CN101119839A - 用于弯曲件的加衬模具的工艺和工具 - Google Patents
用于弯曲件的加衬模具的工艺和工具 Download PDFInfo
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- CN101119839A CN101119839A CNA2005800453890A CN200580045389A CN101119839A CN 101119839 A CN101119839 A CN 101119839A CN A2005800453890 A CNA2005800453890 A CN A2005800453890A CN 200580045389 A CN200580045389 A CN 200580045389A CN 101119839 A CN101119839 A CN 101119839A
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- 238000000034 method Methods 0.000 title abstract description 6
- 230000006978 adaptation Effects 0.000 claims abstract 2
- 238000005516 engineering process Methods 0.000 claims description 14
- 238000009434 installation Methods 0.000 claims description 2
- 150000001875 compounds Chemical class 0.000 claims 1
- 239000000463 material Substances 0.000 description 10
- 239000000203 mixture Substances 0.000 description 4
- 239000000835 fiber Substances 0.000 description 3
- 239000003054 catalyst Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003112 inhibitor Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/12—Surface bonding means and/or assembly means with cutting, punching, piercing, severing or tearing
- Y10T156/1348—Work traversing type
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/17—Surface bonding means and/or assemblymeans with work feeding or handling means
- Y10T156/1788—Work traversing type and/or means applying work to wall or static structure
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- Engineering & Computer Science (AREA)
- Robotics (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
- Coating Apparatus (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Braking Arrangements (AREA)
Abstract
本发明涉及一种对用于弯曲件的模具的加衬的工艺和工具,该工艺包括:以连续几遍的形式施加宽度为A2的衬里(15)在模具(3)上,在其上施加压力以使其适合所述弯曲件的曲率,所述遍的次数是最小需求的次数,由此带(15)的宽度A2允许实现这种适应,工具包括施加衬里(15)的鼓(25),在每一遍的开始时将它的末端连接到模具(3)上的装置,在衬里(15)上沿着它的整个宽度均匀施加压力的圆锥形辊(25),和通过安置在模具(3)上的边侧引导件(27、28)而使其可以运动的部件(26、29),所述模具(3)平行于划定所述弯曲件的曲线(5、7)。
Description
技术领域
本发明涉及一种应用于航空工业中的弯曲件的加衬模具的工艺和工具。
背景技术
加衬(lining)是一种以衬里的形式将由强化组合物形成的层放置到模具上的工艺。在航空工业中普遍使用的组合物的例子是预浸渍组合物,其是一种纤维强化物和用于生产组合物的聚合物基体的混合物,以此其可以被储存以备以后使用。
它可以是片、衬里、绳或织物的形式。对于热固性基体来说,树脂通常是部分固化或用另外一种方法进行处理至所控制的粘度,即所谓的B-阶段(B-stage)。添加剂如火焰催化剂(flame catalysts)、抑制剂和延缓剂可以被加入以在最终应用中得到特殊性能并改善加工、储存和处理特点。
在该工艺中,衬里不是任意排列的,但是它们通常以一定的方向排列或放置,特别是以0度、90度、45度和-45度放置。层的数量(厚度)和衬里在特定的方向上或者在其他方向上的布置根据所述弯曲件在各个点支撑的应力的属性和大小来决定。
有两种衬里:平面形的和弯曲形的,分别根据被加衬的表面是平面形状或弯曲形状而定。
加衬过程可以通过手工或自动来执行。执行加衬的机械基本上有两种形式:
-加衬机械:在平面或稍微弯曲的表面上加衬。
-纤维定位机械:在加衬机械不能加衬的大曲率表面上加衬。
有主要两个准则确定是否一部分用手工或自动加衬:所使用的材料和所述弯曲件的尺寸。
除了其它材料之外应用到加衬上的一个材料是预浸渍材料。这种材料是粘性的并且它的处理不简单。手工配装预浸渍衬至平面上包含的直线不是非常的复杂,然而将此种衬配装至曲面是非常复杂的,因为这种材料自身不能变形,所以操作人员必须在衬上施加恒定压力使其变形并适应所要求的曲面,并因为衬里是粘性的增加了困难。此外,如果被放置的衬里的数量非常高,表面上增加了复杂性。
本发明的产生是根据对新的空中客车A380飞机的部件加衬的需要,其在平面上承载的、用倾斜的面对圆柱体截面所获得一个椭圆形。
