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1.发明授权Method and apparatus for zooming and reconfiguring circular beams for satellite communications 失效用于缩放和重新配置用于卫星通信的圆形波束的方法和装置公开(公告)号：US06577282B1
公开(公告)日：2003-06-10
申请号：US09619042
申请日：2000-07-19
IPC分类号： H01Q1300
摘要： A method and system for reconfiguring an antenna system are disclosed. The system comprises a feed horn, a subreflector, and a main reflector. The feed horn is pointed at an axis removed from the bisector axis of the subreflector. The distance between the feed horn and the subreflector can be changed to defocus the feed horn with respect to the subreflector, wherein a size of the outgoing beam emanating from the main reflector changes when the distance between the feed horn and the subreflector is changed. The method comprises pointing an axis of a feed horn at a subreflector, wherein the axis of the feed horn is aligned differently from the bisector axis of the subreflector, and changing the distance between the feed horn and the subreflector to defocus the feed horn with respect to the subreflector, wherein a size of an outgoing beam emanating from a main reflector changes when the distance between the feed horn and the subreflector is changed.
摘要翻译： 公开了一种用于重新配置天线系统的方法和系统。 该系统包括馈电喇叭，副反射器和主反射器。 馈电喇叭指向从子反射器的平分线轴线移除的轴线。 可以改变馈电喇叭和副反射器之间的距离，使馈电喇叭相对于副反射器散焦，其中当主反射器发射的输出光束的尺寸在馈电喇叭和副反射器之间的距离改变时改变。 该方法包括将馈电喇叭的轴线指向副反射器，其中馈电喇叭的轴线与子反射器的等分线轴线不对准地对准，并且改变馈电喇叭和副反射器之间的距离以使馈电喇叭相对于 到子反射器，其中当主反射器发射的输出光束的尺寸在馈电喇叭和副反射器之间的距离改变时改变。
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2.发明授权Simplified spacecraft antenna reflector for stowage in confined envelopes 失效简化的航天器天线反射器，用于存放在封闭的信封中
公开(公告)号：US5574472A
公开(公告)日：1996-11-12
申请号：US491331
申请日：1995-06-30
申请人： Stephen A. Robinson
发明人： Stephen A. Robinson
CPC分类号： H01Q15/161 , B64G1/22 , Y10S343/02 , Y10T29/49016
摘要： A method for stowing a unitary flexible antenna reflector 10 in a confining envelope and deploying the reflector from the envelope. In a most general sense, the invention includes the steps of: a) applying a deforming force to diametrically opposed positions 16 and 18 near an edge of the reflector 10 to place the reflector in a deformed state; b) maintaining the reflector 10 in the deformed state until deployment; and c) releasing the reflector 10 from the deformed state. In a specific embodiment, the step of maintaining the reflector 10 in a deformed state includes the step of attaching a restraining element between the diametrically opposed positions on the edge of the reflector which is released on deployment.
摘要翻译： 将一个单一的柔性天线反射器10收纳在限制的信封中并从信封部署反射器的方法。 在最普遍的意义上，本发明包括以下步骤：a）在反射器10的边缘附近对径向相对的位置16和18施加变形力，以将反射器置于变形状态; b）将反射器10保持在变形状态直到展开; 以及c）将反射器10从变形状态释放。 在具体实施例中，将反射器10维持在变形状态的步骤包括将约束元件附接在在展开时释放的反射器的边缘上的直径相对的位置之间的步骤。
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公开(公告)号：US06323817B1
公开(公告)日：2001-11-27
申请号：US09488205
申请日：2000-01-19
IPC分类号： H01Q1300
CPC分类号： H01Q1/288 , H01Q21/28 , H01Q25/007
摘要： A method and apparatus for producing contiguous spot beam communications coverage on the Earth's surface are disclosed. The apparatus comprises an antenna system including two wide scan antennas and two narrow scan antennas. The two wide scan antennas are disposed substantially opposite each other, and the two narrow scan antennas are disposed substantially opposite each other and substantially normal to the wide scan antennas. The first wide scan antenna, second wide scan antenna, and first narrow scan antenna produce a first beam pattern on a planetary surface and the first wide scan antenna, second wide scan antenna, and second narrow scan antenna produce a second beam pattern on the planetary surface.
摘要翻译： 公开了一种用于在地球表面上产生连续点波束通信覆盖的方法和装置。 该装置包括一个包括两个宽扫描天线和两个窄扫描天线的天线系统。 两个宽扫描天线基本上彼此相对设置，并且两个窄扫描天线基本上彼此相对设置并且基本上垂直于宽扫描天线。 第一宽扫描天线，第二宽扫描天线和第一窄扫描天线在行星表面上产生第一波束图案，并且第一宽扫描天线，第二宽扫描天线和第二窄扫描天线在行星上产生第二波束图案 表面。
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4.发明授权公开(公告)号：US06208317B1
公开(公告)日：2001-03-27
申请号：US09504544
申请日：2000-02-15
IPC分类号： H01Q1520
CPC分类号： H01Q15/147 , H01Q15/161
摘要： The present invention is directed to a method of and a device for adjusting the concavity of a springback antenna reflector. The method and device of the present invention can be used to adjust the concavity of the springback reflector prior to stowage within a satellite to correct actual or anticipated variations in the desired shape of reflector that are caused by storage of the reflector, fabrication of the reflector, thermal effects on the reflector, and moisture absorption by the material from which the reflector is fabricated. By adjusting the concavity of the reflector to correct the variations in the shape of the reflector, degradation of the performance of the reflector due to distortions in the shape of the reflector may be greatly reduced.
