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11. 发明授权

US08734711B2 Method for producing a profile from composite fiber material 有权
标题翻译：从复合纤维材料制造型材的方法
公开(公告)号：US08734711B2
公开(公告)日：2014-05-27
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： B29C70/44
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。

12. 发明申请

US20110308714A1 METHOD AND SHAPING DEVICE FOR PRODUCING A COMPOSITE FIBRE COMPONENT FOR AIR AND SPACE TRAVEL 有权
标题翻译：用于生产用于空气和空间旅行的复合纤维部件的方法和形成装置
公开(公告)号：US20110308714A1
公开(公告)日：2011-12-22
申请号：US12989813
申请日：2009-03-13
申请人： Peter Sander , Hauke Lengsfeld , Hans Marquardt
发明人： Peter Sander , Hauke Lengsfeld , Hans Marquardt
IPC分类号： B29C70/08
CPC分类号： B29C70/44 , B29C33/30 , B29C70/443 , B29C70/46 , B29C70/54 , B29D99/0003 , B29D99/0014 , B29K2707/04 , B29L2031/003 , B29L2031/3076 , Y02T50/43
摘要： A forming tool with a predefined mould portion is provided in a method for producing a reinforced fibre composite component for aviation and aerospace. A forming/support element is moulded by means of the mould portion of the forming tool. A semi-finished fibre product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fibre product is deformed by means of the forming/support element to form at least one reinforcing portion. The forming/support element is then removed from the forming tool together with the reinforcing section formed on this element, followed by defined positioning of the reinforcing section thus formed with respect to an associated fibre composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fibre composite component. A forming device is provided with a predefined mould portion which holds a forming/support element such that it can be removed.
摘要翻译：在制造用于航空和航空航天的增强纤维复合材料部件的方法中提供了具有预定义的模具部分的成型工具。成形/支撑元件通过成形工具的模具部分模制。然后将半成品纤维产品至少部分沉积在成形/支撑元件上。沉积的半成品纤维产品通过成形/支撑元件变形以形成至少一个增强部分。然后将成形/支撑元件与形成在该元件上的加强部分一起从成形工具中移除，然后通过与成形/支撑元件的支撑相对于相关联的纤维复合部件部分形成的加强部分的定位。固化增强部分以形成增强纤维复合部件。成形装置设置有预定的模具部分，其保持成形/支撑元件，使得其可以被移除。

13. 发明授权

US07993479B2 Method for joining precured or cured stringers to at least one structural component of an aircraft or spacecraft 有权
标题翻译：将预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：US07993479B2
公开(公告)日：2011-08-09
申请号：US11904310
申请日：2007-09-26
申请人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
发明人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
IPC分类号： B29C65/00 , B32B37/00
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 precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement necessary for the joining is produced in two parts. In a first step, each precured stringer is covered in advance with a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Respective vacuum film strips are subsequently arranged on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.
摘要翻译：本发明涉及一种用于将预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。连接所需的真空布置分两部分。在第一步中，每个预固化的桁条预先用覆盖真空膜覆盖。以这种方式制备的桁条被布置在结构部件上。随后将各真空薄膜条布置在相邻的桁条上并在相邻桁条之间的中间空间上。通过使用真空密封装置，真空膜条和覆盖真空膜8形成连续的真空装置。随后使用该真空装置，将桁条随后在加压下结合到结构部件。

