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    Low disturbance solar array
    121.
    发明授权
    Low disturbance solar array 失效
    低干扰太阳能阵列

    公开(公告)号：US5620529A

    公开(公告)日：1997-04-15

    申请号：US552811

    申请日：1995-11-03

    申请人： Samir F. Bassily ,  Stuart F. Bockman ,  George N. Young

    发明人： Samir F. Bassily ,  Stuart F. Bockman ,  George N. Young

    IPC分类号： B64G1/22 ,  B64G1/44 ,  H01L31/045 ,  H01L31/048

    CPC分类号： H01L31/048 ,  B64G1/222 ,  B64G1/443 ,  H02S30/20 ,  Y02E10/50 ,  Y10S136/292

    摘要： A rigid panel solar array for a spacecraft. The layers of materials for the panels are selected and oriented to control the net coefficient of thermal expansion in the array's longitudinal direction. Some of the layers are discontinuous and softly coupled to the others by flexible adhesive materials. The panels are interconnected with hinge members which are positioned at appropriate locations and with appropriate degrees of freedom so that thermally induced transverse bending does not cause transverse motion of the center-of-mass of the panels.

    摘要翻译： 用于航天器的刚性面板太阳能阵列。 选择和定向用于面板的材料层以控制阵列纵向方向上的热膨胀系数。 一些层通过柔性粘合剂材料不连续并且轻柔地耦合到其它层。 这些面板与铰链构件互连，铰链构件定位在适当的位置并具有适当的自由度，使得热诱导的横向弯曲不会引起面板质心的横向运动。

    Satellite stabilization system
    122.
    发明授权
    Satellite stabilization system 失效
    卫星稳定系统

    公开(公告)号：US5618012A

    公开(公告)日：1997-04-08

    申请号：US371821

    申请日：1995-01-12

    申请人： John A. Lehner ,  Thomas Holmes

    发明人： John A. Lehner ,  Thomas Holmes

    IPC分类号： B64G1/24 ,  B64G1/40 ,  B64G1/44 ,  G05D1/08

    CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/407 ,  B64G1/44

    摘要： A satellite stabilization system compensates for the destabilizing torque introduced by solar radiation pressure by the emplacement of tabs of material angled relative to the back surfaces of the antenna reflectors to intercept solar rays. The material of the tabs interacts with the solar radiation in substantially the same manner as the interaction of the material on the back surface of each antenna reflector to produce a radiation pressure and consequential increment in a torque about an axis of the satellite. Each of the tabs is constructed in the manner of a plate or disk, and is attached by means of a spring mount to the back surface of one of the reflectors. The reflectors are angled relative to each other, as well as to a body of the satellite which holds feeds for illuminating the reflectors, for directing beams of radiation from the feeds towards the earth. Due to the angulation of the reflectors to each other, the total solar energy incident upon a pair of of the reflectors is generally unequal, this resulting in a net torque from the solar radiation pressure which tends to rotate the satellite. By virtue of the angulation of the tabs relative to the reflectors, an increased amount of solar radiation is received by the reflector which is angled away from the sun's rays, thereby to equalize the torque from both of the reflectors.

    摘要翻译： 卫星稳定系统补偿由太阳辐射压力引入的不稳定扭矩，通过放置相对于天线反射器的后表面成角度的突片，以拦截太阳光线。 翼片的材料以与每个天线反射器的背面上的材料的相互作用基本相同的方式与太阳辐射相互作用，以产生围绕卫星的轴线的转矩的辐射压力和相应的增量。 每个突片以板或盘的方式构造，并且通过弹簧安装件附接到一个反射器的背面。 反射器相对于彼此成角度，以及卫星的主体，其保持用于照射反射器的馈送物，用于将来自馈电的辐射束引导到地球。 由于反射器彼此成角度，入射到一对反射器上的总太阳能通常是不相等的，这导致来自倾向于使卫星旋转的太阳辐射压力的净转矩。 由于凸片相对于反射器的角度，太阳辐射量的增加被反射器所接收，该反射器远离太阳光线成角度，从而平衡来自两个反射器的转矩。

    Foldable low concentration solar array
    124.
    发明授权
    Foldable low concentration solar array 失效
    可折叠低浓度太阳能电池阵列

