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    Satellite having a stackable configuration
    2.
    发明公开
    Satellite having a stackable configuration 失效
    具有可堆叠配置的卫星

    公开(公告)号：EP0669251A2

    公开(公告)日：1995-08-30

    申请号：EP94120968.6

    申请日：1994-12-30

    申请人： ORBITAL SCIENCES CORPORATION

    发明人： Steffy, David Alan ,  Robinson, Anthony D.

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

    CPC分类号： B64G1/641 ,  B64G1/002 ,  B64G1/1007 ,  B64G1/1085 ,  B64G1/222 ,  B64G1/44 ,  B64G1/645 ,  B64G2001/643 ,  Y10S136/292

    摘要： A satellite (10) has two solar array panels (40,42) which are moveable between a closed configuration and an open configuration. The solar array panels are pivotably mounted on hinges (44,46) attached along the top and bottom of the satellite and extend outwardly from the top and bottom of the satellite in the open configuration. The height of the perimeter sidewall (14) is selected such that the satellite has a generally oblate configuration. Each solar array panel has a surface area substantially equal to that of the satellite cross-sectional area. The hinges (44,46) are mounted on pintles (48,50) extending from a solar array drive motor (58) which rotates the solar panel about the axis defined by the pintles to provide one axis sun tracking. The solar array panels are pivoted about the axes of the hinges until substantially parallel to the top and bottom of the satellite to form a compact, stackable configuration of the satellite for stowage. Three couplers (54A,54B,54C) positioned along the perimeter wall couple the satellite to similarly configured satellites within the fairing of a launch vehicle. The coupled satellites form a stack having three load-bearing columns consisting of the satellite couplers. In the stacked configuration, the couplers of one satellite are attached to the couplers of adjacent satellites by bolts restrained within non-explosive separation nuts (106). Pre-loaded compression springs (144A,144B) extend between the couplers of adjacent satellites. After the stack of satellites separates from the fairing (52), each satellite is successively deployed from the stack, starting with the top-most satellite. Deployment begins by activating the non-explosive separation nuts (106) in the couplers of the top-most satellite. Thereafter, the pre-loaded compression springs (144A,144B) extending between the coupling devices of the top-most satellite and the subjacent satellite (or, for the bottom-most satellite, the subjacent booster stage) accelerate the top-most satellite away from the stack and booster stage.

    摘要翻译： 卫星（10）具有两个太阳能电池阵列面板（40,42），其能够在闭合构造和开放构造之间移动。 太阳能电池阵列面板可枢转地安装在沿卫星的顶部和底部连接的铰链（44,46）上，并且在打开配置下从卫星的顶部和底部向外延伸。 周边侧壁（14）的高度被选择为使得卫星具有大致扁平的构造。 每个太阳能电池阵列面板具有基本上等于卫星截面面积的表面积。 铰链（44,46）安装在从太阳能电池阵列驱动电动机（58）延伸的枢轴（48,50）上，该驱动电动机使太阳能电池板围绕由枢轴限定的轴线旋转，以提供一个轴线的太阳跟踪。 太阳能电池阵列面板围绕铰链的轴线枢转，直到基本平行于卫星的顶部和底部，以形成用于装载的卫星的紧凑的可堆叠配置。 沿着周边壁定位的三个耦合器（54A，54B，54C）将卫星耦合到运载火箭的整流罩内的类似配置的卫星。 耦合的卫星形成一个堆叠，其具有三个由卫星耦合器组成的承载柱。 在堆叠配置中，一颗卫星的耦合器通过限制在非爆炸性分离螺母（106）内的螺栓附接到相邻卫星的耦合器。 预加载的压缩弹簧（144A，144B）在相邻卫星的耦合器之间延伸。 在一堆卫星与整流罩（52）分离之后，每个卫星从最上面的卫星开始依次从堆叠部署。 通过激活最顶端卫星耦合器中的非爆炸性分离螺母（106）开始部署。 此后，在最上面的卫星和下面的卫星（或者对于最下面的卫星，下面的升压器级）的耦合装置之间延伸的预加载的压缩弹簧（144A，144B）加速离开最上面的卫星 从堆叠和助推器阶段。

    Satellite having a stackable configuration
    5.
    发明公开
    Satellite having a stackable configuration 失效
    卫星与可堆叠配置。

    公开(公告)号：EP0669251A3

    公开(公告)日：1995-12-27

    申请号：EP94120968.6

    申请日：1994-12-30

    申请人： ORBITAL SCIENCES CORPORATION

    发明人： Steffy, David Alan ,  Robinson, Anthony D.

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

    CPC分类号： B64G1/641 ,  B64G1/002 ,  B64G1/1007 ,  B64G1/1085 ,  B64G1/222 ,  B64G1/44 ,  B64G1/645 ,  B64G2001/643 ,  Y10S136/292

    摘要： A satellite (10) has two solar array panels (40,42) which are moveable between a closed configuration and an open configuration. The solar array panels are pivotably mounted on hinges (44,46) attached along the top and bottom of the satellite and extend outwardly from the top and bottom of the satellite in the open configuration. The height of the perimeter sidewall (14) is selected such that the satellite has a generally oblate configuration. Each solar array panel has a surface area substantially equal to that of the satellite cross-sectional area. The hinges (44,46) are mounted on pintles (48,50) extending from a solar array drive motor (58) which rotates the solar panel about the axis defined by the pintles to provide one axis sun tracking. The solar array panels are pivoted about the axes of the hinges until substantially parallel to the top and bottom of the satellite to form a compact, stackable configuration of the satellite for stowage. Three couplers (54A,54B,54C) positioned along the perimeter wall couple the satellite to similarly configured satellites within the fairing of a launch vehicle. The coupled satellites form a stack having three load-bearing columns consisting of the satellite couplers. In the stacked configuration, the couplers of one satellite are attached to the couplers of adjacent satellites by bolts restrained within non-explosive separation nuts (106). Pre-loaded compression springs (144A,144B) extend between the couplers of adjacent satellites. After the stack of satellites separates from the fairing (52), each satellite is successively deployed from the stack, starting with the top-most satellite. Deployment begins by activating the non-explosive separation nuts (106) in the couplers of the top-most satellite. Thereafter, the pre-loaded compression springs (144A,144B) extending between the coupling devices of the top-most satellite and the subjacent satellite (or, for the bottom-most satellite, the subjacent booster stage) accelerate the top-most satellite away from the stack and booster stage.

    Self-deploying helical structure
    7.
    发明公开
    Self-deploying helical structure 失效
    自我部署的螺旋结构

    公开(公告)号：EP0666612A2

    公开(公告)日：1995-08-09

    申请号：EP94120944.7

    申请日：1994-12-30

    申请人： ORBITAL SCIENCES CORPORATION

    发明人： Robinson, Anthony D.

    IPC分类号： H01Q11/08 ,  H01Q1/28 ,  B64G1/22

    CPC分类号： B64G1/66 ,  B64G1/22 ,  B64G9/00 ,  H01Q1/288 ,  H01Q11/086 ,  Y10T16/5253

    摘要： A helical antenna structure is deformable and capable of being stowed in a small volume. At deployment, the helical antenna structure uses the stored strain energy in its resilient helices to revert to its original shape without the use of any outside force. Multiple antenna structures can be linked using a plurality of resilient lenticular shaped hinges.

    摘要翻译： 螺旋天线结构是可变形的并且能够存放在小体积中。 在部署时，螺旋天线结构利用其弹性螺旋中存储的应变能恢复到其原始形状，而无需使用任何外力。 多个天线结构可以使用多个弹性透镜状铰链连接。