14. 发明申请

US20080083850A1 METHOD FOR JOINING A PROFILED FIRST STRUCTURAL COMPONENT TO A SECOND STRUCTURAL COMPONENT 失效
标题翻译：将第一个结构部件配置成第二个结构部件的方法
公开(公告)号：US20080083850A1
公开(公告)日：2008-04-10
申请号：US11904312
申请日：2007-09-26
申请人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
发明人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
IPC分类号： B64C1/00 , B64C1/06
CPC分类号： B29C66/001 , B29C65/02 , B29C65/48 , B29C65/483 , B29C66/1122 , B29C66/43441 , B29C66/47 , B29C66/721 , B29C66/82423 , B29C66/82661 , B29C70/443 , B29C2043/3644 , B29K2105/06 , B29L2031/3076 , Y02T50/43
摘要： The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement required for the joining is produced in two parts. In a first step, each precured stringer is covered in advance by a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Vacuum film strips are subsequently arranged in each case on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.
摘要翻译：本发明涉及一种用于将预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。连接所需的真空布置分两部分制造。在第一步中，每个预固化的桁条预先被覆盖的真空膜覆盖。以这种方式制备的桁条被布置在结构部件上。随后在相邻的桁条上并且在相邻的桁条之间的中间空间上，每个情况下布置真空薄膜带。通过使用真空密封装置，真空膜条和覆盖真空膜8形成连续的真空装置。随后使用该真空装置，将桁条随后在加压下结合到结构部件。

15. 发明授权

US08083976B2 Device and method 有权
标题翻译：设备和方法
公开(公告)号：US08083976B2
公开(公告)日：2011-12-27
申请号：US12548032
申请日：2009-08-26
申请人： Hauke Lengsfeld , Hans Marquardt
发明人： Hauke Lengsfeld , Hans Marquardt
IPC分类号： B29C70/18 , B29C53/48
CPC分类号： B29C70/504 , B29C70/542 , Y10T156/1007
摘要： The present invention provides a device, in particular within the aeronautical and aerospace fields, comprising a first and second tool and guide means, which guide the first and second tools in such a way that they press a preliminary fabric arranged in a pressing zone of the device along a second axis as said fabric moves along a first axis through the pressing zone, said second axis being substantially transverse to the first axis, so as to form a consolidated preliminary fabric, the guide means guiding the first and second tools parallel to one another, in part, along the first axis in the pressing zone.
摘要翻译：本发明提供了一种装置，特别是在航空和航空航天领域内，包括第一和第二工具和导向装置，该装置和引导装置以这样一种方式引导第一和第二工具，使得它们按压布置在当所述织物沿着第一轴线移动通过挤压区域时，所述第二轴线沿着第二轴线移动，所述第二轴线基本上横向于所述第一轴线，以便形成固结的预备织物，所述引导装置将所述第一和第二工具平行于一个另一个部分地沿着按压区域中的第一轴线。

16. 发明授权

US07771557B2 Method for joining a stringer to a structural component of an aircraft or spacecraft 有权
标题翻译：将桁条连接到飞行器或航天器的结构部件的方法
公开(公告)号：US07771557B2
公开(公告)日：2010-08-10
申请号：US11904311
申请日：2007-09-26
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： B64C1/12
摘要： The invention relates to a method for joining an uncured stringer to a structural component of an aircraft or spacecraft. The uncured stringer is supplied with at least one joining section and at least one web section. A rapidly curing low-temperature auxiliary material is deposited on web flanks of the at least one web section, which are to be supported. The at least one joining section of the uncured stringer is fitted to the structural component. Curing of the auxiliary material then takes place at a first curing temperature in order to form cured supporting elements for the web flanks of the at least one web section, which are to be supported. Curing of the uncured stringer is undertaken at a second curing temperature which is greater than the first precuring/curing temperature, and then the deposited and cured auxiliary material is removed.
摘要翻译：本发明涉及一种用于将未固化纵梁连接到飞行器或航天器的结构部件的方法。未固化的纵梁被提供有至少一个连接部分和至少一个腹板部分。快速固化的低温辅助材料沉积在待支撑的至少一个腹板部分的腹板侧面上。未固化纵梁的至少一个接合部分装配到结构部件上。辅助材料的固化然后在第一固化温度下进行，以便形成待支撑的至少一个纤维网部分的腹板侧面的固化的支撑元件。未硬化纵梁的固化在大于第一预固化/固化温度的第二固化温度下进行，然后去除沉积和固化的辅助材料。

