公开(公告)号：US08979035B2

公开(公告)日：2015-03-17

申请号：US12912185

申请日：2010-10-26

申请人： Franz Straumann ,  Richard Von Arx

发明人： Franz Straumann ,  Richard Von Arx

IPC分类号： B64G1/64

CPC分类号： B64G1/641 ,  B64G1/645

摘要： A system and corresponding method for a launch vehicle or spacecraft for releasably connecting a first body (100) with a first interface (101) and a second body (200) with a second matching interface (201), said system comprising: a belt (300) for releasably securing said first body (100) to said second body (200); a circumferential trench (203) at said second interface (201) for receiving said belt (300) in order to provide for a fixation of said belt (300) with relation to said second body (200); mechanical fixation means (301) attaching said belt (300) to said first body (100), said mechanical fixation means (301) being provided to enable a circumferential shifting movement of said belt (300) with respect to said circumference of said first body (100) in order to initiate a separation of the first body (100) from the second body (200), wherein said circumferential shifting movement induces a relative movement of said belt (300) with respect to said circumference of said first body (100) in order to remove said belt (300) from said trench (203), and wherein the system further comprising a releasing mechanism (303) causing said circumferential shifting movement.

摘要翻译： 一种用于将第一主体（100）与第一接口（101）和第二主体（200）可释放地连接到第二匹配接口（201）的运载火箭或航天器的系统和相应方法，所述系统包括：带（ 300），用于将所述第一主体（100）可释放地固定到所述第二主体（200）; 在所述第二接口（201）处的圆周沟槽（203）用于接收所述带（300），以便提供所述带（300）相对于所述第二主体（200）的固定; 将所述带（300）附接到所述第一主体（100）的机械固定装置（301），所述机械固定装置（301）被设置成使得所述带（300）相对于所述第一主体 （100），以便开始第一主体（100）与第二主体（200）的分离，其中所述周向移动运动引起所述带（300）相对于所述第一主体（100）的所述圆周的相对运动 ），以从所述沟槽（203）中移除所述带（300），并且其中所述系统还包括引起所述周向移动运动的释放机构（303）。

公开(公告)号：US08973873B2

公开(公告)日：2015-03-10

申请号：US13652101

申请日：2012-10-15

申请人： The Boeing Company

发明人： Richard W. Aston ,  Michael John Langmack ,  Brett T. Cope ,  Anna M. Tomzynska

IPC分类号： B64G1/66 ,  B64G1/40

CPC分类号： B64G1/402 ,  B64G1/405 ,  B64G1/641 ,  Y10T29/49826

摘要： A spacecraft having a primary structural frame and a propellant tank, in which the spacecraft may include a tank mount adopted to engage a portion of the propellant tank, the tank mount being configured to transfer launch loads directly from the propellant tank to a lunch vehicle interface ring.

摘要翻译： 具有主要结构框架和推进剂罐的航天器，其中航天器可以包括用于接合推进剂罐的一部分的油箱底座，油箱底座构造成将发射载荷直接从推进剂罐转移到午餐车辆界面 环。

公开(公告)号：US20140332632A1

公开(公告)日：2014-11-13

申请号：US14099674

申请日：2013-12-06

申请人： Space Systems/Loral, LLC

发明人： Robert E. Helmer ,  Hauke G. Nehrenheim

IPC分类号： B64G1/64

CPC分类号： B64G1/641 ,  B64G2001/228 ,  F16F15/00 ,  F16F15/04

摘要： An adapter arrangement includes a first adapter ring for interfacing with a launch vehicle payload interface ring, a second adapter ring for interfacing with a payload launch vehicle interface ring, and a plurality of vibration isolation devices disposed between and attached to each of the first adapter ring and the second adapter ring. The first adapter ring has a first standard interface with the launch vehicle payload interface ring and the second adapter ring has a second standard interface with the payload launch vehicle interface ring.

摘要翻译： 适配器装置包括用于与发射车载荷接口环接口的第一适配器环，用于与有效载荷发射车辆接口环接口的第二适配环，以及设置在每个第一适配环上并连接到每个第一适配环的多个隔振装置 和第二适配器环。 第一适配器环具有与发射车载荷接口环的第一标准接口，并且第二适配器环具有与有效载荷发射车辆接口环的第二标准接口。

公开(公告)号：US20140234566A1

公开(公告)日：2014-08-21

申请号：US13770330

申请日：2013-02-19

申请人： THE BOEING COMPANY

发明人： Richard W. ASTON ,  Brett T. COPE ,  Andrew R. STREETT

IPC分类号： B32B3/06

CPC分类号： B32B38/1808 ,  B29C65/02 ,  B29C66/432 ,  B29K2105/256 ,  B29L2009/00 ,  B29L2031/3097 ,  B32B1/00 ,  B32B3/02 ,  B32B5/12 ,  B32B5/26 ,  B32B37/06 ,  B32B37/182 ,  B32B2250/20 ,  B32B2262/02 ,  B32B2307/306 ,  B32B2307/308 ,  B32B2307/734 ,  B32B2605/00 ,  B64G1/22 ,  B64G1/641 ,  Y10T156/10 ,  Y10T428/192

