a magnesium alloy.
  • US2016369378 also discloses a magnesium alloy used in aircraft applications which is extruded and comprises a dispersion of (Mg,Al)2Ca.
  • the crystal grain diameter and the microstructure of a magnesium alloy are varied depending on processing conditions, and then the strength and the ductility of magnesium alloy are varied.
  • Fig. 5 illustrates a metallographic structure photograph of an Mg-Al-Ca-Si based alloy as an example. As illustrated in Fig. 5 , ⁇ -Mg (Al, Ca being dissolved into a solid solution), an Mg-Si-Ca compound, an (Mg, Al) 2 Ca compound (C36), and the like are included in the metallographic structure.
  • Fig. 6 illustrates a metallographic structure photograph of an Mg-Si-Ca compound.
  • Fig. 7 illustrates a metallographic structure photograph of an (Mg, Al) 2 Ca compound.
  • the present disclosure has been made in view of the above problems and intends to provide a manufacturing method that enables stable acquisition of a magnesium alloy member having both good strength and ductility regardless of a billet size.
  • the manufacturing method of an aircraft member of the present disclosure employs the following measures and as given in the claims.
  • the present disclosure provides a manufacturing method of an aircraft member to perform extrusion processing by using an Mg-Al-Ca based alloy containing an (Mg, Al) 2 Ca compound
  • the manufacturing method of an aircraft member includes: selecting a billet of an Mg-Al-Ca based alloy containing Al: greater than or equal to 6 atom% and less than or equal to 8 atom% and Ca: greater than or equal to 3 atom% and less than or equal to 4 atom%, optionally Mn: less than or equal to 0.3 atom% and optionally Si: less than or equal to 0.1 atom% with respect to the whole amount, the remaining part being Mg and unavoidable impurities; and extruding the billet under a condition where a temperature of the billet is maintained to be lower than a melting temperature of the (Mg, Al) 2 Ca compound, wherein the billet contains the (Mg, Al) 2 Ca compound by greater than or equal to 10 volume% and less than or equal to 35 volume%, the (Mg, Al) 2 Ca compound
  • a billet whose Al content and Ca content are within the above range is used, and extrusion processing conditions are optimized, so that an aircraft member having both good strength and ductility can be obtained more stably than in the conventional methods. Further, according to the manufacturing method of the present disclosure, an aircraft member that meets required incombustibility can be obtained.
  • a manufacturing method according to the present disclosure is suitable for manufacturing a secondary structure member for an aircraft.
  • the secondary structure member is a member installed in a primary structure member such as a stringer.
  • the secondary structure member is a clip, a bracket, a metal fitting used for fastening pipes, a seat frame, or the like.
  • the secondary structure member is not loaded as heavily as the primary structure member.
  • an aircraft member is extruded by using an Mg-Al-Ca based alloy billet including an (Mg, Al) 2 Ca compound (hereinafter, (Mg, Al) 2 Ca).
  • the extrusion processing is performed under a condition where the billet temperature is maintained to be lower than a melting temperature of the (Mg, Al) 2 Ca compound.
  • (Mg, Al) 2 Ca is dispersed in a metallographic structure.
  • the above Mg-Al-Ca based alloy (billet) is a casting manufactured by melt casting.
  • the cooling rate during billet casting is lower than or equal to 1000 K/sec, preferably, lower than or equal to 100 K/sec.
  • the diameter of the billet is greater than or equal to 29 mm and less than or equal to 180 mm.
  • the diameter of the billet may be greater than or equal to 69 mm.
  • an Mg-Al-Ca based alloy containing Al of greater than or equal to 6 atom% and less than or equal to 8 atom% and Ca of greater than or equal to 3 atom% and less than or equal to 4 atom% with respect to the whole amount is selected.
  • the Mg-Al-Ca based alloy may contain Mn of greater than 0 atom% and less than or equal to 0.3 atom%, preferably, greater than or equal to 0.01 and less than or equal to 0.05.
  • the remaining part of the Mg-Al-Ca based alloy (billet) is made of Mg. This not only means that the whole remaining part is made of Mg but also indicates that the remaining part may include impurities or other elements to the extent that does not affect the alloy characteristics.
  • the Mg-Al-Ca based alloy does not contain Si. This not only means that the Si content is 0 atom% but also indicates that Si may be unavoidably contained (for example, less than or equal to 0.1 atom%).
  • the above Mg-Al-Ca based alloy (billet) contains an (Mg, Al) 2 Ca compound.
  • (Mg, Al) 2 Ca is contained by greater than or equal to 10 volume% and less than or equal to 35 volume%, preferably, greater than or equal to 10 volume% and less than or equal to 30 volume%.
  • the melting temperature of (Mg, Al) 2 Ca is 490 degrees Celsius.