17. 发明申请

US20100059169A1 DEVICE AND METHOD 有权
标题翻译：装置和方法
公开(公告)号：US20100059169A1
公开(公告)日：2010-03-11
申请号：US12548032
申请日：2009-08-26
申请人： Hauke Lengsfeld , Hans Marquardt
发明人： Hauke Lengsfeld , Hans Marquardt
IPC分类号： B29C70/18 , B29C53/48
CPC分类号： B29C70/504 , B29C70/542 , Y10T156/1007
摘要： The present invention provides a device, in particular within the aeronautical and aerospace fields, comprising a first and second tool and guide means, which guide the first and second tools in such a way that they press a preliminary fabric arranged in a pressing zone of the device along a second axis as said fabric moves along a first axis through the pressing zone, said second axis being substantially transverse to the first axis, so as to form a consolidated preliminary fabric, the guide means guiding the first and second tools parallel to one another, in part, along the first axis in the pressing zone.
摘要翻译：本发明提供了一种装置，特别是在航空和航空航天领域内，包括第一和第二工具和导向装置，该装置和引导装置以这样一种方式引导第一和第二工具，使得它们按压布置在当所述织物沿着第一轴线移动通过挤压区域时，所述第二轴线沿着第二轴线移动，所述第二轴线基本上横向于所述第一轴线，以便形成固结的预备织物，所述引导装置将所述第一和第二工具平行于一个另一个部分地沿着按压区域中的第一轴线。

18. 发明申请

US20090140098A1 COMPONENT WITH CARBON NANOTUBES 有权
标题翻译：碳纳米管组分
公开(公告)号：US20090140098A1
公开(公告)日：2009-06-04
申请号：US12260165
申请日：2008-10-29
申请人： Hauke Lengsfeld , Felix Caspar Helfrich , Hans Marquardt
发明人： Hauke Lengsfeld , Felix Caspar Helfrich , Hans Marquardt
IPC分类号： B64C1/00
CPC分类号： B64D45/02 , B64C1/12
摘要： The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component.
摘要翻译：本发明涉及具有树脂基质的组分，特别是涉及航空和航天领域的组分，其中嵌入碳纳米管用于组分的高导电性。

19. 发明申请

US20080083491A1 Method for joining a stringer to a structural component of an aircraft or spacecraft 有权
标题翻译：将桁条连接到飞行器或航天器的结构部件的方法
公开(公告)号：US20080083491A1
公开(公告)日：2008-04-10
申请号：US11904311
申请日：2007-09-26
申请人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
发明人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
IPC分类号： B29C65/48
CPC分类号： B64C1/12
摘要： The invention relates to a method for joining an uncured stringer to a structural component of an aircraft or spacecraft. The uncured stringer is supplied with at least one joining section and at least one web section. A rapidly curing low-temperature auxiliary material is deposited on web flanks of the at least one web section, which are to be supported. The at least one joining section of the uncured stringer is fitted to the structural component. Curing of the auxiliary material then takes place at a first curing temperature in order to form cured supporting elements for the web flanks of the at least one web section, which are to be supported. Curing of the uncured stringer is undertaken at a second curing temperature which is greater than the first precuring/curing temperature, and then the deposited and cured auxiliary material is removed.
摘要翻译：本发明涉及一种用于将未固化纵梁连接到飞行器或航天器的结构部件的方法。未固化的纵梁被提供有至少一个连接部分和至少一个腹板部分。快速固化的低温辅助材料沉积在待支撑的至少一个腹板部分的腹板侧面上。未固化纵梁的至少一个接合部分装配到结构部件上。辅助材料的固化然后在第一固化温度下进行，以便形成待支撑的至少一个纤维网部分的腹板侧面的固化的支撑元件。未硬化纵梁的固化在大于第一预固化/固化温度的第二固化温度下进行，然后去除沉积和固化的辅助材料。

20. 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。

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