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1. 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。

2. 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）。

3. 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。

4. 发明授权

US09096021B2 Method and shaping device for producing a composite fiber component for air and space travel 有权
标题翻译：用于生产用于空中和太空旅行的复合纤维部件的方法和成形装置
公开(公告)号：US09096021B2
公开(公告)日：2015-08-04
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 , B29C70/44 , B29C33/30 , B29C70/46 , B29C70/54 , B29D99/00 , B29K707/04 , B29L31/00 , B29L31/30
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 mold portion is provided in a method for producing a reinforced fiber composite component for aviation and aerospace. A forming/support element is molded by means of the mold portion of the forming tool. A semi-finished fiber product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fiber 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 fiber composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fiber composite component. A forming device is provided with a predefined mold 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。

5. 发明授权

US08920698B2 Production method for a workpiece composed of a fibre-composite material 有权
标题翻译：由纤维复合材料制成的工件的生产方法
公开(公告)号：US08920698B2
公开(公告)日：2014-12-30
申请号：US12310113
申请日：2007-05-04
申请人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
发明人： Peter Sander , Hans Marquardt , Hauke Lengsfeld
IPC分类号： B29C70/34 , B29C37/00 , B29C70/52
CPC分类号： B29C37/0075 , B29C70/34 , B29C70/525 , Y10T156/10 , Y10T428/24612 , Y10T428/24628 , Y10T442/10
摘要： The present invention relates to a production method for a workpiece (15) composed of a fibre-composite material, having the following steps: at least one support means (3) is provided. A main material (6) composed of a pre-impregnated fibre semi-finished product and/or of a secondary material (7) are/is applied to the at least one support means (3) in order to form at least two blank-mould areas (1, 10), in such a manner that at least one of the at least two blank-mould areas (1, 10) has the main material, and at least one of the blank-mould areas (1, 10) has the secondary material. The blank-mould areas (1, 10) are pressure-bonded to one another to form a workpiece blank (14) such that the at least one support means (3) is provided on a surface of the workpiece blank (14). The at least one support means (3) and the secondary material (7) are removed from the workpiece blank (14) in order to form the workpiece (15).
摘要翻译：本发明涉及一种由纤维复合材料构成的工件（15）的制造方法，其具有以下步骤：提供至少一个支撑装置（3）。将由预浸渍的纤维半成品和/或次级材料（7）组成的主要材料（6）施加到所述至少一个支撑装置（3），以便形成至少两个坯料 - 模具区域（1,10），使得至少两个坯料模具区域（1,10）中的至少一个具有主要材料，并且至少一个模坯区域（1,10）有二次材料。空白模具区域（1,10）彼此压合以形成工件坯件（14），使得至少一个支撑装置（3）设置在工件坯件（14）的表面上。为了形成工件（15），将至少一个支撑装置（3）和辅助材料（7）从工件坯件（14）上移除。

6. 发明申请

US20110308722A1 METHOD FOR JOINING PRECURED STRINGERS TO AT LEAST ONE STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT 有权
标题翻译：将先进的字符串连接到航空器或空间的至少一个结构部件的方法
公开(公告)号：US20110308722A1
公开(公告)日：2011-12-22
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： B32B37/10 , B32B37/14
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, including depositing covering vacuum films in advance at least on a predetermined region of each of the stringers to be joined, 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 in such a manner that a continuous vacuum arrangement, including 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 the continuous vacuum arrangement formed.
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，包括至少在要连接的每个桁条的预定区域上预先沉积覆盖真空膜，将桁条放置在至少一个结构部件，沉积和压制相应的真空薄膜条，使得每个条带连接到一对桁条，并且以这样的方式使用真空密封件存在于一对桁条之间，使得连续的真空装置包括覆盖真空形成薄膜和真空薄膜条，并且通过形成的连续真空装置将桁条加压连接到至少一个结构部件。

7. 发明申请

US20100015405A1 PRODUCTION METHOD FOR A WORKPIECE COMPOSED OF A FIBRE-COMPOSITE MATERIAL , AND A FIBRE-COMPOSITE COMPONENT IN THE FORM OF A PROFILE WITH A PROFILE CROSS SECTION WHICH VARIES OVER ITS LENGTH 有权
标题翻译：用于纤维复合材料组合的工件的生产方法，以及具有轮廓的剖面形式的纤维复合组分，其横截面长度超过其长度
公开(公告)号：US20100015405A1
公开(公告)日：2010-01-21
申请号：US12310113
申请日：2007-05-04
申请人： Michael Bechtold , Christian Nitsch , Peter Sander , Hans Marquardt , Hauke Lengsfeld
发明人： Michael Bechtold , Christian Nitsch , Peter Sander , Hans Marquardt , Hauke Lengsfeld
IPC分类号： B32B1/00 , B31B1/60 , D04G1/00 , B32B37/00
CPC分类号： B29C37/0075 , B29C70/34 , B29C70/525 , Y10T156/10 , Y10T428/24612 , Y10T428/24628 , Y10T442/10
摘要： The present invention relates to a production method for a workpiece (15) composed of a fibre-composite material, having the following steps: at least one support means (3) is provided. A main material (6) composed of a pre-impregnated fibre semi-finished product and/or of a secondary material (7) are/is applied to the at least one support means (3) in order to form at least two blank-mould areas (1, 10), in such a manner that at least one of the at least two blank-mould areas (1, 10) has the main material, and at least one of the blank-mould areas (1, 10) has the secondary material. The blank-mould areas (1, 10) are pressure-bonded to one another to form a workpiece blank (14) such that the at least one support means (3) is provided on a surface of the workpiece blank (14). The at least one support means (3) and the secondary material (7) are removed from the workpiece blank (14) in order to form the workpiece (15).
摘要翻译：本发明涉及一种由纤维复合材料构成的工件（15）的制造方法，其具有以下步骤：提供至少一个支撑装置（3）。将由预浸渍的纤维半成品和/或次级材料（7）组成的主要材料（6）施加到所述至少一个支撑装置（3），以便形成至少两个坯料 - 模具区域（1,10），使得至少两个坯料模具区域（1,10）中的至少一个具有主要材料，并且至少一个模坯区域（1,10）有二次材料。空白模具区域（1,10）彼此压合以形成工件坯件（14），使得至少一个支撑装置（3）设置在工件坯件（14）的表面上。为了形成工件（15），将至少一个支撑装置（3）和辅助材料（7）从工件坯件（14）上移除。

8. 发明授权

US08574391B2 Method for joining a profiled first structural component to a second structural component 失效
标题翻译：将成型的第一结构部件接合到第二结构部件的方法
公开(公告)号：US08574391B2
公开(公告)日：2013-11-05
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： B32B37/10
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。

9. 发明授权

US08146861B2 Component with carbon nanotubes 有权
标题翻译：碳纳米管组分
公开(公告)号：US08146861B2
公开(公告)日：2012-04-03
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： B64C1/10
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。

10. 发明申请

US20080083494A1 Method for joining precured or cured stringers to at least one structural component of an aircraft or spacecraft 有权
标题翻译：将预固化或固化的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：US20080083494A1
公开(公告)日：2008-04-10
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
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。

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