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公开(公告)号：WO2017127747A1
公开(公告)日：2017-07-27
申请号：PCT/US2017/014433
申请日：2017-01-20
发明人： CHUNG, Kirby
CPC分类号： H04W72/0453 , H04B7/18504 , H04B7/18508 , H04B7/18513 , H04B7/18521 , H04B7/2041 , H04W4/021 , H04W72/0413 , H04W72/042
摘要： A wireless communication system includes frequency reuse between terminals in common coverage regions using a multiple satellite architecture with spatial diversity. Different terminals may be associated with different ones of the satellites such that a common frequency can be reused by the different terminals. A gateway may communicate with a first satellite using a feeder beam having an overlapping geographic coverage region with a user beam used for communication between a set of user terminals and a second satellite. Spatial diversity is provided between the satellites, and the feeder beam and the user beam operate at common frequencies within the overlapping coverage region. In this manner, the bandwidth of both satellites at the common coverage region is used to increase the available capacity.
摘要翻译： 无线通信系统包括使用具有空间分集的多卫星架构的公共覆盖区域中的终端之间的频率再用。 不同的终端可以与不同的卫星相关联，使得不同的终端可以重复使用公共频率。 网关可以使用具有重叠地理覆盖区域的馈线波束与第一卫星进行通信，其中用户波束用于一组用户终端和第二卫星之间的通信。 在卫星之间提供空间分集，并且馈送波束和用户波束以重叠覆盖区域内的公共频率操作。 以这种方式，两个卫星在共同覆盖区域的带宽被用于增加可用容量。
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公开(公告)号：WO2017053387A1
公开(公告)日：2017-03-30
申请号：PCT/US2016/052821
申请日：2016-09-21
发明人： WANG, Leah
CPC分类号： H04L5/0048 , H04B7/18506 , H04B7/18517 , H04B7/2041 , H04B17/12 , H04B17/18 , H04W72/0406 , H04W72/046
摘要： This disclosure provides systems, methods and apparatus for determining beamforming coefficients. In one aspect, a subsystem of a satellite can receive livetraffic signals and tap the signals to provide reference signals. The reference signals can be provided on a calibration path including passive components. The signals can be compared with the reference signals to determine differences between the phases and amplitudes and used to determine beamforming coefficients.
摘要翻译： 本公开提供了用于确定波束成形系数的系统，方法和装置。 在一个方面，卫星的子系统可以接收信号并触发信号以提供参考信号。 可以在包括无源部件的校准路径上提供参考信号。 信号可以与参考信号进行比较，以确定相位和幅度之间的差异，并用于确定波束成形系数。
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公开(公告)号：WO2016209525A3
公开(公告)日：2016-12-29
申请号：PCT/US2016/034274
申请日：2016-05-26
摘要： A power combining arrangement includes an input divider waveguide and an output combiner waveguide, and a first and second amplifier. The power combining arrangement is configured to amplify RF energy having a characteristic wavelength λ. The first amplifier has a first input electrically coupled with a first output port of the divider waveguide. The second amplifier has a second input electrically coupled with a second output port of the divider waveguide. The first and second output ports are separated by a first distance corresponding to a phase delay 01; the first distance being selected substantially independently of the characteristic wavelength. The first amplifier has a first output electrically coupled with a first input port of the combiner waveguide and the second amplifier has a second output electrically coupled with a second input port of the combiner waveguide. The first and second input ports are separated by the first distance.
摘要翻译： 功率组合装置包括输入分配器波导和输出组合器波导，以及第一和第二放大器。 功率组合装置被配置为放大具有特征波长λ的RF能量。 第一放大器具有与分频器波导的第一输出端口电耦合的第一输入端。 第二放大器具有与分频器波导的第二输出端口电耦合的第二输入端。 第一和第二输出端口以对应于相位延迟01的第一距离隔开; 第一距离基本上独立于特征波长而被选择。 第一放大器具有与组合器波导的第一输入端口电耦合的第一输出，并且第二放大器具有与组合器波导的第二输入端口电耦合的第二输出。 第一和第二输入端口被第一距离隔开。
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公开(公告)号：WO2016144884A1
公开(公告)日：2016-09-15
申请号：PCT/US2016/021213
申请日：2016-03-07
CPC分类号： B64G1/222 , B64G1/641 , B64G1/66 , B64G4/00 , B64G2004/005
摘要： A spacecraft including a main body structure 110 and at least a first deployable element 130 is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement 140. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement 160. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.