  • the melting temperature is derived from a phase diagram.
  • the billet temperature during extrusion processing may be maintained to be lower than the melting temperature by setting an extrusion temperature and an extrusion exit rate.
  • the "extrusion exit rate” is a rate at which a material is extruded from an extrusion mold (die) during extrusion molding.
  • a extrusion ratio may be higher than or equal to 10 and lower than or equal to 80.
  • the cross section of the extruded material may be an L-shape, a T-shape, or a Z-shape, for example.
  • the billet of the Mg-Al-Ca based alloy may be heat-treated at a temperature higher than or equal to 400 degrees Celsius and lower than or equal to 500 degrees Celsius for a period longer than or equal to one hour and shorter than or equal to six hours before extrusion processing.
  • the processing temperature is preferably higher than or equal to 450 degrees Celsius and lower than or equal to 500 degrees Celsius. More desirably, the processing time is made shorter, which is about one hour.
  • Billets were extruded under predetermined conditions, and the tensile strength (FTY) and the ductility (elongation/EL) of the obtained extruded material were measured.
  • FTY tensile strength
  • EL ductility
  • Fig. 1 and Table 1 illustrate measurement results.
  • the horizontal axis (x-axis) represents an extrusion temperature (degrees Celsius)
  • the vertical axis (y-axis) represents an extrusion exit rate Ve (m/min)
  • a circle (O) plot x: 375 degrees Celsius, y: 3.6 m/min
  • a circle plot x: 450 degrees Celsius, y: 0.9 m/min.
  • a colored portion on the right side of the above-described straight line in the sheet is a region of conditions where the material temperature during extrusion (billet temperature) exceeds 490 degrees Celsius.
  • Table 1 Extrusion material No. Extrusion condition Tensile strength (MPa) Ductility (%) Extrusion temperature (°C) Extrusion exit rate (m/min) 1 350 2.7 290 5.6 2 375 3.6 281 6.0 3 2.7 283 6.2 4 0.9 310 3.5 5 400 1.5 294 5.3 6 0.9 294 4.7 7 420 1.5 280 5.5 8 425 2.7 264 1.6 9 450 0.9 270 7.1
  • the extruded material (a cross (X) plot /extruded material No. 8) extruded under a condition where the billet temperature exceeds 490 degrees Celsius (the billet being melted) had tensile strength of 264 MPa and ductility of 1.6%.
  • all the extruded materials (circle plots /extruded materials No. 1 to 7, 9) extruded under a condition of a billet temperature at which no melting occurs (the temperature being maintained to be lower than the billet melting temperature) had tensile strength greater than or equal to 270 MPa and ductility greater than or equal to 3%.
  • Fig. 2 illustrates a range of preferable extrusion processing conditions suggested from the result of Fig. 1 .
  • the horizontal axis (x-axis) represents an extrusion temperature (degrees Celsius)
  • the vertical axis (y-axis) represents an extrusion exit rate Ve (m/min)
  • a long dashed double-short dashed line represents a preferable range
  • a shaded portion between the solid line and the long dashed double-short dashed line is a region that represents a more preferable range.
  • a colored portion on the right side of the above-described straight line in the sheet is a region of conditions where the material temperature during extru
  • the extrusion temperature is higher than or equal to 350 degrees Celsius, and the extrusion exit rate is higher than or equal to 0.3 m/min.
  • the extrusion temperature is lower than 350 degrees Celsius, the fluidity of the billet is deteriorated, which makes extrusion difficult.
  • the extrusion exit rate is lower than 0.3 m/min, it becomes difficult to perform rate control of the extrusion apparatus.
  • Fig. 3 and Table 2 illustrate results obtained by measuring the tensile strength (FTY) and the ductility (elongation/EL) of extruded materials obtained by performing extrusion processing by using billets whose Al and Ca contents are larger than values of the range defined in the present embodiment.
  • Extruded materials No. 12 to 23 were heated by using a heater, and the temperatures at the time of ignition were measured. The extrusion ratio during extrusion processing was 15. The measurement results are illustrated in Table 3.
  • Table 3 Extruded material No. Billet ( ⁇ 69mm) Composition Extrusion condition Ignition temperature (°C) Extrusion temperature (°C) Extrusion exit rate (m/min) Measurement result Average 12 Mg-8Al-4Ca-0.015Mn 375 3.6 1033 1038 13 1062 14 1020 15 Mg-8Al-4Ca-0.015Mn 450 0.9 1036 1039 16 1049 17 1032 18 Mg-6Al-3Ca 400 0.9 1080 1077 19 1075 20 1077 21 Mg-6Al-3Ca-0.05Mn 400 0.9 1017 1061 22 1082 23 1085 Reference : Elektron 43 845 869 865 898
  • salt water 5% NaCl
  • Fig. 4 illustrates results of the corrosion test.
  • the vertical axis represents a corrosion rate (mm/year), and a bar of each test piece represents an average value.
  • the corrosion rate (average) of Mg-10Al-5Ca was 0.75 mm/year.
