专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08528865B2 Connecting arrangement for joining two stiffening elements having different cross-sectional profiles for an aircraft or spacecraft, and shell component 有权
标题翻译：用于连接用于飞行器或航天器和壳体部件的具有不同横截面轮廓的两个加强元件的连接装置
公开(公告)号：US08528865B2
公开(公告)日：2013-09-10
申请号：US12838950
申请日：2010-07-19
申请人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
发明人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T403/70
摘要： A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto.
摘要翻译：一种用于连接飞行器或航天器的两个增强元件的连接装置，其中所述加强元件具有不同的横截面轮廓，其具有至少一个脚部和至少一个梳齿部分，至少一个脚部连接元件可以在一侧适合于第一增强元件的脚部的几何形状，并且在相对侧上可以适应于第二增强元件的脚部的几何形状，并且可以刚性连接到其上; 并且至少一个梳状部分连接元件，其一侧可以适应于第一增强元件的梳理部分的几何形状，并且在相对侧上适合于第二增强元件的梳齿部分的几何形状，以及可以与其刚性连接。

2. 发明申请

US20110011980A1 CONNECTING ARRANGEMENT FOR JOINING TWO STIFFENING ELEMENTS HAVING DIFFERENT CROSS-SECTIONAL PROFILES FOR AN AIRCRAFT OR SPACECRAFT, AND SHELL COMPONENT 有权
标题翻译：连接安装有两个具有不同的跨部门轮廓的飞机或飞机组件和两个组件的安装元件
公开(公告)号：US20110011980A1
公开(公告)日：2011-01-20
申请号：US12838950
申请日：2010-07-19
申请人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
发明人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T403/70
摘要： A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with in each case at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto in each case.
摘要翻译：一种用于连接飞机或航天器的两个增强元件的连接装置，其中所述加强元件具有不同的横截面轮廓，在每种情况下具有至少一个脚部和至少一个梳状部分，至少一个脚部连接元件侧面可以适应于第一增强元件的脚部的几何形状，并且在相对侧可以适应于第二增强元件的脚部的几何形状并且可以刚性连接到其上; 并且至少一个梳状部分连接元件，其一侧可以适应于第一增强元件的梳理部分的几何形状，并且在相对侧上适合于第二增强元件的梳齿部分的几何形状，以及在每种情况下均可与其刚性连接。

3. 发明申请

US20100276069A1 METHOD AND DEVICE FOR THE PRODUCTION OF TUBULAR STRUCTURAL COMPONENTS 审中-公开
标题翻译：用于生产管状结构构件的方法和装置
公开(公告)号：US20100276069A1
公开(公告)日：2010-11-04
申请号：US12794487
申请日：2010-06-04
申请人： Hauke Lengsfeld , Volker Reye
发明人： Hauke Lengsfeld , Volker Reye
IPC分类号： B29C70/56 , B32B37/10
CPC分类号： B29C70/48 , B29C33/505 , B29C70/345 , B29C70/36 , B29C70/443 , B29C70/446 , B29C70/541 , B29D23/001 , B29K2105/089 , B29K2307/04 , B29L2023/22 , B29L2031/3082 , B30B5/02 , Y02T50/43
摘要： The present invention provides a method for the production of a tubular structural component. A tubular moulding tool having an inner mould surface which is shaped corresponding to an outer surface of the structural component is provided. A support surface of an expandable support which is formed such that in an unexpanded state, it fills the moulding tool, leaving an expansion spacing of the support surface to the mould surface, is covered with a tubular fibre-woven fabric. After the support has been arranged in the moulding tool, the fibre-woven fabric is pressed against the mould surface by expanding the support and is infiltrated by a curable matrix. From another point of view, a device is provided for the production of a tubular structural component.
摘要翻译：本发明提供一种生产管状结构部件的方法。提供一种具有对应于结构部件的外表面成形的内模表面的管状模制工具。可膨胀支撑件的支撑表面被形成为使得在未膨胀的状态下，其填充模制工具，留下支撑表面到模具表面的膨胀间隔被管状纤维织物覆盖。在支撑件已经被布置在模制工具中之后，通过膨胀支撑件将纤维织物压靠在模具表面上并被可固化基体渗入。另一方面，提供了一种用于生产管状结构部件的装置。