摘要翻译： 包括主体结构110和至少第一可部署元件130的航天器从发射配置重新配置到轨道配置。 在发射配置中，第一可部署元件通过第一装置140机械地附接到航天器主体结构。在轨道构造中，第一可展开元件通过飞行器主体结构机械地附接到航天器主体结构 第二装置160.重新构造航天器包括从第一装置分离第一可展开元件，使第一展开元件相对于航天器主体结构移动; 以及将所述第一可展开元件附接到所述第二布置。
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公开(公告)号：WO2016094786A1
公开(公告)日：2016-06-16
申请号：PCT/US2015/065223
申请日：2015-12-11
CPC分类号： H04B7/18513 , H03F1/0261 , H03F1/0277 , H03F3/195 , H03F3/211 , H03F3/245 , H03F3/68 , H03F3/72 , H03F2200/429 , H03F2203/7206 , H03F2203/7236 , H04B1/0458 , H04B7/0617 , H04B7/18515 , H04L5/06
摘要： A spacecraft includes a payload subsystem including a plurality of transmit antenna feeds, a digital channelizer, and a power amplification arrangement including a plurality of power amplifiers. The power amplification arrangement has at least one input communicatively coupled with an output of the digital channelizer and at least one output communicatively coupled with at least one of the plurality of transmit antenna feeds. A processor is configured to control the digital channelizer, and to adjust a saturated output power of at least one power amplifier of the plurality of power amplifiers in the power amplification arrangement.
摘要翻译： 航天器包括有多个发射天线馈送的有效载荷子系统，数字信道发生器和包括多个功率放大器的功率放大装置。 功率放大装置具有至少一个与数字信道发射器的输出通信耦合的输入，以及至少一个与多个发射天线馈送中的至少一个通信地耦合的输出。 处理器被配置为控制数字信道化器，并且调整功率放大装置中的多个功率放大器中的至少一个功率放大器的饱和输出功率。
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6.发明申请MULTI-PORT AMPLIFIERS (MPAS) USING OUTPUT FILTERING TO IMPROVE PERFORMANCE OVER LIFE 审中-公开多端口放大器（MPAS）使用输出滤波来提高生命周期的性能
公开(公告)号：WO2017136360A1
公开(公告)日：2017-08-10
申请号：PCT/US2017/015883
申请日：2017-01-31
IPC分类号： H04B7/185
CPC分类号： H04B7/18515
摘要： A payload subsystem of a satellite includes a plurality of transmit antenna feeds, a plurality of frequency filters, and a power amplification arrangement including a plurality of power amplifiers. The power amplification arrangement has at least one multiport amplifier, the multiport amplifier including a plurality of output ports, each output port coupled with a respective one of the plurality of transmit antenna feeds by way of a respective one of the plurality of frequency filters.
摘要翻译： 卫星的有效载荷子系统包括多个发射天线馈源，多个频率滤波器以及包括多个功率放大器的功率放大装置。 该功率放大装置具有至少一个多端口放大器，多端口放大器包括多个输出端口，每个输出端口通过多个频率滤波器中的相应一个与多个发射天线馈源中的相应一个耦合。 / p>
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7.发明申请SPACECRAFT WITH RIGID ANTENNA REFLECTOR DEPLOYED VIA LINEAR EXTENSION BOOM 审中-公开采用线性扩展臂部署的刚性天线反射器的SPACECRAFT
公开(公告)号：WO2017123349A2
公开(公告)日：2017-07-20
申请号：PCT/US2016/065444
申请日：2016-12-07
发明人： HART III, William G.