在一个制造试验中,能够看出,对于给定的被加衬的曲面几何形状和被排列的层的教高的数量,手工为模具加衬是非常复杂的。
加衬也可以用加衬机械来执行。在这些情况下,对于给定的模具尺寸,首先加衬大面积,随后其继续进行切割操作以确定上述的曲面。因为机械没有被最优地使用,这个方法并不是成本有效的。
本发明致力于克服所提到的、所述弯曲件的手工加衬和非成本有效的加衬或纤维定位机械所遇到的困难。
发明内容
本发明提供一种可以令人满意的解决上述讨论的问题的工艺和工具,特别是针对在航空工业上需要的大件的情况。
当试图用单个衬里为一个平面模具加衬来形成一个给定宽度的弯曲件时,要考虑的基本问题是,如果加衬材料不能自己变形,那么衬里不能精确跟随曲线的几何形状,就像在将被使用的、所需的预浸渍加衬的情况。
为了解决这种问题,本发明提出一种工艺,包括应用一定宽度的连续几遍(passes)的衬里,这样,通过在其上施加压力,它适应将被成型的弯曲件的曲率并且所述遍数是需要达到这种适合所需的最小值,在每一遍中所应用的衬里被连接起来。
换句话说,被加衬的区域以一定的宽度被分成不同的区域,所述宽度允许正确地布置顺应曲面的几何形状的衬里。该宽度根据曲率和被加衬区域的总宽度,通过合适的试验加以确定,考虑到需要施加压力到材料上,所以它发生变形并可以适合曲面的几何形状。
本发明也提出一种执行以上讨论的工艺的工具,包括以下基本要素:
-施加衬里的鼓,具有在必须对整个区域进行加衬的遍数相同数目的布置位置。
-在每-遍开始时斜衬里的末端连接到模具的装置。
-一旦衬里沿模具的整个宽度被均匀地施加到模具上、在衬里上施加压力的圆锥形辊;
-通过安装在模具上的侧引导件、使工具移动的装置,其平行于划分所述弯曲件的曲线。
本发明的其它特点和优点将从随后的对目的的示例的详细说明并结合附图得到理解。
附图说明
图1示出被加衬区域的几何特点。
图2示出依靠本发明解决的问题。
图3示出根据本发明的加衬工艺。
图4示出根据本发明的加衬工具。
具体实施方式
本发明的工艺和工具的目标是对模具3上的由曲线5和7划分的以形成应用在飞机结构中的件的区域进行加衬。
因为附图不是按比例表示这个区域,必须指出为了更好的理解本发明,在一个特定的实施例中,尺寸L和H的数值是2240mm和170mm,其目的是说明它们的几何特点。
如图2中所示,用宽度为W的衬里试图使其适合曲率时将出现不希望的折痕(folds)13。
根据本发明和如图3所示,宽度为A2的衬里15以连续几遍来施加。
衬里15的最大宽度是根据区域3的曲率从而使得衬里可以顺应所述曲面被安置,总是在材料上施加压力以使其变形。需要对整个区域进行加衬的遍数是根据最大宽度而决定的,其将最终决定衬里15的宽度A2使得其覆盖宽度为A1的整个区域3。
衬里15可以包括在其应用到模具上时必须被除去的保护部件。
在随后的图4中,可以看到根据本发明提出的工具包括应用衬里的鼓23和一个在其上施加压力的圆锥形的辊25。该工具在侧引导件27、28上的轮子26上移动,该引导件被定位于模具上平行于划分片材的曲线5、7(考虑到图4的示意性、在该图中用直线表示)。工具的运动通过致动牵引件29而手动执行。
衬里15缠绕在衬里供给鼓23上,包括一个摩擦离合器以总是保持衬里的应力。
供给鼓23有衬里15卷状物的三个安置位置31、33、35,以使其在三遍中的每一遍中施加到三个区域37、39、41。
鼓23与压力辊25刚性连接并在离地一小段距离保持悬浮,因此当在衬里15上施加压力时它不受影响。
压力辊25是圆锥形的,由此当其在内曲线7和外曲线5上前进时,其在衬里的整个宽度上均匀施加压力。辊25有对应于鼓23上31、33、35位置的三个支承区域并在每一遍中保证,被安置的衬里的绑定与前面一次中的布置是对齐的。
工具包括在每一遍中用于连接衬里的末端到模具从而方便它的安置的部件(没有示出)。
如果使用具有保护部件的衬里的情况下,工具将有便于除去它的部件。
任何对以下权利要求定义的范围内的修改能够被引入以上描述的优选实施例中。
Claims (6)
1.一种工艺,用于以加衬形式通过将自身不变形的复合物施加到平面模具(3)上,以形成由两个平行曲线(5、7)划定的、宽度为A1的件,其特征在于,所述工艺包括:在模具(3)上以连续几遍施加宽度为A2的衬里(15),由此每个衬里与前一遍的衬里横向绑定,在衬里(15)上施加压力,从而所述衬里适应于所述件的曲率,所述遍数是宽度为A2的衬里(15)以允许实现这种适应的最小所需遍数。
2.根据权利要求1所述的工艺,其特征在于衬里(15)包括一个当其施加到模具(3)上时被除去的保护部件。
3.一种实施权利要求1-2所述的工艺的工具,其特征在于所述工具包括:
a)施加衬里(15)的鼓(23),其安置位置(31、33、35)具有与必须给予对模具加衬的遍数相同的数目;
b)在每一遍开始时将衬里(15)的末端连接到模具(3)的装置;
c)圆锥形辊(25),一旦应用到模具(3)上,在衬里(15)上沿着它的整个宽度均匀施加压力;和
d)通过设置在模具(3)上的侧引导件(27、28)而使其可以运动的装置(26、29),该侧引导件平行于划分所述件的曲线(5、7)。
4.根据权利要求3所述的工具,其特征在于,用于施加衬里(15)的鼓(23)包括一个保持衬里(15)的应力的摩擦离合器。
5.根据权利要求3所述的工具,其特征在于,所述工具包括去除衬里(15)的保护部件的装置。
6.根据权利要求3所述的工具,其特征在于,施加衬里的鼓(23)与压力辊(25)刚性绑定,并安置与模具(3)的表面有一小段距离以方便压力辊(25)的致动。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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ES200403147A ES2267367B1 (es) | 2004-12-30 | 2004-12-30 | Procedimiento y util para el encintado de moldes de piezas curvas. |
ES200403147 | 2004-12-30 | ||
PCT/EP2005/057213 WO2006070015A1 (en) | 2004-12-30 | 2005-12-29 | Process and tooling for lining molds of curved pieces |