摘要翻译： 本发明涉及一种用于调节回弹式天线反射器的凹度的方法和装置。 本发明的方法和装置可用于在卫星内存放之前调节回弹反射器的凹度，以校正由反射器的储存引起的反射器所需形状的实际或预期变化，反射器的制造 ，对反射器的热效应以及由反射器制造的材料的吸湿性。 通过调整反射器的凹度来校正反射器的形状的变化，可以大大降低由于反射器的形状的变形引起的反射器性能的劣化。
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5.发明授权Rigid solar panel with discrete lattice and carrier structures bonded together 失效具有离散晶格和载体结构的刚性太阳能电池板结合在一起
公开(公告)号：US5614033A
公开(公告)日：1997-03-25
申请号：US512727
申请日：1995-08-08
IPC分类号： B64G1/50 , H01L31/048 , H01L31/052
CPC分类号： H01L31/048 , B64G1/50 , H01L31/052 , H02S20/00 , H02S20/30 , H02S40/42 , Y02E10/50 , Y10T428/236
摘要： Discrete carrier and lattice structures are bonded together to form a lightweight rigid solar panel. The carrier includes a pair of electrically inert face sheets bonded on opposite sides of a thin thermoconductive honeycomb core. The face sheets provide an electrically inert surface for receiving a solar cell array and the honeycomb core forms a heat sink for conducting heat away from the solar cell array. The lattice includes a pair of patterned face sheets having a high elastic modulus bonded on opposite sides of a lattice base. The patterned face sheets provide axial stiffness and the lattice base separates them to provide bending stiffness. By splitting the solar panel into discrete carrier and lattice components, the present invention reduces the weight of existing solar panels by approximately 40% and increases power efficiency by approximately 10%.
摘要翻译： 离散载体和晶格结构结合在一起形成轻量级的刚性太阳能电池板。 载体包括结合在薄导热蜂窝芯的相对侧上的一对电惰性面片。 面板提供用于接收太阳能电池阵列的电惰性表面，并且蜂窝芯形成用于将热量从太阳能电池阵列传导出来的散热器。 格子包括一对具有高的弹性模量的图案化的面片，其结合在晶格基底的相对两侧。 图案化的面板提供轴向刚度，并且格子基座将它们分开以提供弯曲刚度。 通过将太阳能电池板分成离散的载体和晶格部件，本发明将现有太阳能电池板的重量减少大约40％，并将电力效率提高约10％。
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6.发明授权
公开(公告)号：US4300737A
公开(公告)日：1981-11-17
申请号：US142483
申请日：1980-04-21
CPC分类号： B64G1/645 , B64G1/641 , Y10T403/32565 , Y10T403/581 , Y10T403/598
摘要： A spacecraft specifically adapted for launch from the space shuttle by means of a cradle having locking and ejection mechanisms mounted therein. The cradle fastens into the payload bay of the space shuttle and returns therewith for reuse in subsequent launches. The spacecraft mounts at three points to the cradle, and the cradle mounts at three points to the shuttle such that a plane through the attachment points passes through the roll axis of the spacecraft at approximately the center of mass thereof. The cradle utilizes the truss structure of the spacecraft to produce the required stiffness by providing a structural tie between the two ends and the bottom of the cradle. At launch, the spacecraft is ejected with both linear and angular momentum, the spin providing gyroscopic stability. The locking mechanisms in the cradle can be remotely controlled to relock the spacecraft to the cradle in the event of an unsuccessful deployment attempt. The spacecraft includes a safety circuit employing acceleration sensing switches which sense spin-up of the spacecraft and prevent premature ignition of the perigee boost motor. The spacecraft has imbedded within its envelope a solid-propellant perigee boost motor surrounded by a liquid-propellant apogee motor. By employing apogee and perigee propulsion stages internal to the spacecraft, the storage length in the space shuttle is minimized, and the geometry and mass characteristics of the spacecraft make for a stable spinning vehicle during both the perigee and apogee boost phases.
摘要翻译： 专用于通过其中安装有锁定和弹出机构的支架从航天飞机发射的航天器。 托架紧固到航天飞机的有效载荷舱中，并随之返回，以便在随后的发射中重新使用。 航天器在三点安装在支架上，托架在三点安装在梭子上，使得穿过连接点的平面大致在其中心附近穿过航天器的滚轴。 摇篮利用航天器的桁架结构，通过在支架的两端和底部之间提供结构连接来产生所需的刚度。 在发射时，航天器以线性和角动量喷射，旋转提供陀螺稳定性。 在不成功的部署尝试的情况下，托架中的锁定机构可以被远程控制以将航天器重新锁定到支架上。 航天器包括一个采用加速度传感开关的安全电路，该开关感测到航天器的旋转并防止近地点升压马达的过早点火。 航天器在其信封内嵌入了由液体推进剂远地度电机包围的固体推进剂近地点升压电机。 通过在航天器内部采用远地点和近地点推进阶段，航天飞机的存储长度最小化，并且在近地点和远地点升压阶段期间，航天器的几何形状和质量特性为稳定的纺纱车辆。
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