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. 发明申请

US20120208005A1 USE OF INORGANIC PARTICLES TO PRODUCE A BARRIER LAYER ON AIRCRAFT COMPONENTS 审中-公开
标题翻译：使用无机颗粒在飞机组件上生产障碍层
公开(公告)号：US20120208005A1
公开(公告)日：2012-08-16
申请号：US13456549
申请日：2012-04-26
申请人： Peter Turanski , Heinz-Peter Busch , Berend Schoke , Wilko Östereich
发明人： Peter Turanski , Heinz-Peter Busch , Berend Schoke , Wilko Östereich
IPC分类号： B32B5/16 , B29C65/14
CPC分类号： C08J5/24 , B29C70/585 , B32B3/12 , B32B5/02 , B32B5/024 , B32B29/02 , B32B2250/40 , B32B2255/02 , B32B2255/20 , B32B2260/021 , B32B2260/046 , B32B2264/104 , B32B2307/306 , B32B2307/3065 , B32B2605/003 , B32B2605/18 , Y02T50/43 , Y10T428/251
摘要： The present invention relates to a plastics material component for an aircraft, comprising (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica.
摘要翻译：本发明涉及一种用于飞行器的塑料材料部件，其包括（i）基底，其包括一种或多种热固性塑料材料，和（ii）施加到基底上的一层或多层，至少一层S1包括云母

2. 发明申请

US20110042515A1 ARRANGEMENT FOR PROVIDING ACTIVE FIRE PROTECTION IN AIRCRAFT 审中-公开
标题翻译：在飞机上提供主动火警保护的安排
公开(公告)号：US20110042515A1
公开(公告)日：2011-02-24
申请号：US12935716
申请日：2009-02-11
申请人： Berend Schoke , Heinz-Peter Busch
发明人： Berend Schoke , Heinz-Peter Busch
IPC分类号： A62C3/08 , A62C2/06
CPC分类号： A62C2/065 , A62C2/247 , A62C3/08
摘要： The invention relates to an arrangement for providing active fire protection in aircraft by means of at least one protective shield. According to the invention, the at least one protective shield is formed with an intumescent material, which in the event of a fire can be activated, in particular made to expand, in a controlled manner well below the initial temperature otherwise usual for intumescent materials of the order of 250° C. by means of an electrical heating device. The current temperature in the hold (preferably at various temperature measuring points) of the aircraft is measured by means of at least one temperature sensor and transmitted to a controlling and regulating device. In the event of a fire, the heating devices are activated and the intumescent reactions of the protective shields for providing fire protection are initiated within a temperature interval between 90° C. and 150° C.
摘要翻译：本发明涉及一种通过至少一个防护罩在飞行器中提供主动防火的装置。根据本发明，所述至少一个保护罩形成有膨胀材料，其在发生火灾的情况下可以以受控的方式被激活，特别是以可控的方式膨胀，远低于初始温度，否则通常用于膨胀材料通过电加热装置的温度为250℃。通过至少一个温度传感器测量飞行器的保持当前温度（优选在各种温度测量点），并传输到控制和调节装置。在发生火灾的情况下，加热装置被激活，用于提供防火的防护罩的膨胀反应在90℃至150℃的温度区间内开始。

3. 发明授权

US08205836B2 Fire protection device for an aircraft or spacecraft 有权
标题翻译：飞机或航天器的防火装置
公开(公告)号：US08205836B2
公开(公告)日：2012-06-26
申请号：US12001482
申请日：2007-12-11
申请人： Falk Brinkmann , Heinz-Peter Busch , Berend Schoke
发明人： Falk Brinkmann , Heinz-Peter Busch , Berend Schoke
IPC分类号： B64D45/00 , E05F15/20 , A62C3/08
CPC分类号： A62C3/08 , A62C2/065 , B64C1/38
摘要： A fire protection device for an aircraft or spacecraft is disclosed. The fire protection device can include a fireproof bulkhead and an adjusting device, the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage.
摘要翻译：公开了一种用于飞机或航天器的防火装置。防火装置可以包括防火舱壁和调节装置，防火舱壁可以从通风位置I调整到筛选位置II。当机身下方发生火灾时，这可能会阻止烟雾和热量流入舱内。