4. 发明授权

US08808493B2 Method for joining cured stringers to at least one structural component of an aircraft or spacecraft 有权
标题翻译：将固化桁条连接到飞行器或航天器的至少一个结构部件的方法
公开(公告)号：US08808493B2
公开(公告)日：2014-08-19
申请号：US13186027
申请日：2011-07-19
申请人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
发明人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
IPC分类号： B29C65/00
CPC分类号： B29C66/721 , B29C65/02 , B29C66/1122 , B29C66/474 , B29C66/532 , B29C66/61 , B29C66/73751 , B29C66/73753 , B29C66/7394 , B29C66/81455 , B29D99/0014 , B29K2105/06 , B29K2105/24 , B29L2031/3076 , B29L2031/766 , Y10T156/1089
摘要： The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.
摘要翻译：本发明涉及一种用于将固化桁条连接到飞行器或航天器的至少一个结构部件的方法，包括将桁条放置在至少一个结构部件上，沉积和压制相应的真空薄膜条，使得每个条带连接到一对的桁条，并且以这样的方式使用真空密封装置在一对桁条之间存在，从而形成包括覆盖真空膜和真空膜条的连续真空装置，并且将桁条加压至少至少通过形成连续的真空排列构成一个结构部件。

5. 发明授权

US08208148B2 Method for determining a characteristic parameter of a CRP specimen 有权
标题翻译：确定CRP试样的特征参数的方法
公开(公告)号：US08208148B2
公开(公告)日：2012-06-26
申请号：US12308013
申请日：2007-07-20
申请人： Hauke Lengsfeld , Peter Sander , Hans Marquardt , Rudolf Duwald
发明人： Hauke Lengsfeld , Peter Sander , Hans Marquardt , Rudolf Duwald
IPC分类号： G01N21/00
CPC分类号： G01N33/44 , G01N21/8914 , G01N21/9515 , G01N2021/8472
摘要： The invention relates to a method for determining at least one characteristic parameter of a CRP specimen (3, 4), in particular a specimen of prepreg material, for aerospace, comprising the following method steps: presenting the specimen (3, 4), irradiating the. specimen (3, 4) with a predetermined spectrum of electromagnetic radiation, recording the interaction between the specimen (3, 4) and the electromagnetic radiation in a data record (20) and determining the at least one characteristic parameter from the recorded data record (20).
摘要翻译：本发明涉及一种确定用于航空航天的CRP试样（3,4）特别是预浸料材料试样的至少一个特性参数的方法，包括以下方法步骤：将样品（3,4）照射的。在具有预定的电磁辐射光谱的样本（3,4）上记录样本（3,4）与数据记录（20）中的电磁辐射之间的相互作用，并根据记录的数据记录确定至少一个特性参数（ 20）。

6. 发明申请

US20120152461A1 METHOD FOR REINFORCING A FIBRE COMPOSITE COMPONENT AND A VACUUM MAT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBRE COMPOSITE COMPONENT 审中-公开
标题翻译：用于增强纤维复合组分的方法和用于生产增强纤维复合组分的真空垫和布置
公开(公告)号：US20120152461A1
公开(公告)日：2012-06-21
申请号：US13408660
申请日：2012-02-29
申请人： Christian Luebbering , Hauke Lengsfeld , Roland Brandenburg
发明人： Christian Luebbering , Hauke Lengsfeld , Roland Brandenburg
IPC分类号： B32B37/10
CPC分类号： B29C70/443 , B29C33/405 , B29C33/46 , B29C70/54 , B29K2063/00 , B29K2707/04
摘要： In a method for reinforcing a fibre composite component for aviation and space flight, a vacuum mat is configured with at least one receiving portion for reproducibly receiving at least one reinforcing element. The at least one reinforcing element is introduced into the at least one receiving portion of the vacuum mat. The vacuum mat with at least one introduced reinforcing element is applied reproducibly in a sealed manner to the fibre composite component to be reinforced to form a mould portion and at least the formed mould portion is cured to connect the at least one reinforcing element to the fibre composite component. The vacuum mat is then removed from the reinforced fibre composite component so that the vacuum mat can be reused.
摘要翻译：在用于加强用于航空和太空飞行的纤维复合材料部件的方法中，真空垫被构造成具有至少一个用于可重复地接收至少一个增强元件的接收部分。将至少一个增强元件引入到真空垫的至少一个接收部分中。具有至少一个引入的增强元件的真空垫以密封的方式可重复地施加到待加强的纤维复合材料部件上以形成模具部分，并且至少形成的模具部分被固化以将至少一个增强元件连接到纤维复合组件。然后将真空垫从增强纤维复合材料部件中取出，使真空垫可以重复使用。

