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

US06481670B1 Apparatus for spacecraft thermal management 有权
标题翻译：航天器热管理装置
公开(公告)号：US06481670B1
公开(公告)日：2002-11-19
申请号：US09693534
申请日：2000-10-20
申请人： Robert T. Bigelow , Russell J. Common , John Mezits , David A. Cavaleri
发明人： Robert T. Bigelow , Russell J. Common , John Mezits , David A. Cavaleri
IPC分类号： B64G146
CPC分类号： B64G1/58 , B64G1/50 , B64G1/503 , B64G1/506 , B64G1/54 , B64G2001/224
摘要： The present invention provides a thermal, and if desired, a radiation barrier to protect the exterior surface of a spacecraft. In particular, the present invention protects the polymeric materials of construction utilized in inflatable and expandable spacecraft from the deleterious effects of both thermal and radiation aging. The protective barrier is formed from a tube or tubes through which a fluid circulates. The tube segment substantially enclose the spacecraft, and in particular, the critical layers that are desired to be protected. This protective barrier provides a thermal heat sink, temperature equalization, and a waste heat rejection system, that can moderate the temperature extremes encountered by spacecraft. In addition, dependent on the fluid selected, substantial radiation shielding can be provided that can protect the entire spacecraft.
摘要翻译：本发明提供了一种热，并且如果需要，提供了用于保护航天器的外表面的辐射屏障。特别地，本发明保护在可充气和可膨胀的宇宙飞船中使用的结构的聚合物材料免受热和辐射老化的有害影响。保护屏障由流体循环通过的管或管形成。管段基本上包围航天器，特别是期望保护的临界层。该保护屏障提供热散热器，温度均衡和废热排放系统，可以缓解航天器遇到的极端温度。另外，依赖于所选择的流体，可以提供可以保护整个航天器的显着的辐射屏蔽。

2. 发明授权

US06669147B2 Deployable radiator for a space vehicle 有权
公开(公告)号：US06669147B2
公开(公告)日：2003-12-30
申请号：US10114277
申请日：2002-04-03
申请人： Philippe Bertheux , Emmanuel Texier , Bernard Jacqué , Jean-Marie Seguin
发明人： Philippe Bertheux , Emmanuel Texier , Bernard Jacqué , Jean-Marie Seguin
IPC分类号： B64G146
CPC分类号： B64G1/503 , B64G1/222 , B64G1/506
摘要： The invention provides a deployable radiator for a space vehicle such as a satellite. The radiator of the invention has two radiating faces, one of which is insulating over a portion of its area so that during launch and while the satellite is being moved onto station, with the radiator in the stored position, it naturally serves to keep the highest possible temperature on board the vehicle.

3. 发明授权

US06478257B1 Phase change material thermal control for electric propulsion 失效
标题翻译：电力推进相变材料热控制
公开(公告)号：US06478257B1
公开(公告)日：2002-11-12
申请号：US09881942
申请日：2001-06-15
申请人： David Oh , Lenny Low
发明人： David Oh , Lenny Low
IPC分类号： B64G146
CPC分类号： F03H1/0031 , B64G1/405 , B64G1/406 , B64G1/503 , B64G1/58
摘要： Systems and methods that employ a phase change material to provide thermal control of electric propulsion devices (thrusters). A spacecraft is configured to have an electric propulsion thruster. The electric propulsion thruster is surrounded with a phase change material. Suitable phase change materials include high-density polyethylene (HDPE), waxes, paraffin materials, and eutectic salts. The spacecraft is launched into orbit. The electric propulsion thruster is fired for a predetermined period of time. Heat generated by the electric propulsion thruster is absorbed and stored in the phase change material while the thruster is firing. The stored heat is dissipated into space after the thruster has stopped firing.
摘要翻译：采用相变材料的电力推进装置（推进器）的热控制的系统和方法。航天器被配置为具有电动推进推进器。电推进推进器被相变材料包围。合适的相变材料包括高密度聚乙烯（HDPE），蜡，石蜡材料和共晶盐。航天器进入轨道。电推进推进器在预定的时间内被点燃。电推进推进器产生的热量在推进器点火时被吸收并储存在相变材料中。储存的热量在推进器停止点火后消散到太空中。

