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406 条记录 (耗时 0.041 秒)

    Low shock release device
    51.
    发明授权
    Low shock release device 失效
    低减震装置

    公开(公告)号：US5718531A

    公开(公告)日：1998-02-17

    申请号：US589487

    申请日：1996-01-22

    申请人： Edward Charles Mutschler, Jr. ,  Philip Olikara ,  David George Reed

    发明人： Edward Charles Mutschler, Jr. ,  Philip Olikara ,  David George Reed

    IPC分类号： B64G1/22 ,  F16B1/00 ,  F16G11/00 ,  F16B4/00 ,  C22K1/00

    CPC分类号： F16G11/00 ,  B64G1/22 ,  F16B1/0014 ,  Y10T403/21 ,  Y10T403/23 ,  Y10T403/74

    摘要： A release device is actuated to release a workpiece by operation of either of two elongated shape memory metal alloy (SMMA) members. Each SMMA member has on one end a feature that engages a fitting on the workpiece, while its other end is mounted to a housing. A heater on each SMMA member raises its temperature to a transition temperature at which it returns to an unstressed (e.g. shorter) length, thereby releasing the workpiece. The two SMMA elements may be disposed in opposite directions from the housing or may be coaxial or offset and disposed in the same direction.

    摘要翻译： 通过两个细长形状记忆金属合金（SMMA）构件中的任一个的操作来致动释放装置以释放工件。 每个SMMA构件的一端具有与工件上的配件接合的特征，而其另一端安装到壳体。 每个SMMA构件上的加热器将其温度升高到转变温度，在此转变温度返回到不受应力（例如较短）的长度，从而释放工件。 两个SMMA元件可以设置在与壳体相反的方向上，或者可以是同轴的或偏移的并且设置在相同的方向上。

    Spacecraft antennas and beam steering methods for satellite communciation system
    52.
    发明授权
    Spacecraft antennas and beam steering methods for satellite communciation system 失效
    航天器天线和卫星通信系统的波束转向方法

    公开(公告)号：US5642122A

    公开(公告)日：1997-06-24

    申请号：US241103

    申请日：1994-05-11

    申请人： Douglas Gene Lockie ,  Mark Thomson

    发明人： Douglas Gene Lockie ,  Mark Thomson

    IPC分类号： B64G1/22 ,  H01Q1/28 ,  H01Q25/00 ,  H04B7/204 ,  H01Q1/08

    CPC分类号： B64G1/22 ,  H01Q1/288 ,  H01Q25/00 ,  H04B7/2041 ,  Y10S343/02

    摘要： An advanced active element phased array satellite antenna is disclosed. Incorporating these novel antenna systems on a constellation of low Earth orbit spacecraft, allows phone customers worldwide to communicate through a system whose switching intelligence resides on orbit, bypassing traditional land-based networks, and offering a revolutionary expansion of communications potential. The present invention utilizes electronic beam steering is utilized to provide extremely high gain signals. In one preferred embodiment, a satellite (S) includes an Earth-facing array (10) of hexagonal antenna facets (12), mated together along their sides to form a slightly flattened, hemispherical shell. The antenna array (10) is connected to two rectilinear, unfurled, solar panels (P). The antennas (10) transmit and receive signals from terrestrial units located within the footprints (14) of the beams (11). Another embodiment (34) uses deployable, folding panels (41) which maximize panel surface area for a given weight and launch vehicle container volume. The panels (41) are stacked upon a central plate (39) along the depth axis of the container in accordion fold layers and are separately deployed radially from the center (C) of the central plate (39). The contour of the deployed panels permit the antenna beam footprints (14) to cover the desired area.