7. 发明申请

US20100314807A1 METHOD FOR PRODUCING A PROFILE FROM COMPOSITE FIBER MATERIAL 有权
标题翻译：从复合纤维材料生产型材的方法
公开(公告)号：US20100314807A1
公开(公告)日：2010-12-16
申请号：US12808284
申请日：2008-11-07
申请人： Hauke Lengsfeld , Wolfgang Cruys , Roland Brandenburg , René Schroeder , Hans Marquardt
发明人： Hauke Lengsfeld , Wolfgang Cruys , Roland Brandenburg , René Schroeder , Hans Marquardt
IPC分类号： B29C43/10
CPC分类号： B29C70/44 , B29C43/3607 , B29C43/3642 , B29C70/443 , B29C70/46 , B29C70/543 , B29C2043/3644 , B29C2043/3649 , B29C2043/3655 , B29L2031/003
摘要： The present invention provides a method for producing a profile from composite fiber material, in particular in the aviation and aerospace field, having the following steps: A preliminary fabric, particularly made of pre-impregnated fiber material, is first packed in a vacuum bag. Then support elements are laid on the packed preliminary fabric to support the latter. The vacuum bag is then supplied with a vacuum. Next, the preliminary fabric is hardened to the profile under the action of heat, in particularly in an autoclave. With the claimed method the support elements can be formed advantageously from favorable material, in particular aluminum, instead of highly expensive nickel-36 steel, since the support elements are uncoupled mechanically from the preliminary fabric in a longitudinal direction by means of the vacuum bag, enabling movement of the support elements in the longitudinal direction relative to the preliminary fabric.
摘要翻译：本发明提供了一种从复合纤维材料特别是在航空和航天领域制造型材的方法，其具有以下步骤：将预先特别由预浸纤维材料制成的初步织物首先包装在真空袋中。然后将支撑元件放置在包装的初步织物上以支撑后者。然后将真空袋提供真空。接下来，预热织物在热的作用下，特别是在高压釜中硬化到轮廓。根据要求保护的方法，由于支撑元件通过真空袋在纵向上与预备织物机械地脱离，所以可以有利地由有利的材料，特别是铝代替高度昂贵的镍-36钢形成支撑元件，使得支撑元件能够相对于预备织物在纵向方向上移动。

8. 发明申请

US20100200156A1 METHOD AND TOOL FOR PRODUCING A T-STRINGER 失效
标题翻译：用于生产T-STRINGER的方法和工具
公开(公告)号：US20100200156A1
公开(公告)日：2010-08-12
申请号：US12667780
申请日：2008-06-17
申请人： Hauke Lengsfeld , Christian Luebbering
发明人： Hauke Lengsfeld , Christian Luebbering
IPC分类号： B29C70/46 , B29C70/42
CPC分类号： B29C70/462 , B64C1/064 , Y02T50/43 , Y10T156/1049
摘要： The present invention provides a method as well as a tool (1, 48) for producing a T-stringer, in particular in the aircraft and spacecraft sector. The method is characterized by two lay-up strips (3, 4) being arranged on top of one another, wherein areas (5, 6) of the lay-up strips (3, 4) corresponding to the stringer foot (60) that is to be formed, are spaced apart from one another by means of separation films (7, 8) and areas (14, 15) of the lay-up strips (5, 6) corresponding to a stringer web (61) come into direct contact with one another, in particular, forming a material bond. In a further method step, the lay-up strips (3, 4) are clamped at the areas (14, 15) corresponding to the stringer web (61) that is to be formed. In an even further step, the areas (5, 6) corresponding to the stringer foot (60) that is to be formed are folded open in opposite directions (28, 29) by means of a folding-open mandrel (25), and by means of a pressing roller (37) the areas (5, 6) are pressed against corresponding pressing surfaces (23, 24) of the clamping device (1) such that the areas (23, 24) are properly flush. Finally, the folded lay-up strips (3, 4) are cured to form the T-stringer that is to be produced. The method according to the invention has the advantage over the known method for producing T-stringers that a smaller number of steps is required to produce the T-stringer and can be automated easily.
摘要翻译：本发明提供了一种方法以及特别是在飞行器和航天器领域中用于制造T型纵梁的工具（1,48）。该方法的特征在于两个布置在彼此顶部的叠置条（3,4），其中对应于桁条脚（60）的叠置条（3,4）的区域（5,6），其中通过分离膜（7,8）彼此间隔开，并且对应于桁条网（61）的叠层条（5,6）的区域（14,15）直接形成彼此接触，特别是形成材料粘合。在另一种方法步骤中，铺设条（3,4）被夹紧在对应于待形成的纵梁腹板（61）的区域（14,15）处。在另一步骤中，通过折叠打开的心轴（25）将对应于待形成的纵梁（60）的区域（5,6）以相反方向（28,29）打开，并且通过加压辊（37）将区域（5,6）按压在夹紧装置（1）的相应的压紧表面（23,24）上，使得区域（23,24）适当地齐平。最后，折叠的叠置条（3,4）被固化以形成要被制造的T形纵梁。根据本发明的方法具有优于用于生产T型机的已知方法的优点，即需要较少数量的步骤来生产T型钢丝绳并且可以容易地自动化。