4. 发明授权

US06595470B2 Deployable radiator with flexible line loop 有权
标题翻译：具有柔性线环的可部署散热器
公开(公告)号：US06595470B2
公开(公告)日：2003-07-22
申请号：US10002498
申请日：2001-11-02
申请人： Bryan V. Keeler , Arthur Mathias Lehtinen , Billy W. McGee
发明人： Bryan V. Keeler , Arthur Mathias Lehtinen , Billy W. McGee
IPC分类号： B64G146
CPC分类号： B64G1/222 , B64G1/503
摘要： Radiator assembly (10) for use on a spacecraft (12) is provided including at least one radiator panel assembly (26) repeatably movable between a panel stowed position (28) and a panel deployed position (36), at least two flexible lines (40) in fluid communication with the at least one radiator panel assembly (26) and repeatably movable between a stowage loop (42) and a flattened deployed loop (44).
摘要翻译：提供了用于航天器（12）的散热器组件（10），其包括至少一个散热器板组件（26），其可重复地在面板收起位置（28）和面板展开位置（36）之间移动，至少两根柔性线 40）与所述至少一个散热器面板组件（26）流体连通并且可重复地在收起环（42）和扁平展开环（44）之间移动。

5. 发明授权

US06497390B1 Thermal protection system especially for space vehicles 有权
标题翻译：热保护系统尤其适用于太空车
公开(公告)号：US06497390B1
公开(公告)日：2002-12-24
申请号：US09669128
申请日：2000-09-25
申请人： Wolfgang Fischer , Walter Vogel , Joerg Bolz , Wolff-Dieter Ebeling , Ulrich Rieck
发明人： Wolfgang Fischer , Walter Vogel , Joerg Bolz , Wolff-Dieter Ebeling , Ulrich Rieck
IPC分类号： B64G146
CPC分类号： B32B5/26 , B32B5/28 , B32B7/12 , B32B19/06 , B32B2262/105 , B32B2307/304 , B32B2605/18 , B64G1/58 , F16L59/02 , Y10T428/24033 , Y10T428/24132
摘要： A thermal protection system suitable as a heat shield for a space vehicle includes a flexible insulation mat that is adhesively bonded onto the outer skin of the space vehicle, a cover layer made of at least one ply of a ceramic fiber composite material secured onto the insulation mat, and a coating of an inorganic material applied onto an outer surface of the ceramic cover layer. The cover layer is secured to the insulation mat by adhesive bonding, stitching with ceramic threads or the like, or by a snap fastener button connection. The ceramic fiber composite materials of the cover layer include inorganic fibers which are preferably oxides, carbides or mixtures thereof embedded in a matrix of the same compositional components, whereby the components can be selected appropriately depending on the requirements of the particular application. The overall thermal protection system remains flexible, lightweight, and highly effective for thermal shielding, so that it may be used not only on the relatively cooler portions of the space vehicle, but also on the most highly thermally loaded areas such as the nose and the leading edges of wings and the like.
摘要翻译：适用于空间飞行器的隔热罩的热保护系统包括：粘合地粘合到太空车外表面上的柔性绝缘垫，由至少一层固定在绝缘层上的陶瓷纤维复合材料层制成的覆盖层垫和涂覆在陶瓷覆盖层的外表面上的无机材料的涂层。覆盖层通过粘合剂粘接，用陶瓷丝线等缝合或通过揿钮按钮连接固定到绝缘垫上。覆盖层的陶瓷纤维复合材料包括嵌入相同成分组分的基质中的氧化物，碳化物或其混合物的无机纤维，由此可以根据具体应用的要求适当地选择组分。整个热保护系统保持灵活，重量轻并且对于热屏蔽是非常有效的，因此它不仅可以用于太空车辆的相对较冷的部分，而且可以用在最高热负荷的区域，例如鼻子和翅膀的前缘等。

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