4. 发明申请

US20130287482A1 Facing arrangement and aircraft or spacecraft 有权
标题翻译：面对安排和飞机或航天器
公开(公告)号：US20130287482A1
公开(公告)日：2013-10-31
申请号：US13813609
申请日：2011-07-28
申请人： Heinz-Peter Busch , Berend Schoke
发明人： Heinz-Peter Busch , Berend Schoke
IPC分类号： B64C1/06
CPC分类号： B64C1/06 , B64C1/066 , F16B5/0036 , F16B5/0068 , F16B21/09 , Y10T403/51
摘要： A facing arrangement for a hold of an aircraft or spacecraft. The facing arrangement comprises a first and a second panel which form a gap between them; a first mounting part which is to be attached to a primary structure of the hold and which has at least one locking arrangement, and a second mounting part which has at least one counter locking arrangement. The locking arrangement and/or the counter locking arrangement passing, at least in portions, through the gap between the first and the second panel. The locking arrangement and the counter locking arrangement being locked together in order to connect the first mounting part to the second mounting part for holding the first and second panels between the first mounting part and the second mounting part.
摘要翻译：用于持有飞机或航天器的面对安排。面对装置包括在它们之间形成间隙的第一和第二面板; 第一安装部件，其被附接到保持件的主要结构并且具有至少一个锁定装置;以及第二安装部件，其具有至少一个反向锁定装置。锁定装置和/或反向锁定装置至少部分地穿过第一和第二面板之间的间隙。锁定装置和对位锁定装置被锁定在一起，以将第一安装部分连接到第二安装部分，用于将第一和第二面板保持在第一安装部分和第二安装部分之间。

5. 发明申请

US20110274863A1 THERMAL INSULATING TAPE WITH FIRE PROTECTING SYSTEM AND ITS USE IN AIRCRAFT CONSTRUCTION 审中-公开
标题翻译：具有防火保护系统的热绝缘带及其在飞机结构中的应用
公开(公告)号：US20110274863A1
公开(公告)日：2011-11-10
申请号：US13089353
申请日：2011-04-19
申请人： Heinz-Peter Busch , Berend Schoke
发明人： Heinz-Peter Busch , Berend Schoke
IPC分类号： F16L59/02 , B32B15/082 , E04B1/82 , F16L9/14 , H01B7/29 , C09J7/02 , H01B17/56
CPC分类号： C09D5/185 , C08K7/24 , C09D7/70 , C09J7/29 , C09J2400/163 , C09J2433/00 , H02G3/0412 , H02G3/0481 , Y10T428/1471 , Y10T428/264 , Y10T428/2804
摘要： A thermal insulating tape is configured for fire protection for use in aircraft construction. The insulating tape has a multilayer construction including a flexible carrier tape providing protection against burn-through, the carrier tape being formed as a thermally conductive metal tape. An adhesive film is disposed on a first side of the carrier tape and is configured for partial fixation or complete wrapping of the insulating tape on a protected component. A flexible intumescent coating is disposed on a second side of the carrier tape.
摘要翻译：隔热带被配置为用于飞机结构中的防火。绝缘带具有多层结构，其包括提供防止燃烧的保护的柔性载体带，载带形成为导热金属带。粘合剂膜设置在载带的第一侧上，并且被配置为将绝缘带部分地固定或完全包裹在受保护的部件上。柔性膨胀型涂层设置在载带的第二面上。

6. 发明授权

US09505482B2 Facing arrangement and aircraft or spacecraft 有权
公开(公告)号：US09505482B2
公开(公告)日：2016-11-29
申请号：US13813609
申请日：2011-07-28
申请人： Heinz-Peter Busch , Berend Schoke
发明人： Heinz-Peter Busch , Berend Schoke
IPC分类号： B64C1/06 , F16B5/00 , F16B21/09
CPC分类号： B64C1/06 , B64C1/066 , F16B5/0036 , F16B5/0068 , F16B21/09 , Y10T403/51
摘要： A facing arrangement for a hold of an aircraft or spacecraft. The facing arrangement comprises a first and a second panel which form a gap between them; a first mounting part which is to be attached to a primary structure of the hold and which has at least one locking arrangement, and a second mounting part which has at least one counter locking arrangement. The locking arrangement and/or the counter locking arrangement passing, at least in portions, through the gap between the first and the second panel. The locking arrangement and the counter locking arrangement being locked together in order to connect the first mounting part to the second mounting part for holding the first and second panels between the first mounting part and the second mounting part.

7. 发明申请

US20100276539A1 Fire protection device for an aircraft or spacecraft 有权
标题翻译：飞机或航天器的防火装置
公开(公告)号：US20100276539A1
公开(公告)日：2010-11-04
申请号：US12001482
申请日：2007-12-11
申请人： Falk Brinkmann , Heinz-Peter Busch , Berend Schoke
发明人： Falk Brinkmann , Heinz-Peter Busch , Berend Schoke
IPC分类号： B64D45/00
CPC分类号： A62C3/08 , A62C2/065 , B64C1/38
摘要： Provided is a fire protection device for an aircraft or spacecraft. The fire protection device is provided with a fireproof bulkhead and an adjusting device, by means of which the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage.
摘要翻译：提供一种用于飞机或航天器的防火装置。防火装置设有防火舱壁和调节装置，通过这种装置，防火舱壁可以从通风位置I调整到筛选位置II。当机身下方发生火灾时，这可能会阻止烟雾和热量流入舱内。