    摘要翻译： 公开了一种先进的有源元件相控阵卫星天线。 将这些新颖的天线系统结合在低地球轨道航天器的星座上，使得全球的电话客户能够通过交换智能驻扎在轨道上的系统进行通信，绕过传统的陆基网络，并提供革命性的通信潜力。 本发明利用电子束操纵来提供极高的增益信号。 在一个优选实施例中，卫星（S）包括六边形天线小面（12）的接地阵列（10），沿着它们的侧面配合在一起以形成稍微扁平的半球形壳体。 天线阵列（10）连接到两个直线，未铺展的太阳能电池板（P）。 天线（10）从位于波束（11）的足迹（14）内的地面单元发射和接收信号。 另一个实施例（34）使用可展开的折叠面板（41），其对于给定的重量和运载车辆容器容积最大化面板表面积。 面板（41）沿着容纳折叠层的容器的深度轴线堆叠在中心板（39）上，并且与中心板（39）的中心（C）分开展开。 所展开的面板的轮廓允许天线束足迹（14）覆盖所需的区域。

    Digital image system for determining relative position and motion of in-flight vehicles
    53.
    发明授权
    Digital image system for determining relative position and motion of in-flight vehicles 失效
    用于确定飞行中车辆的相对位置和运动的数字图像系统

    公开(公告)号：US5493392A

    公开(公告)日：1996-02-20

    申请号：US247922

    申请日：1994-05-23

    申请人： James B. Blackmon ,  Kenneth W. Stone

    发明人： James B. Blackmon ,  Kenneth W. Stone

    IPC分类号： B64G1/22 ,  B64G1/36 ,  G01B11/26

    CPC分类号： B64G1/36 ,  B64G1/22

    摘要： The system includes a reflector assembly mounted on a first one of a pair of spacecraft. The reflector assembly includes a mirror around which are positioned a mirror and retroreflectors. A light source mounted on the second spacecraft illuminates the assembly the reflections from which are directed into a radiometer which is also mounted on the second spacecraft. The mirror has a known curvature, and the known curvature in conjunction with the retroreflectors allow calculation of the position and motion parameters of the first spacecraft relative to the second.

    摘要翻译： 该系统包括安装在一对航天器中的第一个上的反射器组件。 反射器组件包括反射镜，反射镜周围设有反射镜和后向反射器。 安装在第二航天器上的光源照射组件，其反射被引导到也安装在第二航天器上的辐射计。 反射镜具有已知的曲率，并且与回射器结合的已知曲率允许计算第一航天器相对于第二航空器的位置和运动参数。

    Method and apparatus for disposal/recovery of orbiting space debris
    56.
    发明授权
    Method and apparatus for disposal/recovery of orbiting space debris 失效
    用于处理/回收轨道空间碎片的方法和装置

    公开(公告)号：US5421540A

    公开(公告)日：1995-06-06

    申请号：US937057

    申请日：1992-08-26

    申请人： Paul C. Ting

    发明人： Paul C. Ting

    IPC分类号： B64G1/22 ,  B64G1/62 ,  B64G1/64

    CPC分类号： B64G1/1078 ,  B64G1/22 ,  B64G1/62 ,  B64G1/646

    摘要： Method and apparatus for elimination of space debris from Earth orbit to thus minimize the hazards to space personnel and equipment that are now present as increasing as space exploration and use continues. As a first aspect space debris is collected and deorbited where it is completely burned by the heat developed by the kinetic energy of its reentry through the Earth's atmosphere. As a second aspect, valuable space debris is collected and deorbited in a recovery reentry vehicle and which lands at a designated site on the Earth's surface. A third method includes parking collected space debris in a designated parking orbit at a location well away from traveled orbit zones, including a high, relatively unused orbit sector. A fourth method includes solar and laser energy destruction of the non-valuable space debris while in orbit. A fifth aspect of this invention contemplates ejecting collected, containerized space debris from Earth orbit to an interplanetary orbit that does not intersect any planet of this solar system. The last method is to immediately remove the space debris after any new activities in space.

