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

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。

4. 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。

5. 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。

6. 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。

7. 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。

8. 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。

9. 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。

10. 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。

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