  • the corrosion rate (average) of Mg-10Al-5Ca-0.015Mn was 0.125 mm/year. Accordingly, it was confirmed that the presence of Mn affects the corrosion rate.
  • the corrosion rate (average) of Mg-8Al-4Ca-0.015Mn containing Mn was also low such as 0.175 mm/year.
  • the corrosion rate (average) of Elektron 43 was 0.425 mm/year. It was confirmed that the Mg-Al-Ca based alloy containing Mn has a lower corrosion rate than Elektron 43.
  • the corrosion rate (average) of 7075-T6 was 0.15 mm/year. It was confirmed that the Mg-Al-Ca based alloy containing Mn has the same corrosion rate as 7075-T6.
  • a refrigerant, a design method of the same, and a freezing machine filled with the refrigerant described in the above embodiment are understood as follows, for example.
  • the present disclosure relates to a manufacturing method of an aircraft member to perform extrusion processing by using an Mg-Al-Ca based alloy containing (Mg, Al) 2 Ca.
  • a billet of an Mg-Al-Ca based alloy containing Al: greater than or equal to 6 atom% and less than or equal to 8 atom% and Ca: greater than or equal to 3 atom% and less than or equal to 4 atom% with respect to the whole amount is selected, and the billet is extruded under a condition where the temperature of the billet is maintained to be lower than a melting temperature of the (Mg, Al) 2 Ca.
  • the melting temperature of (Mg, Al) 2 Ca is 490 degrees Celsius.
  • the Mg-Al-Ca based alloy described above has less specific gravity than an aluminum alloy used in a conventional aircraft field. Therefore, the weight can be reduced by 10% or more as compared to an aluminum alloy member by processing such an Mg-Al-Ca based alloy into an aircraft member.
  • (Mg, Al) 2 Ca that is a C36 type compound is a hard compound.
  • (Mg, Al) 2 Ca is dispersed in a metallographic structure, high strength and relatively large ductility can be obtained.
  • the degree of dispersion of (Mg, Al) 2 Ca may be greater than or equal to 1 piece/ ⁇ m 2 . It is preferable that (Mg, Al) 2 Ca be fine (for example, less than or equal to 2 um).
  • Addition of Ca can improve the incombustibility and the mechanical property of the extruded material (aircraft member). If the Ca content is excessively high, this makes it difficult to obtain a solidified state of the magnesium alloy, and extrusion processing becomes difficult. If the Ca content is excessively low, it is not possible to obtain sufficient incombustibility.
  • Addition of Al can improve the mechanical property and the corrosion resistance of the extruded material. If the Al content is excessively high, it is not possible to obtain sufficient strength. If the Al content is excessively low, it is not possible to obtain sufficient ductility.
  • Increased contents of Al and Ca contained in an Mg-Al-Ca based alloy may become a factor of coarsening (Mg, Al) 2 Ca in a metallographic structure. If the (Mg, Al) 2 Ca is coarsened, the ductility of the extruded material is likely to be reduced. With the contents of Al and Ca being within the range described above, this may result in an extruded material having desired ductility.
  • the condition is set by an extrusion temperature and an extrusion exit rate, and with respect to a straight line connecting a first plot (x: 375 degrees Celsius, y: 3.6 m/min) to a second plot (x: 450 degrees Celsius, y: 0.9 m/min) in a graph of the x-y coordinate system where the x-axis represents the extrusion temperature (degrees Celsius) and the y-axis represents the extrusion exit rate (m/min), the extrusion temperature and the extrusion exit rate may be selected from values on the straight line or a range in which x and y are smaller than values on the straight line.
  • the temperature of the billet can be maintained to be lower than the melting temperature of the (Mg, Al) 2 Ca during extrusion processing. Coordinates of the first plot and the second plot are obtained by actual measurement, which are highly reliable. Therefore, an extruded material having both good tensile strength and ductility can be more stably manufactured than in the conventional materials.
  • the extrusion temperature in the condition be higher than or equal to 350 degrees Celsius. If the extrusion temperature is excessively low, the fluidity of the billet is reduced, which makes the extrusion difficult.
  • the extrusion exit rate in the condition be higher than or equal to 0.3 m/min.
  • the Mg-Al-Ca based alloy may contain Mn of greater than 0 atom% and less than or equal to 0.3 atom%.
  • Mn has an effect of improving the corrosion resistance even with a small amount.
  • the ductility of the extruded material is reduced in accordance with an increase in the addition amount.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Extrusion Of Metal (AREA)
EP21209865.1A 2021-04-09 2021-11-23 Manufacturing method of aircraft member Active EP4071258B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2021066471A JP7356116B2 (ja) 2021-04-09 2021-04-09 航空機部材の製造方法

