公开(公告)号：US06523784B2

公开(公告)日：2003-02-25

申请号：US09957802

申请日：2001-09-21

申请人： Frank Steinsiek ,  Hansjuergen Guenther ,  Bernd Bischof

发明人： Frank Steinsiek ,  Hansjuergen Guenther ,  Bernd Bischof

IPC分类号： B64G164

CPC分类号： B64G1/1078 ,  B64G1/641 ,  B64G1/646 ,  B64G4/00

摘要： A recovery craft with a coupling arrangement captures, engages, and transports a defective or expended non-maneuverable spacecraft. The coupling arrangement includes a coupling mast (e.g. a telescoping pipe), a releasable rigid mount that secures one end of the coupling mast to the recovery craft, and spreader arms that are radially spreadable from the other end of the coupling mast. The spreader arms are initially radially inwardly retracted, and are inserted into an interface ring of the spacecraft. Then the spreader arms are radially outwardly extended to engage behind a protruding rim of the interface ring. A spring braces against the spacecraft. Next, the rigid mount is released and the coupling mast remains connected to the recovery craft only by a tension-transmitting cable. Thrusters of the recovery craft are activated to tow the spacecraft to a new target position, orbit, or trajectory.

公开(公告)号：US06305871B1

公开(公告)日：2001-10-23

申请号：US09334141

申请日：1999-06-15

申请人： Miguel Lancho Doncel ,  Enrique Cabrera Revuelta ,  Fernando Cespedosa Castan

发明人： Miguel Lancho Doncel ,  Enrique Cabrera Revuelta ,  Fernando Cespedosa Castan

IPC分类号： B64G164

CPC分类号： B64G1/641 ,  B64G1/002 ,  F16F3/00 ,  F16F7/00 ,  Y10T74/2132 ,  Y10T403/50 ,  Y10T403/593

摘要： A system for the modification of the rigidity and damping properties of structural joints comprises at least an intermediate structure (3) to receive, on both sides, two structures (1, 2) to be coupled; releasable blocking means (6) to immobilize, in a coupled condition, said two structures to be coupled and said intermediate structure; first and second sets of bistable components (7, 8), the structural resistance features of the components of the first set being different from those of the second set; the components of the first set being internally connected to one of said structures to be coupled and to said intermediate structure; the components of the second set being internally connected to one and other of said structures to be coupled; said bistable components being in an unstable condition when all the mentioned structures are coupled together. The invention is applicable to the field of space vehicles.

摘要翻译： 用于改变结构接头的刚度和阻尼特性的系统包括至少一个中间结构（3），用于在两侧接纳两个待耦合的结构（1,2）; 可释放的阻挡装置（6），用于在耦合状态下固定所述待耦合的两个结构和所述中间结构; 第一组和第二组双稳态部件（7,8），第一组件的部件的结构电阻特征与第二组组件的结构电阻特征不同; 所述第一组件的部件内部连接到要联接的所述结构中的一个并且连接到所述中间结构; 所述第二组件的部件内部连接到要联接的所述结构中的一个和另一个; 当所有提到的结构连接在一起时，所述双稳态组件处于不稳定状态。 本发明适用于太空车辆领域。

公开(公告)号：US06557802B2

公开(公告)日：2003-05-06

申请号：US10012566

申请日：2001-12-12

申请人： Juergen Kroeker

发明人： Juergen Kroeker

IPC分类号： B64G164

CPC分类号： B64G1/641 ,  B64G1/002 ,  B64G1/1085 ,  B64G1/645

摘要： A separation frame for mounting and separating satellites in a launch vehicle, includes two congruent frames (10, 12) are arranged one inside the other. The frames are connected to each other by means of a swivel joint.

公开(公告)号：US06485213B1

公开(公告)日：2002-11-26

申请号：US09704702

申请日：2000-11-03

申请人： Daniel Viale

发明人： Daniel Viale

IPC分类号： B64G164

CPC分类号： B64G1/222 ,  B64G1/443 ,  B64G1/645 ,  Y10T403/1608 ,  Y10T403/1624 ,  Y10T403/32467 ,  Y10T403/32483

摘要： A system including a retaining member passing through an element and connected at one end to a structure and bearing at the other end on an external side of the element; a separating mechanism for separating the member from the structure to move the element from a folded position to a deployed position; and a drive mechanism for pulling the corresponding part of the retaining member outwards after actuation of the separator mechanism. The system has a device which includes a barrel receiving the retaining member concentrically, cut-outs in the wall of the barrel forming spring tongues adapted to be bent wholly or partially towards the inside of the barrel in order to come into contact with the part, an enlargement of which is adapted to cooperate with the tongues to hold the member after actuation of the drive mechanism.