9. 发明授权

US09393746B2 Method and a device for the preparation of a dry textile preform 有权
标题翻译：用于制备干织物预制件的方法和装置
公开(公告)号：US09393746B2
公开(公告)日：2016-07-19
申请号：US13823496
申请日：2011-09-15
申请人： Christian Luebbering , Hauke Lengsfeld
发明人： Christian Luebbering , Hauke Lengsfeld
IPC分类号： B29C70/56 , B29B11/16 , B29C51/16 , B29C51/26 , B29C70/44 , B29C70/02
CPC分类号： B29C70/56 , B29B11/16 , B29C51/16 , B29C51/262 , B29C70/02 , B29C70/443
摘要： A method for the preparation of a dry textile preform for a large surface area fiber-reinforced composite component, in which resin-free textile material layers for purposes of manufacturing the preform are tensioned in each case in a tensioning frame, and in the stretched state are laid down on a moulding body by means of a linear relative movement between the tensioning frame and the moulding body. Also disclosed is a device for the execution of a method of this type with a tensioning frame for purposes of tensioning the material layers, and with a clamping unit for purposes of fixing the laid-down material layers on a moulding body.
摘要翻译：一种用于制备用于大面积纤维增强复合材料部件的干织物预制品的方法，其中用于制造预成型件的无树脂的纺织材料层在每种情况下在张紧框架中张紧，并处于拉伸状态通过在张紧框架和成型体之间的线性相对运动而放置在成型体上。还公开了一种用于执行这种类型的方法的装置，其具有用于张紧材料层的张紧框架，以及用于将铺放材料层固定在成型体上的夹紧单元。

10. 发明授权

US09149990B2 Apparatus for the forming of a lay-up of fibre composite material 有权
标题翻译：用于形成纤维复合材料层叠的装置
公开(公告)号：US09149990B2
公开(公告)日：2015-10-06
申请号：US12080019
申请日：2008-03-31
申请人： Hauke Lengsfeld , Olaf Rocker , Rainer Graeber
发明人： Hauke Lengsfeld , Olaf Rocker , Rainer Graeber
IPC分类号： B28B7/42 , B29C70/30 , B29C33/04 , B29C33/06 , B29C35/02 , B29C33/02 , B29C33/30 , B29C35/04 , B29C35/08
CPC分类号： B29C70/30 , B29C33/02 , B29C33/04 , B29C33/06 , B29C33/30 , B29C35/02 , B29C35/041 , B29C2035/0811 , B29C2035/0855
摘要： An apparatus for the forming of a lay-up of fiber composite material, in particular in the aerospace sector is provided. In this case, the apparatus has at least one forming tool, which has a surface contour corresponding to a desired geometry of the lay-up after the forming, and a tool carrier, to which the at least one forming tool is releasably fastened. From a further viewpoint, the invention makes available an apparatus with a modular structure, it then being possible for any desired forming tools to be combined with the tool carrier according to requirements. This leads in particular to less laborious handling, since it obviates the need for handling of the comparatively large tool carrier.
摘要翻译：提供了一种用于形成纤维复合材料层叠装置，特别是在航空航天领域。在这种情况下，该装置具有至少一个成形工具，该成形工具具有对应于成形后的叠层的期望几何形状的表面轮廓，以及刀具架，至少一个成形工具可释放地紧固到该工具托架上。从另一个观点来看，本发明提供了一种具有模块化结构的装置，然后可以根据需要将任何所需的成形工具与工具架组合。这特别导致更少的处理费用，因为它消除了处理相对较大的工具架的需要。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式