8. 发明授权

US08630534B2 Heating system and component with such a heating system 有权
标题翻译：加热系统和具有这种加热系统的部件
公开(公告)号：US08630534B2
公开(公告)日：2014-01-14
申请号：US11688736
申请日：2007-03-20
申请人： Heinz-Peter Busch , Soeren Schumacher
发明人： Heinz-Peter Busch , Soeren Schumacher
IPC分类号： H05B3/20
CPC分类号： B64D13/08 , B32B3/12 , B32B5/10 , B32B5/26 , B32B27/38 , B32B29/02 , B32B2255/02 , B32B2255/20 , B32B2260/023 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2307/202 , B32B2605/003 , B32B2605/18 , Y10T428/1234 , Y10T428/249924
摘要： A heating system according to the invention comprises a heating layer that is integrated into a prepreg layer of a high-resistance prepreg material. The heating layer may comprise a bonded heating fabric, a metal oxide coating or electrically conductive threads. According to the invention, the heating system is integrated into a component to be heated. This component may consist, for example, of a floor panel for an aircraft.
摘要翻译：根据本发明的加热系统包括集成到高电阻预浸料坯料的预浸料层中的加热层。加热层可以包括结合的加热织物，金属氧化物涂层或导电丝。根据本发明，加热系统被集成到待加热的部件中。该部件可以由例如飞机的底板组成。

9. 发明授权

US08740606B2 Press device for the energy-efficient curing of a sandwich component for aircraft 有权
标题翻译：用于航空器夹层组件的高效固化的压力装置
公开(公告)号：US08740606B2
公开(公告)日：2014-06-03
申请号：US11990899
申请日：2006-08-23
申请人： Heinz-Peter Busch , Stephan Bonk
发明人： Heinz-Peter Busch , Stephan Bonk
IPC分类号： B29C35/04 , B29C43/52
CPC分类号： B29C43/52 , B29C35/045 , B29C2035/046 , B29C2043/3615 , B29K2105/0854 , B29L2031/3085 , B32B37/06 , B32B2038/0076 , B32B2305/024 , B32B2310/0454 , Y02P70/26
摘要： A press device for the energy-efficient curing of a sandwich component for an aircraft, includes an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides. The sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space. At least one of at least one cover layer and the core structure includes a curable duroplastic plastic material. A conveying device feeds heated air through the core structure of the sandwich component in a closed heated-air circuit or preferably in an open heated-air circuit in order to ensure energy-efficient curing of the sandwich component from the inside out. The heated air is temperature-controlled by a heater. In the case of an open heated-air circuit, heat recovery by a heat exchanger is provided.
摘要翻译：一种用于航空器夹层组件的能量效率固化的压力装置，包括开放和机械适当地装载的芯结构，其中覆盖层被施加到一侧或两侧。三明治组件被限制在压力活塞，支座和压力装置的侧壁之间，从而形成基本上封闭的内部空间。至少一个覆盖层和芯结构中的至少一个包括可固化的塑性塑料材料。输送装置在封闭的加热空气回路中或优选在开放的加热空气回路中将加热的空气通过夹层组件的芯结构进行供给，以确保夹层组件从内向外的能量效率的固化。加热的空气由加热器进行温度控制。在开放的加热 - 空气回路的情况下，提供通过热交换器的热回收。

10. 发明申请

US20090155403A1 Press Device for the Energy-Efficient Curing of a Sandwich Component for Aircraft 有权
标题翻译：用于飞机三明治组件的高效固化的装置
公开(公告)号：US20090155403A1
公开(公告)日：2009-06-18
申请号：US11990899
申请日：2006-08-23
申请人： Heinz-Peter Busch , Stephan Bonk
发明人： Heinz-Peter Busch , Stephan Bonk
IPC分类号： B29C49/00
CPC分类号： B29C43/52 , B29C35/045 , B29C2035/046 , B29C2043/3615 , B29K2105/0854 , B29L2031/3085 , B32B37/06 , B32B2038/0076 , B32B2305/024 , B32B2310/0454 , Y02P70/26
摘要： A press device for the energy-efficient curing of a sandwich component for an aircraft, comprising an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides, characterised in that the sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space, and at least one cover layer and/or the core structure comprise/comprises a curable duroplastic plastic material.A conveying device feeds heated air through the core structure of the sandwich component in a closed heated-air circuit or preferably in an open heated-air circuit in order to ensure energy-efficient curing of the sandwich component from the inside out. The heated air is temperature-controlled by a heater. In the case of an open heated-air circuit, heat recovery by a heat exchanger is provided.
摘要翻译：一种用于飞行器的夹层组件的能量效率固化的压力装置，包括开放和机械适当地装载的芯结构，其具有施加到一侧或两侧的覆盖层，其特征在于，所述夹层构件被限制在压力活塞，压力装置的邻接和侧壁，从而形成基本上封闭的内部空间，并且至少一个覆盖层和/或芯结构包括/包括可固化的塑性塑料材料。输送装置在封闭的加热空气回路中或优选在开放的加热空气回路中将加热的空气通过夹层组件的芯结构进行供给，以确保夹层组件从内向外的能量效率的固化。加热的空气由加热器进行温度控制。在开放的加热 - 空气回路的情况下，提供通过热交换器的热回收。

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