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11.发明公开
公开(公告)号：EP0008503A1
公开(公告)日：1980-03-05
申请号：EP79301499.4
申请日：1979-07-27
CPC分类号： F42B15/34 , F28F13/00 , F28F2013/008 , G05D23/01 , G12B15/06
摘要： A solid state temperature gradient cooling system in which thermal energy is, under a first condition, carried from a heat source to a heat storage device (20) and under a second condition is carried from the heat source and storage device (20) to a heat dissipator (2). The change in conditions is responsive to changes in the temperature of the heat dissipator above and below a predetermined value. Bimetallic disc elements (16) are employed, which respond to temperature changes about the predetermined temperature, and snap from a first condition concave/convex surface configuration to a second condition convex/concave configuration. The disc elements (16) are supported about their outer peripheries so that the change in configuration will cause the centre of the disc (16) to move along an axis normal to the disc. This movement is used to respectively open and close a low resistance thermal path (10, 12, 8) between the heat dissipator (2) and a first thermal conducting path (24, 10, 22) defined to transmit thermal energy between the heat source and the heat sink (20).
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公开(公告)号：EP0246226A4
公开(公告)日：1990-12-12
申请号：EP85905949
申请日：1985-09-30
摘要： A closed loop system reduces pointing errors in one or more spacecraft instruments. Associated with each instrument is a means (3) for commanding motion in that instrument and a pointing control system (5) for imparting motion in that instrument in response to a command (4) from the commanding means (3). Spacecraft motion compensation logic (25) compensates for instrument pointing errors caused by instrument-motion-induced spacecraft motion. Any finite number of instruments can be so compensated, by providing each pointing control system (5) and each commanding means (3), for the instruments desired to be compensated, with a link to the spacecraft motion compensation logic (25). The spacecraft motion compensation logic (25) is an electronic manifestation of the algebraic negative of a model of the dynamics of motion of the spacecraft. An example of a suitable model, and computer-simulated results, are presented.
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公开(公告)号：EP0188873B1
公开(公告)日：1990-07-18
申请号：EP85307653.7
申请日：1985-10-23
CPC分类号： H01M2/26 , H01M6/48 , H01M8/0297 , H01M8/24 , H01M8/242 , H01M10/345
摘要： A bipolar metal-gas battery cell stack (1) eliminates the heavy bipolar plates (11) of the prior art by means of locating the series electrical connections (25, 27) between oppositely polarized electrodes (5, 7) of adjacent cells (3) external to the cells (3) in a dielectric frame (21, 23). As a result, the reliability of said electrical connections (25, 27) is improved, weight is saved, and reactant gas screens (15) and electrolyte reservoirs (13) can beneficially be made of compressible lightweight materials. Electrolyte is beneficially confined within each cell (3), and secondary (overcharge) gasses are beneficially confined within each cell (3) in a region (17) proximate the positive electrode (7). A hydrophobic barrier (29) and the frame segments (21, 23) prevent intercell migration of electrolyte and secondary gasses.
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公开(公告)号：EP0173452B1
公开(公告)日：1990-03-07
申请号：EP85305281.9
申请日：1985-07-24
发明人： Wisniewski, Jacob H.
IPC分类号： H03G11/00
CPC分类号： H03G11/008
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公开(公告)号：EP0131573B1
公开(公告)日：1988-12-28
申请号：EP83901443.8
申请日：1983-01-20
IPC分类号： F42B15/033
CPC分类号： F42B10/663
摘要： An open-ended diffusion chamber (16) and an adjacent combustion chamber (18) located in the nose (12) of a projectile (10) to receive ram air that ignites a solid fuel material (20) within the combustion chamber (18). A pair of oppositely disposed lateral steering ports (22, 24) are provided aft of the combustion chamber (18) and are interconnected therewith via a diverting valve (28) that is controllable to selectively divert the escaping combustion gases from the combustion chamber (18) to one or both of the steering ports (22, 24) to thereby change or maintain the trajectory course of the projectile (10) after firing.
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公开(公告)号：EP0246226A1
公开(公告)日：1987-11-25
申请号：EP85905949.0
申请日：1985-09-30
摘要： Un système à boucle fermée réduit les erreurs de collimation d'un ou plusieurs instruments transportés à bord d'un véhicule spatial. Un dispositif (3) de commande du déplacement est associé à chaque instrument pour provoquer le déplacement de cet instrument en réponse à une commande (4) donnée par le dispositif de commande (3). Une logique (25) de compensation du déplacement du véhicule compense des erreurs de collimation des instruments provoquées par un déplacement du véhicule induit par des déplacements des instruments. Il est ainsi possible de compenser des erreurs d'un nombre fini quelconque d'instruments, en établissant une connexion entre la logique de compensation (25) du déplacement du véhicule et les systèmes de commande de la collimation (5) et de commande (3) de chaque instrument que l'on désire compenser. La logique de compensation (25) du déplacement du véhicule spatial est une manifestation électronique de la négative algébrique d'un modèle dynamique du déplacement du véhicule. On donne un exemple d'un modèle approprié et des résultats simulés sur ordinateur.