    公开(公告)号：US5520747A

    公开(公告)日：1996-05-28

    申请号：US236426

    申请日：1994-05-02

    申请人： Geoffrey W. Marks

    发明人： Geoffrey W. Marks

    IPC分类号： B64G1/22 ,  B64G1/44 ,  F24J2/16 ,  F24J2/36 ,  H01L31/045 ,  H01L31/052

    CPC分类号： B64G1/443 ,  B64G1/222 ,  H01L31/0547 ,  H02S30/20 ,  F24J2/16 ,  F24J2/36 ,  F24J2002/5486 ,  Y02E10/52 ,  Y10S136/292

    摘要： A low concentration solar array for spacecraft and other uses which has a series of solar panels which can be deployed from a folded stowed configuration to a planar configuration. When the solar panels are stowed, the padding of reflector panels cushions and protects the solar panels from the stresses and vibrations of launch and space flight. Once the solar panels are extended into a deployed planar configuration, the reflector panels are raised to concentrate sunlight upon the solar panels. These reflector panels are constructed from rigid honeycomb substrates and therefore are the active structural members of the solar array, providing the structural rigidity for the solar array.

    摘要翻译： 一种用于航天器和其他用途的低浓度太阳能阵列，其具有可以从折叠收起的构型部署到平面构型的一系列太阳能电池板。 当太阳能电池板被收起时，反射板的衬垫缓冲并保护太阳能电池板免受发射和太空飞行的应力和振动。 一旦将太阳能电池板延伸到展开的平面结构中，则将反光板升高以将太阳光集中在太阳能电池板上。 这些反射板由刚性蜂窝基体构成，因此是太阳能阵列的主动结构构件，为太阳能阵列提供结构刚性。

    Hybrid solar rocket utilizing thermal storage for propulsion and electrical power
    126.
    发明授权
    Hybrid solar rocket utilizing thermal storage for propulsion and electrical power 失效
    混合太阳能火箭利用热存储推进和电力

    公开(公告)号：US5459996A

    公开(公告)日：1995-10-24

    申请号：US297678

    申请日：1994-08-29

    申请人： John D. Malloy, III ,  Richard F. Rochow ,  James B. Inman

    发明人： John D. Malloy, III ,  Richard F. Rochow ,  James B. Inman

    IPC分类号： B64G1/40 ,  B64G1/44 ,  F02K99/00 ,  F24S20/20 ,  F24S23/70 ,  F02G1/00

    CPC分类号： F24J2/34 ,  B64G1/409 ,  B64G1/446 ,  F24J2/07 ,  F24J2/10 ,  F24J2/51 ,  B64G1/401 ,  F02G2254/30 ,  F24J2002/4605 ,  Y02E10/41

    摘要： A solar rocket for propelling and powering the electronics of a spacecraft includes a black body cavity of thermal storage material. Propulsion tubes and a connected nozzle axially extend through the black body cavity for burning propellant in order to provide thrust for the rocket. An insulation sleeve is removably located at the outer periphery of the cavity of thermal storage material. Energy conversion diodes surround the insulation sleeve. The thermal storage material, the insulation sleeve and the energy conversion diodes form a receiver. The receiver has a pair of spaced apart holes therethrough which lead into an interior space of the black body cavity in order to receive sunlight. A mirror assembly is located near each hole of the receiver for harnessing sunlight and providing radiant energy through the holes into the internal space of the black body cavity.

    摘要翻译： 用于推进和驱动航天器电子装置的太阳能火箭包括一个黑体腔的蓄热材料。 推进管和连接的喷嘴轴向延伸穿过黑体腔，用于燃烧推进剂，以便为火箭提供推力。 绝热套可拆卸地位于蓄热材料空腔的外周。 能量转换二极管围绕绝缘套管。 蓄热材料，绝缘套管和能量转换二极管形成接收器。 接收器具有穿过其中的一对间隔开的孔，其通向黑色体腔的内部空间以接收阳光。 镜组件位于接收器的每个孔附近，用于利用阳光并通过孔向黑体腔的内部空间提供辐射能。

    Magnetic torque attitude control systems
    127.
    发明授权
    Magnetic torque attitude control systems 失效
    磁力矩姿态控制系统

