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公开(公告)号：EP3055213A1
公开(公告)日：2016-08-17
申请号：EP14795885.4
申请日：2014-09-30
发明人： CHU, Peter Y.
摘要： A launch vehicle payload that includes at least two spacecraft (210(1), 210(2)) is disclosed. The launch vehicle includes a single payload adapter (225). Each spacecraft has a launch vehicle adapter structure (215(1), 215(2)) providing a respectively coplanar structural interface directly with the single launch vehicle payload adapter. The spacecraft share a launch vehicle payload fairing (221) volume substantially side-by-side and are detachably coupled together such that a positive clearance is provided between adjacent, non-abutting structural body surfaces of each spacecraft.
摘要翻译： 公开了包括至少两个航天器的运载火箭有效载荷。 运载火箭包括单个有效载荷适配器。 每个航天器具有运载火箭适配器结构，其提供与单个运载火箭有效载荷适配器直接相连的共面结构接口。 航天器基本并排地共享运载火箭有效载荷整流罩体积，并且可拆卸地联接在一起，使得在每个航天器的相邻的，非邻接的结构体表面之间提供了正的间隙。
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公开(公告)号：EP2939934A4
公开(公告)日：2016-08-10
申请号：EP13869087
申请日：2013-12-24
发明人： HORIE YOUICHI
IPC分类号： B64G1/64
CPC分类号： B64G1/222 , B64G1/64 , B64G1/641 , B64G1/645 , Y10T225/321
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公开(公告)号：EP2758310A1
公开(公告)日：2014-07-30
申请号：EP12761734.8
申请日：2012-09-20
发明人： BULTEL, Pascal
CPC分类号： B64G1/40 , B64G1/007 , B64G1/242 , B64G1/405 , B64G1/406 , B64G1/42 , B64G1/422 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/503 , B64G1/64 , B64G1/641
摘要： The invention relates to a propulsion bay (1) intended to be transported, at least temporarily, in a space launch vehicle (2) and comprising an adapter (3) that co-operates with at least one system located, at least temporarily, on board the bay (1), said system comprising an electrical power supply. The bay is characterised in that it also comprises at least one electric space propulsion engine that can be powered by the power supply of the system.
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34.发明公开COUPLING/UNCOUPLING MECHANISM AND COSMONAUTIC VEHICLE PROVIDED WITH SAME 审中-公开KOPPLUNGS- / ENTKOPPLUNGSMECHANISMUS UND WELTRAUMFAHRZEUG DAMIT
公开(公告)号：EP2660156A1
公开(公告)日：2013-11-06
申请号：EP11853500.4
申请日：2011-12-16
发明人： HORIE, Youichi
CPC分类号： B64G1/641 , B64G1/64 , B64G1/645 , F16B21/065 , Y10T403/7071 , Y10T403/7075
摘要： A coupling/uncoupling mechanism (10A) according to the present invention maintains, when a male coupling body (30A) is coupled to a female coupling body (20A), a condition that the male coupling body (30A) is inserted in an insertion space (SO) and the other end of a lever member (22) is in a position in proximity to the insertion space (SO), so that an engaging surface (23a) of an engaging member (23) is contacted with an engageable surface (31a) of the male coupling body (30A). When the male coupling body (30A) and the female coupling body (20A) is uncoupled, the other end of the lever member (22) moves to a direction to be apart from the insertion space (SO), so that the engaging surface (23a) moves toward a withdrawing direction (D2). This allows releasing the contacting of the engaging surface (23a) with the engageable surface (31a). This provides that sufficient fastening force can be achieved with a simple configuration and the coupling status can be retained with a smaller force as compared with such a fastening force, and further, a recombination can be easily achieved even after a separation is made.
摘要翻译： 根据本发明的耦合/非耦合机构（10A），当阳联接体（30A）联接到阴联结体（20A）时，保持阳连接体（30A）插入到插入空间 （SO）并且杆构件（22）的另一端处于靠近插入空间（SO）的位置，使得接合构件（23）的接合表面（23a）与可接合表面（ 31a）。 当阳联接体（30A）和阴联接体（20A）脱离联接时，杆构件（22）的另一端向与插入空间（SO）分开的方向移动，使得接合表面 23a）朝着退出方向（D2）移动。 这允许释放接合表面（23a）与可接合表面（31a）的接触。 这提供了通过简单的构造可以实现足够的紧固力，并且与这种紧固力相比，可以以较小的力保持联接状态，此外，即使在分离之后也可以容易地实现复合。
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公开(公告)号：EP1467121A2
公开(公告)日：2004-10-13
申请号：EP04251874.6
申请日：2004-03-30
申请人： COM DEV LTD.
发明人： Heinemann, Mark , Voss, Eric Henry
IPC分类号： F16F15/073 , B64G1/64
CPC分类号： B64G1/64 , F16F15/073
摘要： A shock attenuating mounting bracket (30) for isolating a hardware component from shocks associated with an underlying structure includes a base (32) and a planar strip (34) coupled together. The base (32) is coupled to the underlying structure and the planar strip (34) is coupled to the hardware component. The planar strip has at least two bends (36,38) along its length for dissipating the shocks associated with the underlying structure. The planar strip can be C-shaped with first and second free ends coupled to the base and a mid-section coupled to the hardware component. Alternatively, the planar strip can have a C-shaped notch formed within and the bracket can include a multi-sided gusset plate that braces the base to the planar strip. The bracket is designed to improve the shock attenuation in shock sensitive designs while maintaining sufficient structural stiffness to sustain random vibration loads and minimum natural frequencies greater than 100 Hz.