摘要翻译： 闭环系统减少了航天器上携带的一个或多个仪器的准直误差。 位移控制装置（3）与每个仪器相关联，以响应于由控制装置（3）给出的命令（4）而引起该仪器的移动。 用于补偿车辆的位移的逻辑（25）补偿由仪器的运动引起的车辆的位移引起的仪器的准直误差。 因此，能够以补偿任何有限数量的仪器的误差，通过建立所述车辆和所述准直器控制系统（5）和控制装置的运动的补偿逻辑（25）之间的连接（3 ）每个希望补偿的仪器。 空间车辆位移的补偿逻辑（25）是车辆的位移的动态模型的代数负的电子表现。 给出了一个合适的模型和模拟计算机结果的例子。
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公开(公告)号：EP0123448B1
公开(公告)日：1987-11-11
申请号：EP84302026.4
申请日：1984-03-27
IPC分类号： H03B5/18
CPC分类号： H03B5/1817 , H03B5/1823 , H03B5/1829 , H03B5/1864 , H03B2200/0068 , H03B2201/014 , H03B2201/0208
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公开(公告)号：EP0177225A1
公开(公告)日：1986-04-09
申请号：EP85306653.8
申请日：1985-09-18
CPC分类号： F28F9/0278 , F28D15/0275 , F28F3/12 , H01M8/04007 , H01M10/613 , H01M10/617 , H01M10/647 , H01M10/6552 , H01M10/6557 , H01M10/6563 , H01M10/6566 , H01M10/6567 , H01M10/6568
摘要： An active cooling system (40, 41) for cooling electrochemical cells (11) that are arranged in a stack (9) in a fuel cell or battery (3). The cooling system (40, 41) comprises cooling panels (15, 16) carrying a cooling fluid that flows adjacent to and parallel to the plane of, each cell (11). The rate of cooling fluid flow past each cell (11) is made to be substantially equal, so that each cell (11) experiences substantially the same cooling environment, adding to the longevity of the fuel cell or battery (3). This can be accomplished by equalizing the resistance to cooling fluid flow for each cooling path (12), e.g., by using pressure equalizing, monotonically increasingly sized orifices (28) in an input manifold (25). Dual cooling panels (15,16) are preferably employed, in a counterflow mode. The panels (15, 16) may be divided into parallel channels (33). Heat pipe panels (35) containing a two-phase fluid may be used in lieu of panels (15, 16) that contain cooling fluid in a single state.
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公开(公告)号：EP0079684A3
公开(公告)日：1985-11-06
申请号：EP82305515
申请日：1982-10-18
CPC分类号： F41G7/2293 , F41G7/2213 , F41G7/2253 , G02B26/0891 , G02B26/10
摘要： An optical scanning apparatus embodied in a gyroscopic missile seeker to provide a rosette scan pattern of the field of view. A single driving motor (20) is employed with a traction drive assembly (38) to produce the necessary counter-rotation of scanned elements and thereby effect the rosette scan pattern.
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公开(公告)号：EP0136096A2
公开(公告)日：1985-04-03
申请号：EP84305871.0
申请日：1984-08-29
发明人： Stonier, Roger A.
摘要： A technique for making a honeycomb structure includes bonding a less than totally cured composite skin (16) to a possibly contoured honeycomb core (8). The composite skin (16) comprises fibers and a resin chosen to maximize the strength and stiffness of the skin (16) when cured. Non- contiguous adhesive fillets (5) are prepositioned onto faying surfaces of the honeycomb core (8). The adhesive (5) is preselected, independently of the preselection of the resin, to maximize the strength of the bond between the skin (16) and the core (8).
A thin, lightweight scrim cloth (14) is interposed between the starting skin (16) and the filleted core (8). The scrim cloth (14) prevents resin from flowing into the core (8) and allows a safe place for the intermingling of resin and adhesive (5). The assemblage is heated under pressure, cocuring the adhesive (5) and the resin. The fillets (5) are preferably prepositioned on surfaces (10) by means of applying an adhesive-coated fabric to the faying surface, heating the fabric-covered core (8) so that some of the adhesive (5) flows out of the fabric (1) and into the core (8) at a region near the faying surface, cooling the core (8) so that the only substance remaining adhered to the core edges (10) is the adhesive fillets (5).摘要翻译： 一种制造蜂窝结构的技术包括将小于完全固化的复合表皮（16）接合到可能成型的蜂窝芯（8）上。 复合皮肤（16）包括纤维和选择的树脂，以在固化时使皮肤（16）的强度和刚度最大化。 将不连续的胶片（5）预先定位在蜂窝芯（8）的接合表面上。 预先选择粘合剂（5），以独立于树脂的预选择，以使皮肤（16）和芯（8）之间的粘合强度最大化。 在起始皮肤（16）和圆角的芯（8）之间插入一薄而轻的稀松布（14）。 稀松布（14）防止树脂流入芯（8），并且可以安全地将树脂和粘合剂（5）混合在一起。 将组合物在压力下加热，将粘合剂（5）和树脂共固化。 通过将粘合剂涂覆的织物施加到接合表面上，将片状物（5）预先定位在表面（10）上，加热织物覆盖的芯部（8），使得一些粘合剂（5）流出织物 （1）并且在靠近飞行表面的区域处进入芯部（8），冷却芯部（8），使得仅保持粘附到芯部边缘（10）的物质是粘合剂圆角（5）。
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