Publications (2)

Publication Number Publication Date
EP4071258A1 EP4071258A1 (en) 2022-10-12
EP4071258B1 true EP4071258B1 (en) 2024-01-17

Family

ID=78770455

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21209865.1A Active EP4071258B1 (en) 2021-04-09 2021-11-23 Manufacturing method of aircraft member

Country Status (2)

Country Link
EP (1) EP4071258B1 (ja)
JP (1) JP7356116B2 (ja)

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3030338B1 (ja) * 1998-10-05 2000-04-10 工業技術院長 高強度難燃性マグネシウム合金の製造方法
US7695771B2 (en) 2005-04-14 2010-04-13 Chemetall Gmbh Process for forming a well visible non-chromate conversion coating for magnesium and magnesium alloys
JP4539572B2 (ja) * 2006-01-27 2010-09-08 株式会社豊田中央研究所 鋳造用マグネシウム合金および鋳物
JP2009119511A (ja) * 2007-11-16 2009-06-04 Sankyo Tateyama Aluminium Inc Ａｌ添加マグネシウム合金押出管材の製造方法
JP5289904B2 (ja) * 2008-11-18 2013-09-11 三協立山株式会社 マグネシウム合金押出形材の製造方法
JP2010209452A (ja) 2009-03-12 2010-09-24 Sumitomo Electric Ind Ltd マグネシウム合金部材
JP2010242146A (ja) * 2009-04-03 2010-10-28 Toyota Central R&D Labs Inc マグネシウム合金およびマグネシウム合金部材
JP2012097309A (ja) * 2010-10-29 2012-05-24 Sanden Corp マグネシウム合金部材、エアコン用圧縮機及びマグネシウム合金部材の製造方法
US10138535B2 (en) * 2013-10-23 2018-11-27 National University Corporation Kumamoto University Magnesium alloy and method of manufacturing same
JP6452042B2 (ja) * 2015-03-13 2019-01-16 三協立山株式会社 マグネシウム合金の製造方法
JP6667764B2 (ja) * 2015-09-24 2020-03-18 国立大学法人富山大学 マグネシウム合金及びそれを用いた鍛造品
JP2021063256A (ja) * 2019-10-11 2021-04-22 三菱重工業株式会社 航空機部材の製造方法
WO2021157748A1 (ja) * 2020-02-07 2021-08-12 国立大学法人 熊本大学 マグネシウム合金及びその製造方法