    摘要翻译： 从地球轨道消除空间碎片的方法和装置，从而尽可能减少空间人员和设备的危害，这些空间人员和设备随着空间探索和使用的不断增加而逐渐增加。 作为第一个方面，空间碎片被收集和脱气，在其被再次通过地球大气层的动能所产生的热量完全燃烧的地方。 作为第二个方面，收集有价值的空间碎片并在恢复折返车辆中脱轨，并且其落在地球表面上的指定地点。 第三种方法包括将收集的空间碎片停放在远离行进轨道区域的位置（包括较高的相对未使用的轨道部分）的指定停车轨道中。 第四种方法包括太阳能和激光能量在轨道上破坏非贵重空间碎片。 本发明的第五方面考虑将所收集的集装箱空间碎片从地球轨道喷射到不与该太阳系的任何行星相交的行星际轨道。 最后一种方法是在太空中的任何新活动之后立即清除空间碎片。

    RF plasma source and antenna therefor
    57.
    发明授权
    RF plasma source and antenna therefor 失效
    射频等离子体源和天线

    公开(公告)号：US5418431A

    公开(公告)日：1995-05-23

    申请号：US113144

    申请日：1993-08-27

    申请人： Weldon S. Williamson ,  Barret Lippey ,  John D. Williams

    发明人： Weldon S. Williamson ,  Barret Lippey ,  John D. Williams

    IPC分类号： B01J19/08 ,  B08B7/00 ,  B64G1/22 ,  B64G1/66 ,  C23G5/00 ,  H01J27/16 ,  H05H1/46 ,  H01J7/24

    CPC分类号： B64G1/66 ,  B08B7/0035 ,  B64G1/22 ,  H05H1/46

    摘要： Contaminants are cleaned from the surface of a body in space by generating a substantially space-charge neutral reactive plasma, directing the plasma onto the contaminated surface at an energy below the surface sputtering energy (typically 20 eV), and reacting the plasma with the contaminants to remove them. A helicon wave plasma source is made light weight and compact enough for spacecraft use, with a plasma energy low enough to avoid damaging optical surfaces, by using permanent magnets to establish a static axial magnetic field, and a simple but novel rf antenna design. The antenna consists of a pair of spaced conductive rings which extend around the plasma tube, with conductive base and rf feed bars extending between the rings on diametrically opposite sides. The feed bar is interrupted to provide an rf input on opposite sides of the interruption. The antenna is preferably formed as an integral metal unit, with its rings rigidly supported by and integral with opposite ends of the base bar. The plasma source is also useful in neutralizing localized charges on the spacecraft.

    摘要翻译： 通过产生基本上空间电荷的中性反应等离子体，将空气中的污染物从空间的表面清洁，将等离子体以低于表面溅射能量（通常为20eV）的能量引导到污染表面上，并使等离子体与污染物 去除它们。 螺旋波等离子体源的重量轻且足够紧凑，用于航天器的使用，等离子体能量足够低以避免损坏的光学表面，通过使用永磁体建立静态轴向磁场，以及简单而新颖的射频天线设计。 天线由一对间隔开的导电环组成，其间围绕等离子体管延伸，导电基底和射频馈送棒在直径相对的两侧的环之间延伸。 进给杆被中断以在中断的相对侧提供rf输入。 天线优选地形成为一体的金属单元，其环由基条的相对端刚性地支撑并与其一体形成一体。 等离子体源还可用于中和航天器上的局部电荷。

    Multivariable adaptive surface control
    58.
    发明授权
    Multivariable adaptive surface control 失效
    多变量自适应表面控制

    公开(公告)号：US5374011A

    公开(公告)日：1994-12-20

    申请号：US791899

    申请日：1991-11-13

    申请人： Kenneth B. Lazarus ,  Edward F. Crawley

    发明人： Kenneth B. Lazarus ,  Edward F. Crawley

    IPC分类号： B64C3/48 ,  B64G1/22 ,  B64G1/24 ,  B64G1/36 ,  G05D1/08 ,  B64G5/00

    CPC分类号： B64C3/48 ,  B64G1/22 ,  B64G1/24 ,  B64G1/36 ,  G05D1/0825

    摘要： An adaptive sheet structure with distributed strain actuators is controlled by a dynamic compensator that implements multiple input, multiple output control laws derived by model-based, e.g., Linear Quadratic Gaussian (LQG) control methodologies. An adaptive lifting surface is controlled for maneuver enhancement, flutter and vibration suppression and gust and load alleviation with piezoceramic elements located within, or enclosed by sheets of composite material at a particular height above the structure's neutral axis. Sensors detect the amplitudes of lower order structural modes, and distributed actuators drive or damp these and other modes. The controller is constructed from an experimental and theoretical model using conventional control software, with a number of event recognition patterns and control algorithms programmed for regulating the surface to avoid instabilities. The number of control states of the compensator is then reduced by removing states having negligible effects on the plant, and a smaller set of control laws are optimized and then adjusted based on analytical models bench and wind-tunnel testing.