Publications (2)
Publication Number | Publication Date |
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CN101119839A true CN101119839A (zh) | 2008-02-06 |
CN101119839B CN101119839B (zh) | 2011-06-08 |
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CN2005800453890A Expired - Fee Related CN101119839B (zh) | 2004-12-30 | 2005-12-29 | 用于弯曲件的加衬模具的工艺和工具 |
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US (1) | US8074692B2 (zh) |
EP (1) | EP1830999B1 (zh) |
JP (1) | JP4984256B2 (zh) |
CN (1) | CN101119839B (zh) |
AT (1) | ATE403538T1 (zh) |
BR (1) | BRPI0518541A2 (zh) |
CA (1) | CA2594207C (zh) |
DE (1) | DE602005008771D1 (zh) |
ES (2) | ES2267367B1 (zh) |
RU (1) | RU2395393C2 (zh) |
WO (1) | WO2006070015A1 (zh) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8632653B2 (en) | 2005-05-03 | 2014-01-21 | The Boeing Company | Method of manufacturing curved composite structural elements |
US8932423B2 (en) | 2008-04-17 | 2015-01-13 | The Boeing Company | Method for producing contoured composite structures and structures produced thereby |
US9090028B2 (en) | 2008-04-17 | 2015-07-28 | The Boeing Company | Method for producing contoured composite structures and structures produced thereby |
US8349105B2 (en) | 2008-04-17 | 2013-01-08 | The Boeing Company | Curved composite frames and method of making the same |
US9278484B2 (en) | 2008-04-17 | 2016-03-08 | The Boeing Company | Method and apparatus for producing contoured composite structures and structures produced thereby |
ES2400131B1 (es) * | 2011-05-27 | 2014-04-29 | Airbus Operations S.L. | Metodo de apilado para componentes no planos de material compuesto |
CN105121138B (zh) * | 2013-02-08 | 2018-04-24 | Lm Wp 专利控股有限公司 | 用于制造物品的系统和方法 |
US10399283B2 (en) * | 2015-10-06 | 2019-09-03 | The Boeing Company | Method and device for producing contoured composite laminate stiffeners with reduced wrinkling |
DK3830324T3 (da) * | 2018-08-01 | 2022-12-05 | Albany Eng Composites Inc | Kurvet præform og fremgangsmåde til fremstilling deraf |
Family Cites Families (11)
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US3574040A (en) * | 1967-06-29 | 1971-04-06 | Gen Dynamics Corp | Apparatus for making laminated structural shapes by the controlled detrusive placement and polymerization of tectonic filamentous tapes |
US3810805A (en) * | 1972-04-14 | 1974-05-14 | Goldsworthy Eng Inc | Geodesic path length compensator for composite-tape placement head |
US4461669A (en) * | 1983-09-30 | 1984-07-24 | The Boeing Company | Pivotal mount for laminating head |
US4696707A (en) * | 1987-08-18 | 1987-09-29 | The Ingersoll Milling Machine Company | Composite tape placement apparatus with natural path generation means |