摘要： A cone-shaped composite article may include an inner sublaminate containing at least four unidirectional plies having an inner stacking sequence with fiber angles of 0, 90, −45, and +45 degrees such that the inner laminate has a quasi-isotropic layup pattern at any location on the inner laminate. The cone-shaped composite article may also include an outer sublaminate containing at least four unidirectional plies having an outer stacking sequence that is a mirror image of the inner stacking sequence. Each one of the unidirectional plies may be continuous along a ply arclength wrapping 360 degrees around the cone-shaped composite article and may have opposing ply ends terminating at a ply seam.

摘要翻译： 锥形复合制品可以包括含有至少四个单向层的内部层压板，其具有纤维角度为0°，90°-45°和+ 45°的内部堆叠序列，使得内层压板具有准各向同性叠层图案 内层压板上的任何位置。 锥形复合制品还可以包括含有至少四个单向层片的外部层压板，其具有作为内部堆叠序列的镜像的外部堆叠序列。 单向帘布层中的每一个可以沿着围绕锥形复合制品360度缠绕的帘布层长度连续，并且可以具有在帘布层接缝处终止的相对的帘布层末端。

公开(公告)号：US08789796B2

公开(公告)日：2014-07-29

申请号：US13101944

申请日：2011-05-05

申请人： Joel Francis Boccio ,  Gerrit Van Ommering ,  Walter S. Gelon ,  Steven Daniel Perez ,  Eric V. Werner

发明人： Joel Francis Boccio ,  Gerrit Van Ommering ,  Walter S. Gelon ,  Steven Daniel Perez ,  Eric V. Werner

IPC分类号： B64G1/22 ,  B64G1/66

CPC分类号： H01Q1/288 ,  B64G1/1007 ,  B64G1/222 ,  B64G1/641 ,  B64G1/66 ,  H01Q1/08 ,  H01Q15/161 ,  H01Q19/132

摘要： A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.

摘要翻译： 来自具有包括多个大天线的有效载荷的地球轨道卫星提供高容量宽带服务，该卫星在部署在轨道上时具有倒置配置。 卫星具有靠近运载火箭结构界面的后表面，与所述后表面相对的前表面，以及设置在其间的结构。 在发射配置中，两个或多个可展开的天线被放置在前表面上或靠近和向前的前表面上，未被部署; 在轨道上，当卫星被设置成具有大致面向地面的后表面时，有效载荷可操作，同时前表面基本上面向反地球方向。 每个可部署的天线被布置成在部署时面向地面，位于前表面的大致向前和向外的位置。

公开(公告)号：US20140027578A1

公开(公告)日：2014-01-30

申请号：US14003280

申请日：2012-03-06

申请人： Patrick Comtesse

发明人： Patrick Comtesse

IPC分类号： B64G1/00

CPC分类号： B64G1/002 ,  B64G1/1085 ,  B64G1/641

摘要： According to the invention, a link is established between the fixed part (4A) and the removable part (4B) of an enclosure (4) in which the second satellite is previously enclosed, said link being such that said removable part (4B) remains attached to said fixed part (4A) when said removable part (4B), initially in a first position for which said enclosure (4) is closed and encloses said second satellite, lies in a second position for which said enclosure (4) is open and able to release said satellite.

摘要翻译： 根据本发明，在固定部分（4A）和外壳（4）的可移除部分（4B）之间建立了链接，其中第二卫星预先被封闭，所述链节使得所述可移除部分（4B）保持 当所述可移除部分（4B）最初处于所述外壳（4）关闭并包围所述第二卫星的第一位置时，所述固定部分（4A）位于所述外壳（4）打开的第二位置 并能释放所述卫星。

公开(公告)号：US20130214464A1

公开(公告)日：2013-08-22

申请号：US13771381

申请日：2013-02-20

申请人： EADS CASA ESPACIO S.L.

发明人： Miguel Lancho Doncel

IPC分类号： F16F7/00

CPC分类号： F16F7/00 ,  B64G1/641 ,  F16F1/20 ,  F16F1/368 ,  F16F15/022 ,  F16F15/073

摘要： A device used for providing dynamic isolation and damping of dynamic vibrations, in a passive way, originated in the launch vehicle of a space shuttle and reaching the payload or satellite. The device comprises a plurality of identical elementary unit elements, such that the device is designed in a modular way, allowing the individual modularity of each of the elementary unit elements. Each of the elementary unit elements is tailored and designed individually, and the complete device can be designed for each particular application and payload needed as a function of each of the elementary unit elements allowing an easy design and lower costs, for a wide range of payload applications. Each elementary unit element comprises a spring component and a damping component, such that the functionalities provided for each component are separated and can be individually tailored, thus providing a device having a wider range of adaptation capabilities.