    公开(公告)号：US5413293A

    公开(公告)日：1995-05-09

    申请号：US995114

    申请日：1992-12-22

    申请人： Louis Gomberg ,  Shibu Basuthakur ,  Joseph H. Hayden

    发明人： Louis Gomberg ,  Shibu Basuthakur ,  Joseph H. Hayden

    IPC分类号： B64G1/28 ,  B64G1/32 ,  B64G1/42 ,  B64G1/44 ,  G01C21/24 ,  G05D1/08 ,  B64G1/00

    CPC分类号： B64G1/428 ,  B64G1/32 ,  B64G1/443

    摘要： A magnetic torquing system for a spacecraft using conducting coils is disclosed. In one embodiment, the conductors (44, 46) on a spacecraft's (10) solar wing (28, 30) which connect the solar cell strings (38) to the voltage controller (48) are wired to produce a magnetic torque which can be regulated by shunting individual strings to ground (52) or by opening a string circuit. This embodiment does not require the extra weight of a coil because the panel's solar string produces the torque normally produced by an additional coil. In another embodiment, a coil (44, 46)is wired between a shunting switch (54) in the spacecraft voltage controller (48) and a ground (32) so that shunting a string to ground (52) supplies current first to the coil to generate a magnetic torque in the desired direction.

    摘要翻译： 公开了一种使用导电线圈的航天器的磁力扭矩系统。 在一个实施例中，将太阳能电池串（38）连接到电压控制器（48）的航天器（10）太阳能翼（28,30）上的导体（44,46）被布线以产生磁力矩，其可以是 通过将单个线分流到地（52）或通过打开串电路来调节。 该实施例不需要额外的线圈重量，因为面板的太阳能串产生通常由附加线圈产生的扭矩。 在另一个实施例中，线圈（44,46）布线在航天器电压控制器（48）中的分流开关（54）和接地（32）之间，从而将串联到地（52）将电流首先提供给线圈 以产生所需方向的磁力矩。

    Spacecraft bus regulation using solar panel position
    128.
    发明授权
    Spacecraft bus regulation using solar panel position 失效
    航天器总线调节采用太阳能电池板的位置

    公开(公告)号：US5394075A

    公开(公告)日：1995-02-28

    申请号：US987901

    申请日：1992-12-04

    申请人： Allan F. Ahrens ,  Harold A. Rosen

    发明人： Allan F. Ahrens ,  Harold A. Rosen

    IPC分类号： B64G1/42 ,  B64G1/44 ,  H02J7/35 ,  H02J7/00

    CPC分类号： B64G1/443 ,  B64G1/428 ,  H02J7/35 ,  Y10S136/292 ,  Y10S136/293 ,  Y10S320/33 ,  Y10S323/906

    摘要： A spacecraft power bus regulation method and apparatus for a spacecraft. The spacecraft has solar arrays (10) and a battery (30) coupled to the spacecraft power bus (32) to drive electrical loads (34). A bus voltage limiter (38) controls the flow of current from the solar arrays while a bidirectional battery controller (36) controls power flow into and out of the battery. A processor (46) monitors current flow and battery condition using sensors (40, 42, 44, 48) and controls the bus voltage limiter accordingly. Auxiliary control is provided by the solar array drive (24) which controls the orientation of the solar arrays with respect to the sun.

    摘要翻译： 航天器电力总线调节方法和装置。 航天器具有太阳能阵列（10）和耦合到航天器电力总线（32）以驱动电力负载（34）的电池（30）。 当双向电池控制器（36）控制电流进出电池时，总线限制器（38）控制来自太阳能电池阵列的电流流动。 处理器（46）使用传感器（40,42,44,48）监视电流和电池状况，并且相应地控制总线电压限制器。 辅助控制由太阳能阵列驱动器（24）提供，太阳能阵列驱动器控制太阳能阵列相对于太阳的取向。

    Unfolding and locking joint for space elements
    129.
    发明授权
    Unfolding and locking joint for space elements 失效
    展开和锁定空间元件的关节

    公开(公告)号：US5393018A

    公开(公告)日：1995-02-28

    申请号：US149830

    申请日：1993-11-10

    申请人： Martin Roth ,  Helmut Kiendl

    发明人： Martin Roth ,  Helmut Kiendl

    IPC分类号： B64G1/22 ,  B64G1/44 ,  F16C11/10 ,  B64G1/46

    CPC分类号： F16C11/103 ,  B64G1/222 ,  B64G1/443 ,  Y10S136/292 ,  Y10T16/540243

    摘要： A joint is provided for the unfolding and locking of space elements, such as solar generator panels. On one joint half, a detent lever is swivellably connected having a clamping nose as well as a finger as the guiding element. During the unfolding operation, the finger slides on a guiding contour of the other joint half. Shortly before the fully unfolded condition is reached, the finger engages in a depression, and the clamping nose runs up onto a cam and clamps down on the latter under the effect of the spring tension directed to the common axis of rotation. A movable stop element, e.g. universal ball joint, simultaneously presses against a stop surface so that both joint halves are braced with respect to one another. An arrangement of high stiffness which is as free from play as possible results.