    摘要翻译： 具有分布式应变致动器的自适应板结构由动态补偿器控制，动态补偿器实现基于模型的例如线性二次高斯（LQG）控制方法得到的多输入多输出控制规律。 控制自适应提升表面，用于机动增强，颤振和振动抑制，以及位于结构中性轴线上方特定高度处的复合材料薄片内或由复合材料薄片包围的压电陶瓷元件的阵风和负载减轻。 传感器检测低阶结构模式的幅度，分布式执行器驱动或抑制这些和其他模式。 控制器由使用常规控制软件的实验和理论模型构建，具有许多事件识别模式和编程用于调节表面的控制算法以避免不稳定性。 然后通过去除对工厂具有可忽略的影响的状态来减少补偿器的控制状态的数量，并且基于分析模型台架和风洞测试来优化较小的一组控制规律，然后进行调整。

    Multiple application paraboloid spacecraft structure
    59.
    发明授权
    Multiple application paraboloid spacecraft structure 失效
    多应用抛物面飞船结构

    公开(公告)号：US5350137A

    公开(公告)日：1994-09-27

    申请号：US64389

    申请日：1993-05-19

    申请人： Mark W. Henley

    发明人： Mark W. Henley

    IPC分类号： B64G1/00 ,  B64G1/10 ,  B64G1/22 ,  B64G1/44 ,  B64G1/64

    CPC分类号： B64G1/22 ,  B64G1/1085 ,  B64G1/641 ,  B64G1/002 ,  B64G1/44

    摘要： A combined application paraboloid spacecraft structure that is adapted to serve as a structural element for space transportation vehicles, and in additional applications, as a separated spacecraft. The primary structure of the combined application paraboloid spacecraft structure is shaped as the shell of a paraboloid of revolution which has focusing properties for use in such functions as a solar power concentrator, a surveillance or an astronomical telescope, or a communications antenna when deployed in space. The primary structure of this combined application paraboloid can nest and can also be used to support other single or multiple host spacecraft during launch and orbit to orbit transportation. The convex side of the combined application paraboloid primary structure is designed to receive and support auxiliary equipment for combined application paraboloid spacecraft and space transportation vehicles, such as command and control equipment, communications equipment, thrusters, power supplies, and solar power collector panels.The multiple application spacecraft may be employed with a single host spacecraft or a plurality of host spacecraft, or a plurality of such multiple application paraboloid spacecraft may be nested together in a self supporting/protecting stack for launch. The primary structure may also be employed itself as a protective fairing or other aerothermodynamic shield, or in a support function for equipment carried on space transportation vehicles.

    摘要翻译： 一种适用于空间运输车辆的结构部件的应用抛物面飞行器结构，以及作为分离的航天器的其他应用。 组合应用抛物面航天器结构的主要结构形状为旋转抛物面的外壳，其具有聚焦性能，用于诸如太阳能集中器，监视或天文望远镜或在部署在太空中时的通信天线 。 这种组合应用抛物面的主要结构可以嵌套，也可以用于在发射和轨道运输过程中支持其他单个或多个主机航天器。 组合式应用抛物面主结构的凸面设计用于接收和支持组合式应用抛物面飞船和空间运输车辆的辅助设备，如指挥控制设备，通信设备，推进器，电源和太阳能集热板。 多应用航天器可以与单个主机航天器或多个主机航天器一起使用，或者多个这种多应用抛物面宇宙飞船可以嵌套在自支撑/保护堆栈中用于发射。 主要结构也可以自身用作保护性整流罩或其他空气热力学屏障，或者用于空间运输车辆上运载的设备的支撑功能。