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1. 发明授权

US5111354A Process for the perfecting of the grounding of multi-layer insulations (thermal blankets) for space applications 失效
标题翻译：完成多层绝缘（热毯）接地的过程适用于空间应用
公开(公告)号：US5111354A
公开(公告)日：1992-05-05
申请号：US502434
申请日：1990-03-30
申请人： Danilo Marzi , Roger A. Stonier
发明人： Danilo Marzi , Roger A. Stonier
IPC分类号： H05K9/00
CPC分类号： H05K9/0039
摘要： A method and apparatus for grounding multi-layer insulations (MLI) by electric contact, of either of each layer with the other or of all the layers with the underlying structure by means of one or more points of attachment of mechanical type. This makes it possible to simplify the construction procedure and increase the reliability.This method is essentially carried out in the following manner: The layers (FIG. 1) which form the multi-layer insulations (6), (7) (8) are metalized on both faces and have holes (9) which are also metalized. All layers are contacted with each other and with a part of the attachment system (3) which is also electrically conductive.The other part of the attachment system (2) is positioned on the structure (1) in such a manner as to permit the passage of electric charges. By contacting the two parts of the attachment system (2) (3), the multi-layer insulation is grounded with the structure.The invention lies within the technical field of passive thermal protections, especially for space structures (space apparatus and systems etc.).The object of the invention is to permit the removal of electric charges on multi-layer insulations.

2. 发明授权

US4613870A Spacecraft antenna reflector 失效
标题翻译：航天器天线反射器
公开(公告)号：US4613870A
公开(公告)日：1986-09-23
申请号：US532881
申请日：1983-09-16
申请人： Roger A. Stonier
发明人： Roger A. Stonier
IPC分类号： H01Q15/16 , H01Q1/28
CPC分类号： H01Q15/161 , Y10S343/02 , Y10T428/24149
摘要： An antenna reflector structure of the offset-fed type which is suitable for use on spacecraft. The reflector structure includes a central boom, a number of spaced ribs on the boom, an RF reflective mesh layer adjacent to the outer, transverse peripheral edges of the ribs, and contoured angle members for securing the mesh layer to the ribs to provide a specific contour for the reflector surface defined by the mesh layer. The boom can be of one-piece construction or formed from telescoped segments. The reflector structure is deployable and furlable. Several embodiments of the reflector structure are disclosed.
摘要翻译：适用于航天器的偏置馈电型天线反射器结构。该反射器结构包括一个中心吊臂，在起重臂上的多个隔开的肋，邻近肋的外部，横向周边边缘的RF反射网格层，以及用于将网格层固定到肋条上的轮廓角件，由网格层定义的反射器表面的轮廓。起重臂可以是一体式结构，也可以由伸缩段形成。反射器结构是可展开和可展开的。公开了反射器结构的几个实施例。

3. 发明授权

US06367509B1 Thermal harness using encased carbon-based fiber and end attachment brackets 有权
标题翻译：使用封装的碳纤维和端部附件支架的热束
公开(公告)号：US06367509B1
公开(公告)日：2002-04-09
申请号：US09843898
申请日：2001-04-27
申请人： W. Scott Bonneville , Roger A. Stonier
发明人： W. Scott Bonneville , Roger A. Stonier
IPC分类号： F16L900
CPC分类号： F28F21/02 , H01L23/3733 , H01L2924/0002 , H01L2924/00
摘要： An improved thermal harness or thermal heat strap that comprises carbon based (graphite) fiber heat conducting elements coupled to graphite, composite, polymer, or metal end attachment brackets. An outer casing comprising a tubular braided sleeve surrounds the heat conducting elements and eliminates possible contamination caused by the graphite fibers. The thermal harness may be advantageously used in electronic applications to dissipate heat from high temperature components.
摘要翻译：改进的热束带或热热带，其包括耦合到石墨，复合材料，聚合物或金属端附件支架的碳基（石墨）纤维导热元件。外壳包括管状编织套筒围绕导热元件并消除由石墨纤维引起的可能的污染。热线束可有利地用于电子应用中以从高温部件散热。

4. 发明授权

US4284457A Method for bonding a skin member to honeycomb core 失效
标题翻译：将表皮部件与蜂窝芯体接合的方法
公开(公告)号：US4284457A
公开(公告)日：1981-08-18
申请号：US61962
申请日：1979-07-30
申请人： Roger A. Stonier , Richard A. Hayes
发明人： Roger A. Stonier , Richard A. Hayes
IPC分类号： B29C65/52 , B29D24/00 , B32B3/12 , C09J5/00 , B05D5/10 , B32B31/00 , B65C9/25
CPC分类号： C09J5/00 , B29C65/483 , B29C65/4835 , B29C65/526 , B29C66/5346 , B29D24/005 , B32B3/12 , B29L2031/601 , B29L2031/608 , Y10T428/24149
摘要： Described herein is a method for bonding a skin member such as metal, plastic, perforated acoustic skin, or fiberglass or graphite reinforced plastic, to a honeycomb core support structure such as lightweight hollow hexagonally shaped tubes. Such a method can be used in the construction industry for making panels and walls and similar structures, and in the aerospace industry for making airplane and satellite structures, etc. The adhesive employed is an adhesive-coated fabric material which is partially cured onto the honeycomb and cooled down, following which most of the adhesive material is removed when the coated fabric is peeled away. This leaves an optimum amount of adhesive in the most effective locations on the wall edges of the honeycomb cells where it is needed for bonding the core to the skin. The skin member is then bonded to the honeycomb by bringing the adhesive to its final cure. This method thus produces a lightweight structure, and with respect to acoustic panels a structure in which perforations in the skin are not covered or sealed. The method can be used for curved as well as flat honeycomb surfaces.
摘要翻译：这里描述的是将诸如金属，塑料，穿孔声学表皮或玻璃纤维或石墨增强塑料的表皮构件粘合到诸如轻质中空六边形管的蜂窝芯支撑结构上的方法。这种方法可用于制造板材和墙壁和类似结构的建筑行业，并且在航空航天工业中用于制造飞机和卫星结构等。所使用的粘合剂是粘合剂涂覆的织物材料，其被部分固化到蜂窝并冷却，随后当涂布的织物被剥离时，大部分粘合剂材料被去除。这在蜂窝状电池的壁边缘上的最有效的位置留下最佳量的粘合剂，其中需要将芯粘合到皮肤上。然后通过使粘合剂最终固化，将皮肤构件结合到蜂窝体上。因此，该方法产生轻质结构，并且相对于声学面板，其中不覆盖或密封皮肤中的穿孔的结构。该方法可用于弯曲和平坦的蜂窝表面。

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