摘要翻译： 用于将硬件部件与与下面的结构相关联的冲击隔离的减震安装支架（30）包括联接在一起的基座（32）和平面条带（34）。 基座（32）连接到下面的结构，并且平面条（34）耦合到硬件部件。 平面条沿其长度具有至少两个弯曲部（36,38），用于消除与下面的结构相关联的冲击。 平面条带可以是C形的，其中第一和第二自由端连接到基部，并且中间部分耦合到硬件部件。 或者，平面条可以具有形成在其内的C形凹口，并且支架可以包括将基部支撑到平面条的多边角撑板。 支架设计用于改善冲击敏感设计中的冲击衰减，同时保持足够的结构刚度以维持随机振动载荷和大于100 Hz的最小固有频率。
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36.发明公开Method for simultaneously launching multiple satellites into orbit 审中-公开维吾尔语嗯merere Satelliten gleichzeitig在轨道zu bringen
公开(公告)号：EP0979774A1
公开(公告)日：2000-02-16
申请号：EP98114910.7
申请日：1998-08-08
申请人： HONEYWELL INC.
发明人： Collyer, Gordon L.
CPC分类号： B64G1/1085 , B64G1/002 , B64G1/007 , B64G1/40 , B64G1/64
摘要： Satellites are launched to a first orbit (A) on a launch rocket. The satellites are connected together, forming a satellite cluster (22), that is propelled from the first orbit to a higher mission orbit (B) by thrustors on each satellite. The satellite cluster is formed so that satellite cluster rotation from aerodynamic drag on the individual satellites is minimized. The thrustors are sequenced to control satellite cluster attitude during the transition to the second altitude. At the second altitude, the satellites are separated from the satellite cluster and propelled to their mission orbits using their own thrustors and attitude system.
摘要翻译： 卫星在发射火箭上发射到第一个轨道（A）。 卫星连接在一起，形成卫星集群（22），其通过每个卫星上的推力器从第一轨道推进到较高任务轨道（B）。 形成卫星群，使得卫星群从各个卫星上的气动阻力旋转最小化。 推进器在第二高度过渡期间被排序以控制卫星集群姿态。 在第二高度，卫星与卫星群分离，并使用自己的推力器和姿态系统推进到任务轨道。
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公开(公告)号：EP0849169A1
公开(公告)日：1998-06-24
申请号：EP97121953.0
申请日：1997-12-16
申请人： TRW Inc.
摘要： A spacecraft avionics module that is for the most part functionally independent of a core spacecraft structure, and provides its own structural integrity, thermal management and some level of power management. The illustrative embodiment of the module is formed as a flat panel that also serves as a thermal radiator. Electronic components are mounted directly onto the panel, which is normally attached by mounting hardware to the core spacecraft structure, through a backbone interface that provides data interconnection between modules and, in some cases, supplies unregulated power to the module. The module may include a power regulation function, or may also include power storage and power generation functions. For complete independence, the module may also include its own attitude control system.
摘要翻译： 航天器航空电子模块大部分功能上独立于核心航天器结构，并提供自身的结构完整性，热管理和一定程度的电源管理。 模块的说明性实施例形成为也用作散热器的平板。 电子部件直接安装在面板上，该面板通常通过将硬件安装到核心航天器结构上，通过提供模块之间的数据互连的骨干接口，并且在某些情况下向模块提供未调节的电力。 该模块可以包括功率调节功能，或者也可以包括功率储存和发电功能。 为了完全独立，模块还可以包括其自己的姿态控制系统。
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38.发明授权Système pour déployer/replier deux éléments, avec verrouillage par came desdits éléments déployés 失效系统用于展开/与凸轮两个元件的折叠锁定在展开元件
公开(公告)号：EP0694474B1
公开(公告)日：1997-11-19
申请号：EP95401689.5
申请日：1995-07-17
发明人： Geyer, Freddy
CPC分类号： B64G1/44 , B64G1/22 , B64G1/222 , B64G1/64 , B64G1/645 , Y10T74/2063 , Y10T74/2101 , Y10T403/589 , Y10T403/591
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公开(公告)号：EP0211501B1
公开(公告)日：1990-04-11
申请号：EP86304843.5
申请日：1986-06-24
申请人： HONEYWELL INC.
IPC分类号： H01R39/64
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公开(公告)号：EP0211501A1
公开(公告)日：1987-02-25
申请号：EP86304843.5
申请日：1986-06-24
申请人： HONEYWELL INC.
IPC分类号： H01R39/64
摘要： An apparatus for reducing terminal-to-terminal circuit resistance and enhancing heat transfer in a rotary power transfer apparatus of the roll ring type comprising a connecting thimble (11) for attaching an external power cable (23) to a cone shaped terminal (14) which is attached to a tab (18) integral with outer ring (19). An inner ring (25) having a spherical recess mates with the spherical end (30) of a tie connector (26). A cone shaped terminal (14) is fitted to a second connecting thimble (11) for attaching a second external power cable (23).
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