公开(公告)号：US08393582B1

公开(公告)日：2013-03-12

申请号：US12903119

申请日：2010-10-12

申请人： Bernard Friedrich Kutter ,  Jonathan D. Barr ,  Mari E. Gravlee ,  Gerard P. Szatkowski ,  Frank C. Zegler

发明人： Bernard Friedrich Kutter ,  Jonathan D. Barr ,  Mari E. Gravlee ,  Gerard P. Szatkowski ,  Frank C. Zegler

IPC分类号： B64G1/42

CPC分类号： B64G1/402 ,  B64G1/002 ,  B64G1/641

摘要： A launch system is provided which includes a secondary payload. The secondary payload includes a propellant tank and at least one module that is supported by an adapter ring that is commonly used to secure an upper stage to a primary payload. The propellant tank is launched empty and subsequently filled with residual propellant from the upper stage.

摘要翻译： 提供了一种启动系统，包括辅助有效载荷。 辅助有效载荷包括推进剂罐和至少一个由适配器环支撑的至少一个模块，该适配器环通常用于将上部级固定到主要有效载荷。 推进剂罐发射空，随后从上层充满残留的推进剂。

公开(公告)号：US20120317753A1

公开(公告)日：2012-12-20

申请号：US13164414

申请日：2011-06-20

申请人： Randall E. Simons ,  Steven Lee Wittmer ,  James S. Bray

发明人： Randall E. Simons ,  Steven Lee Wittmer ,  James S. Bray

IPC分类号： B65D63/00 ,  B23P17/00 ,  B23P11/00

CPC分类号： B64G1/641 ,  Y10T24/1412 ,  Y10T24/1414 ,  Y10T24/1439 ,  Y10T24/1441 ,  Y10T24/1451 ,  Y10T29/49766 ,  Y10T29/49959

摘要： Techniques for detachably joining a first component and a second component includes a band clamp, a tensioning device, a plurality of shoes, and a plurality of brackets. The band clamp is configured to cause the plurality of shoes to engage an abutting cylindrical flange of each of the first component and the second component and to provide a sufficient clamping pressure to join the first component with the second component. Each of the plurality of brackets is attached to one of the first component and the second component. The sufficient clamping pressure results from redundant, independently inspectable, sources, a primary redundant source being circumferential tension in the band clamp, caused by tightening the tensioning device, to produce a first radial restraining force on the shoes, and a secondary redundant source being a second radial restraining force, applied by way of the plurality of brackets, to the band clamp.

摘要翻译： 用于可拆卸地接合第一部件和第二部件的技术包括带夹，张紧装置，多个鞋和多个托架。 带夹被构造成使得多个鞋子接合第一部件和第二部件中的每一个的邻接的圆柱形凸缘并且提供足够的夹紧压力以将第一部件与第二部件接合。 多个托架中的每一个附接到第一部件和第二部件中的一个。 足够的夹紧压力来自冗余的，可独立检查的源，主要冗余源是带夹中的周向张力，由紧固张紧装置引起，以在鞋上产生第一径向约束力，并且辅助冗余源为 通过多个托架施加的第二径向约束力到带夹。

公开(公告)号：US20120217348A1

公开(公告)日：2012-08-30

申请号：US13399732

申请日：2012-02-17

申请人： Miguel Aguirre Martinez

发明人： Miguel Aguirre Martinez

IPC分类号： B64G1/10 ,  B64G1/44 ,  G02B23/02 ,  B64G1/24 ,  B64G1/66 ,  B64G1/40 ,  B64G1/58

CPC分类号： B64G1/1021 ,  B64G1/1085 ,  B64G1/405 ,  B64G1/44 ,  B64G1/503 ,  B64G1/641

摘要： Embodiments of an Earth observation satellite comprising a satellite main body having an elongated shape extending in the direction of a roll axis R of the satellite from a first base face of the satellite main body to a second base face of the satellite main body, the satellite main body having a plurality of lateral faces extending from the first base face to the second base face; a solar array; and propulsion means for compensating air-drag being arranged on the base face of the satellite main body. A first solar panel of the solar array is mounted on a first lateral face of the satellite main body, a second lateral face of the satellite main body is configured to radiate heat away from the satellite main body, and a third lateral face of the satellite main body has observation means for Earth observations.

摘要翻译： 地球观测卫星的实施例包括卫星主体，卫星主体具有沿着卫星的滚动轴线R的方向从卫星主体的第一基面延伸到卫星主体的第二基面的细长形状，卫星 主体具有从第一基面延伸到第二基面的多个侧面; 太阳能阵列 以及用于补偿空气阻力的推进装置，其布置在卫星主体的基面上。 太阳能阵列的第一太阳能电池板安装在卫星主体的第一侧面上，卫星主体的第二侧面被配置成从卫星主体辐射热量，卫星的第三侧面 主体具有地球观测观测手段。