摘要翻译： 一种系统，包括通过元件的保持构件并且在一端连接到结构并且在另一端处在所述元件的外侧上承载; 用于将构件与结构分离以将元件从折叠位置移动到展开位置的分离机构; 以及用于在分离器机构致动之后向外拉动保持构件的相应部分的驱动机构。 该系统具有一个装置，该装置包括同心地容纳保持构件的桶，在桶的壁中切口形成弹簧舌片，其适于全部或部分地朝向筒体的内部弯曲以与部件接触， 其扩大部件适于与舌头配合以在驱动机构致动之后保持构件。

公开(公告)号：US06547476B2

公开(公告)日：2003-04-15

申请号：US09375721

申请日：1999-08-17

申请人： Mark Kaszubowski ,  Christopher Kerley

发明人： Mark Kaszubowski ,  Christopher Kerley

IPC分类号： B64G164

CPC分类号： B64G1/641 ,  B64G1/222 ,  B64G1/645 ,  Y10T403/59 ,  Y10T403/591 ,  Y10T403/593

摘要： An integrated separation system and interface structure is disclosed for a variety of deployment applications. In one embodiment, a Universal Spacecraft Separation Node (100) includes a separation nut assembly (102), a separation spring assembly (104) an LV node fitting (106) and an SC node fitting (108). The LV node fitting (106) is connected to a launch vehicle (210) and the SC node fitting (108) is connected to a spacecraft (216). The separation nut assembly (102) holds the fittings (106 and 108) together until separation is desired. Upon separation, the separation spring assembly (104) provides a force to urge the launch vehicle (210) and spacecraft (216) apart. Prior to separation, an annular tongue (224) of fitting (108) mates with an annular groove (226) of fitting (106) to resist shear forces.

摘要翻译： 公开了用于各种部署应用的集成分离系统和接口结构。 在一个实施例中，通用航天器分离节点（100）包括分离螺母组件（102），分离弹簧组件（104）LV节点配件（106）和SC节点配件（108）。 LV节点配件（106）连接到运载火箭（210），并且SC节点配件（108）连接到航天器（216）。 分离螺母组件（102）将配件（106和108）保持在一起，直到需要分离。 在分离时，分离弹簧组件（104）提供力以将运载火箭（210）和航天器（216）分开。 在分离之前，配件（108）的环形舌片（224）与配件（106）的环形槽（226）配合以抵抗剪切力。

公开(公告)号：US06508437B1

公开(公告)日：2003-01-21

申请号：US10050066

申请日：2002-01-15

申请人： Toren S. Davis ,  Jack H. Jacobs ,  Steven L. Hadden

发明人： Toren S. Davis ,  Jack H. Jacobs ,  Steven L. Hadden

IPC分类号： B64G164

CPC分类号： F16F9/56 ,  B64G1/641 ,  B64G1/645 ,  F16F13/00 ,  F16F2224/0258 ,  Y10S292/66 ,  Y10T292/20

摘要： A spacecraft payload, suspended by an isolator, is locked down during launch by using a compliant member to pull on a pin, clamping the payload against the launch lock. The payload is unlocked, after launch, by heating a shape memory alloy to move the pin to overcome the compliant member, releasing the payload from launch lock. The payload may be re-locked for reentry by heating another shape memory alloy to push the pin against the other shaped memory alloy.

摘要翻译： 由隔离器悬挂的航天器有效载荷在发射过程中通过使用柔性构件拉动销来锁定，将有效载荷夹紧在发射锁上。 有效载荷在发射后被解锁，通过加热形状记忆合金以移动引脚以克服顺应性构件，从发射锁释放有效载荷。 可以通过加热另一形状记忆合金来将有效载荷重新锁定以重新进入，以将销推到另一形状的记忆合金上。

公开(公告)号：US06357699B1

公开(公告)日：2002-03-19

申请号：US09578666

申请日：2000-05-25

申请人： Donald L. Edberg ,  Michael J. Tracy

发明人： Donald L. Edberg ,  Michael J. Tracy

IPC分类号： B64G164

CPC分类号： B64G1/645 ,  B64G1/002 ,  B64G1/641

摘要： A tension-relieving apparatus for reducing a level of tension in a structure. The tension-relieving apparatus includes a housing, a piston, a spacer member and a heat source. The housing has a wall member that defines a piston cavity. A rod aperture is formed in a first end of the wall member. The piston assembly has a rod and a piston. The rod extends through the rod aperture. The piston is disposed in the piston cavity and is coupled to an end of the rod. The spacer member is disposed in the piston cavity and is coupled to the piston assembly. The spacer member is transformable between a first condition and a second condition, with the first condition maintaining the piston at a first distance from the first end of the housing. The heat source is coupled to one of the housing, the piston assembly, and or the spacer member and provides heat to selectively cause the spacer member to transform to the second condition wherein the spacer member at least partially melts to permit the rod to advance toward the first end of the housing. Advancement of the piston toward the first end of the housing relieves a predetermined portion of the tension in the structure.