    摘要翻译： 提供用于空间元件（例如太阳能发电机面板）的展开和锁定的接头。 在一个关节半部，止动杆可旋转地连接，具有夹紧鼻以及作为引导元件的手指。 在展开操作期间，手指在另一个关节半部的引导轮廓上滑动。 在完全展开状态达到之前，手指接合凹陷，并且夹紧鼻子向上运动到凸轮上，并在弹簧张力的作用下向下夹紧凸轮，该弹簧张力指向公共旋转轴线。 可移动止动元件，例如 万向球接头同时按压止动表面，使得两个接合部分相对于彼此支撑。 高刚度的布置尽可能不发挥作用。

    Spacecraft designs for satellite communication system
    130.
    发明授权
    Spacecraft designs for satellite communication system 失效
    航天器设计用于卫星通信系统

    公开(公告)号：US5386953A

    公开(公告)日：1995-02-07

    申请号：US931625

    申请日：1992-08-18

    申请人： James R. Stuart

    发明人： James R. Stuart

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

    CPC分类号： B64G1/1085 ,  B64G1/1021 ,  B64G1/222 ,  B64G1/44 ,  B64G1/002 ,  Y10S136/292

    摘要： A series of spacecraft designs (10, 26 & 34) for a Satellite Communication System is disclosed. One of the preferred embodiments of the invention called "Domesat" (10) includes a hemispherical, high-gain, electronically-steered antenna array (12) that is always pointed toward the Earth (E). Hexagonal antenna panels (14) are held together by tubular and spherical connectors (22 & 24). The upper portion of the satellite (10) incorporates a space-facing array (16) of panels (18) which are always pointed toward the zenith (Z). The interior of the dome-shaped antenna array (12) is used to store solar cell panels (20) which unfurl through an opening (11) in the space-facing array (16) when the spacecraft (10) reaches its final orbit. An alternative embodiment of the invention called "Gearsat" (26) comprises a hollow torus which inflates when it reaches orbit. When viewed from the side along its circumference, "Gearsat" (26) looks like two flattened pyramids sharing a common base. Phased array antenna panels ( 29) are deployed across the top of the pyramid along an exterior cylindrical surface (28), while twin arrays of solar cells (30) cover the slanted surfaces. The satellite (26) rotates about its center, and individual antenna panels (29) are spatially synchronized to transmit and receive signals from particular regions on the ground. A third alternative embodiment called "Batsat" (34), includes a central cylindrical body (B) and a plurality of substantially circular linked antenna and solar/thermal panels (A1-A9 and S1 & S2) which carry individual antennas (X) and solar/thermal surfaces (Y). All of the embodiments (10, 26 & 34) are capable of being nested or stacked in a compact arrangement that fit within the payload bay of a launch vehicle (L).

    摘要翻译： 公开了一系列用于卫星通信系统的航天器设计（10,26和34）。 称为“Domesat”（10）的本发明的优选实施例之一包括总是指向地球（E）的半球形高增益电子转向天线阵列（12）。 六角形天线板（14）通过管状和球形连接器（22和24）保持在一起。 卫星（10）的上部包括总是指向天顶（Z）的面板（18）的面向空间的阵列（16）。 圆顶状天线阵列（12）的内部用于存储当航天器（10）到达其最终轨道时通过面向空间阵列（16）中的开口（11）展开的太阳能电池板（20）。 称为“Gearsat”（26）的本发明的替代实施例包括当其到达轨道时使其膨胀的空心圆环。 从周边看，“Gearsat”（26）看起来像两个平坦的金字塔共享共同基础。 相对阵列天线板（29）沿着外部圆柱形表面（28）横跨金字塔的顶部展开，而太阳能电池单元（30）的两个阵列覆盖倾斜表面。 卫星（26）绕其中心旋转，并且各个天线面板（29）在空间上同步以从地面上的特定区域发射和接收信号。 称为“Batsat”（34）的第三替代实施例包括中心圆柱体（B）和多个基本圆形连接的天线和太阳能/热板（A1-A9和S1＆S2），其携带单独的天线（X）和 太阳能/热表面（Y）。 所有实施例（10,26和34）能够以适合于运载火箭（L）的有效载荷舱内的紧凑布置嵌套或堆叠。