Also Published As

Publication number Publication date
JP7356116B2 (ja) 2023-10-04
EP4071258A1 (en) 2022-10-12
JP2022161560A (ja) 2022-10-21

Similar Documents

Publication Publication Date Title
EP3859045B1 (en) Highly corrosion-resistant plated steel sheet having excellent plating adhesion and resistance to liquid metal embrittlement
EP2431121B2 (en) High-strength aluminum alloy brazing sheet, and method of manufacturing such sheet
EP2578344B1 (en) Method for producing aluminum alloy heat exchanger
EP2127782B9 (en) Aluminum alloy casting material, method for production of the aluminum alloy casting material, aluminum alloy material, and method for production of aluminum alloy material
JP4535731B2 (ja) 静的機械的特性／耐損傷性の調和が向上したａｌ−ｚｎ−ｍｇ−ｃｕ合金製品
EP2634278A1 (en) Magnesium alloy having excellent ignition resistance and mechanical properties, and method for manufacturing same
EP2492365A2 (en) Flame retardant magnesium alloy with excellent mechanical properties, and preparation method thereof
EP2695959B2 (en) Method for the Production of an Aluminum Alloy Sheet that Exhibits Excellent Surface Quality After Anodizing
EP2832895B1 (en) Silver-based cylindrical target
EP2811042B1 (en) ALUMINiUM ALLOY forged MATERIAL AND METHOD FOR manufacturING the SAME
EP2738273B1 (en) Aluminum alloy sheet and method for manufacturing same
EP3733918B1 (en) Zinc alloy plated steel material having excellent corrosion resistance after being processed and method for manufacturing same
KR20230027312A (ko) 고강도 6xxx 시리즈 알루미늄 합금 및 그 제조 방법
EP3276019B1 (en) Magnesium-lithium alloy, rolled material formed from magnesium-lithium alloy, and processed article containing magnesium-lithium alloy as starting material
EP3208356B1 (en) Magnesium alloy, magnesium alloy plate, magnesium alloy member, and method for producing magnesium alloy
EP2453031B1 (en) Magnesium alloy plate
KR20120074037A (ko) 고온용 마그네슘 합금 및 그 제조 방법
EP3252181A1 (en) Magnesium-lithium alloy, rolled material and shaped article
KR102033820B1 (ko) 알루미늄 핀 합금 및 그 제조 방법
EP3488025B1 (en) Method for providing a zn-al-mg coating
US20140166165A1 (en) High-strength aluminum alloy extruded shape exhibiting excellent corrosion resistance, ductility, and hardenability, and method for producing the same
EP0365367B1 (en) Brazeable aluminum alloy sheet and process for its manufacture
EP3561098B1 (en) Magnesium alloy sheet and manufacturing method thereof
EP3399060A1 (en) Magnesium alloy having excellent mechanical properties and corrosion resistance, and method for manufacturing same
KR102178806B1 (ko) 마그네슘 합금 판재 및 이의 제조방법

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20221007

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20230731

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602021008704

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20240117

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1650563

Country of ref document: AT

Kind code of ref document: T

Effective date: 20240117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240517

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240418

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240417

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240117