摘要翻译： 一种用于减小结构中的张力水平的张力释放装置。 张力释放装置包括壳体，活塞，间隔件和热源。 壳体具有限定活塞腔的壁构件。 杆壁形成在壁构件的第一端中。 活塞组件具有杆和活塞。 杆延伸穿过杆孔。 活塞设置在活塞腔中并且联接到杆的端部。 隔离构件设置在活塞腔中并联接到活塞组件。 间隔件可以在第一状态和第二状态之间变换，其中第一状态将活塞保持在离开壳体的第一端的第一距离处。 热源联接到壳体，活塞组件和/或间隔件中的一个，并且提供热量以选择性地使间隔件转换到第二状态，其中间隔件至少部分熔化以允许杆朝向 住房的第一端。 朝向壳体的第一端部的活塞的前进减轻结构中的张力的预定部分。

公开(公告)号：US06227495B1

公开(公告)日：2001-05-08

申请号：US09228033

申请日：1998-12-10

申请人： Richard T. Howard ,  Michael L. Book ,  Thomas C. Bryan

发明人： Richard T. Howard ,  Michael L. Book ,  Thomas C. Bryan

IPC分类号： B64G164

CPC分类号： G05D1/0225 ,  B64G1/24 ,  B64G1/36 ,  B64G1/646 ,  G05D1/0234 ,  G05D1/0883

摘要： A synchronized target subsystem for use in an automated docking system for docking a chase vehicle with a target vehicle wherein the chase vehicle is provided with a video camera for feeding digitized frames to an image processing unit which controls a timing circuit. The timing circuit turns on the video camera to digitize a foreground frame and at the same time turns on a transmitter on the chase vehicle. A power generating antenna on the target vehicle receives the transmitted signal from the transmitter and actuates lights on the chase vehicle so that these lights appear in the foreground frame. After the foreground frame has been grabbed, the timing circuit turns the transmitter off and signals the video camera to digitize a background frame. The image processing unit subtracts the background frame from the foreground frame and provides a docking signal.

摘要翻译： 一种用于自动对接系统的同步目标子系统，用于将追逐车辆与目标车辆对准，其中追逐车辆设置有用于将数字化帧馈送到控制定时电路的图像处理单元的摄像机。 定时电路打开摄像机数字化前景帧，同时打开追车的变送器。 目标车辆上的发电天线接收来自发射器的发射信号，并且启动追车上的灯，使得这些光出现在前景帧中。 在前景帧被抓住之后，定时电路关闭发射机，并向视频摄像机通知数字化背景帧。 图像处理单元从前景帧中减去背景帧并提供对接信号。

公开(公告)号：US06789767B2

公开(公告)日：2004-09-14

申请号：US10132083

申请日：2002-04-23

申请人： George E. Mueller ,  David B. Cochran ,  Richard H. Kohrs

发明人： George E. Mueller ,  David B. Cochran ,  Richard H. Kohrs

IPC分类号： B64G164

CPC分类号： B64G1/26 ,  B64G1/007 ,  B64G1/1085 ,  B64G1/222 ,  B64G1/641 ,  B64G1/645

摘要： An active satellite dispenser is preferably attachable to a reusable launch vehicle for deployment of one or more satellites into one or more desired orbits. The active satellite dispenser includes a center mast that releasably receives the satellite(s), a liquid propellant rocket, and an orbital control system on an avionics pallet. In the preferred embodiment, a pressurized gas selectively pressurizes the propellant tanks (which may include fuel and oxidizer tanks), to provide propellant to the rocket. In operation, the launch vehicle releases the satellite dispenser in a first deployment orbit. The active dispenser rocket and orbital control system then transport the active dispenser and satellite(s) into the final deployment orbit. In the preferred embodiment the active dispenser can operate multiple times to place individual satellites in different orbits.

摘要翻译： 主动卫星分配器优选地可附接到可重复使用的运载火箭上，用于将一个或多个卫星部署到一个或多个所需轨道中。 主动卫星分配器包括可释放地接收卫星的中心桅杆，液体推进剂火箭和航空电子托盘上的轨道控制系统。 在优选实施例中，加压气体选择性地使推进剂罐（其可以包括燃料和氧化剂罐）加压，以向火箭提供推进剂。 在运行中，运载火箭在第一部署轨道上释放卫星分配器。 主动分配器火箭和轨道控制系统然后将主动分配器和卫星运送到最终部署轨道。 在优选实施例中，主动分配器可以多次操作以将各个卫星放置在不同的轨道中。

公开(公告)号：US06729582B2

公开(公告)日：2004-05-04

申请号：US10203644

申请日：2002-11-07

申请人： Jean-Claude Beyer

发明人： Jean-Claude Beyer

IPC分类号： B64G164

CPC分类号： B64G1/641 ,  B64G1/002 ,  B64G1/222 ,  B64G1/645

摘要： A system and method for making a support base plate for an artificial satellite, including a plurality of base plates arranged in a ring on a dispenser platform, each base plate having a cylindrical wall including curved surface elements and substantially planar surface elements. The modular wall elements with curved surface and the wall elements with planar surface are arranged according to a predetermined base plate geometry, and these elements are assembled along their adjacent edges to produce the base plate cylindrical wall.

摘要翻译： 一种用于制造用于人造卫星的支撑基板的系统和方法，包括在分配器平台上以环形式布置的多个基板，每个基板具有包括弯曲表面元件和基本平坦的表面元件的圆柱形壁。 具有弯曲表面的模块化壁元件和具有平坦表面的壁元件根据预定的基板几何形状布置，并且这些元件沿其相邻边缘组装以产生基板圆柱形壁。