FR2635484B1 (fr) * | 1988-08-18 | 1991-04-05 | Aerospatiale | Procede et dispositifs de fabrication de pieces planes incurvees en materiau composite |
US5394906A (en) * | 1993-02-10 | 1995-03-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and apparatus for weaving curved material preforms |
US5431749A (en) * | 1993-09-30 | 1995-07-11 | The Ingersoll Milling Machine Company | Tape laying head with curved tape laying capability and improved adaptive steering |
US5662855A (en) * | 1994-05-17 | 1997-09-02 | The B.F. Goodrich Company | Method of making near net shaped fibrous structures |
US6451152B1 (en) * | 2000-05-24 | 2002-09-17 | The Boeing Company | Method for heating and controlling temperature of composite material during automated placement |
US6799081B1 (en) * | 2000-11-15 | 2004-09-28 | Mcdonnell Douglas Corporation | Fiber placement and fiber steering systems and corresponding software for composite structures |
FR2869330B1 (fr) * | 2004-04-23 | 2006-07-21 | Messier Bugatti Sa | Procede de fabrication de nappe fibreuse bidimensionnelle helicoidale |
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2004
- 2004-12-30 ES ES200403147A patent/ES2267367B1/es not_active Expired - Fee Related
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2005
- 2005-12-29 US US11/794,001 patent/US8074692B2/en not_active Expired - Fee Related
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- 2005-12-29 AT AT05823706T patent/ATE403538T1/de not_active IP Right Cessation
- 2005-12-29 EP EP05823706A patent/EP1830999B1/en not_active Not-in-force
- 2005-12-29 RU RU2007128908/12A patent/RU2395393C2/ru not_active IP Right Cessation
- 2005-12-29 BR BRPI0518541-6A patent/BRPI0518541A2/pt not_active IP Right Cessation
- 2005-12-29 CN CN2005800453890A patent/CN101119839B/zh not_active Expired - Fee Related
- 2005-12-29 JP JP2007548828A patent/JP4984256B2/ja not_active Expired - Fee Related
- 2005-12-29 DE DE602005008771T patent/DE602005008771D1/de active Active
- 2005-12-29 WO PCT/EP2005/057213 patent/WO2006070015A1/en active Search and Examination
Also Published As
Publication number | Publication date |
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EP1830999B1 (en) | 2008-08-06 |
ATE403538T1 (de) | 2008-08-15 |
JP2008532790A (ja) | 2008-08-21 |
RU2395393C2 (ru) | 2010-07-27 |
EP1830999A1 (en) | 2007-09-12 |
CA2594207C (en) | 2012-10-30 |
ES2312043T3 (es) | 2009-02-16 |
ES2267367B1 (es) | 2009-05-01 |
WO2006070015A1 (en) | 2006-07-06 |
CN101119839B (zh) | 2011-06-08 |
ES2267367A1 (es) | 2007-03-01 |
RU2007128908A (ru) | 2009-02-10 |
US20090020219A1 (en) | 2009-01-22 |
CA2594207A1 (en) | 2006-07-06 |
US8074692B2 (en) | 2011-12-13 |
DE602005008771D1 (de) | 2008-09-18 |
BRPI0518541A2 (pt) | 2008-11-25 |
JP4984256B2 (ja) | 2012-07-25 |
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