摘要： A spacecraft with a linear extension boom, an antenna feed, and a rigid antenna reflector is provided. The rigid antenna reflector may be connected with one end of the linear extension boom, and the other end of the linear extension boom may be connected with the spacecraft main body. In a launch configuration of the spacecraft, the linear extension boom may be retracted into a stowed configuration, and in an on-orbit configuration of the spacecraft, the linear extension boom may be extended into a deployed configuration, thereby moving the rigid antenna reflector away from the yaw axis of the spacecraft and positioning the rigid antenna reflector such that the focal point of the rigid antenna reflector may be oriented to align on, and be collocated with, the antenna feed. The rigid antenna reflector may be connected with the linear extension boom by a positioning mechanism that provides for adjustment in the angular orientation of the rigid antenna reflector relative to the linear extension boom.
摘要翻译：
提供具有线性延伸臂，天线馈源和刚性天线反射器的航天器。 刚性天线反射器可以与线性伸缩臂的一端连接，线性伸缩臂的另一端可以与航天器主体连接。 在航天器的发射配置中，线性延伸臂可以缩回到收起构型，并且在航天器的在轨配置中，线性延伸臂可以延伸到展开构型，由此将刚性天线反射器移开 从该航天器的偏航轴线并且定位该刚性天线反射器，使得该刚性天线反射器的焦点可以被定向成与该天线馈源对准并与之并置。 刚性天线反射器可以通过定位机构与线性延伸臂连接，该定位机构提供对刚性天线反射器相对于线性延伸臂的角度定向的调整。
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公开(公告)号：WO2016138426A1
公开(公告)日：2016-09-01
申请号：PCT/US2016/019855
申请日：2016-02-26
摘要： A spacecraft includes a 3-D closed truss structure including at least four coupling nodes (220.1-4) and at least six strut elements (210.1-6), attached together by a plurality of joints (221), each coupling node (220) including at least two legs, each strut element (210) disposed between and attached with a respective pair of the plurality of coupling nodes (220). Each coupling node (220) is attached, at respective ones of the plurality of joints (221), with at least two strut elements (210). Each strut element (210) is attached at a first end with a first leg of a first coupling node (220) and is attached at a second end with a second leg of a second coupling node (220), the first leg being substantially longer than the second leg.
摘要翻译： 航天器包括三维闭合桁架结构，其包括至少四个耦合节点（220.1-4）和至少六个支撑元件（210.1-6），其由多个接头（221）连接在一起，每个耦合节点（220） 包括至少两个腿，每个支撑元件（210）设置在相应的一对所述多个耦合节点（220）之间并且附接到所述多个耦合节点（220）中。 每个耦合节点（220）在多个关节（221）中的相应的一个处连接有至少两个支柱元件（210）。 每个支柱元件（210）在第一端处与第一联接节点（220）的第一腿连接，并且在第二端处与第二联接节点（220）的第二腿连接，第一腿部基本上更长 比第二条腿。
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公开(公告)号：WO2017123310A3
公开(公告)日：2017-07-20
申请号：PCT/US2016/059766
申请日：2016-10-31
发明人： CHU, Peter Y.
IPC分类号： H04B7/185
摘要： A spacecraft includes a payload subsystem including a digital channelizer. The digital channelizer provides at least a portion of spacecraft command or telemetry functionality. The spacecraft may optionally also include a telemetry and command (T&C) subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter. The digital channelizer may be communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.
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10.发明申请
公开(公告)号：WO2017123310A2
公开(公告)日：2017-07-20
申请号：PCT/US2016/059766
申请日：2016-10-31
发明人： CHU, Peter Y.
CPC分类号： H04B7/18506
摘要： A spacecraft includes a payload subsystem including a digital channelizer. The digital channelizer provides at least a portion of spacecraft command or telemetry functionality. The spacecraft may optionally also include a telemetry and command (T&C) subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter. The digital channelizer may be communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.
摘要翻译： 航天器包括包括数字信道器的有效载荷子系统。 数字信道发生器提供航天器命令或遥测功能的至少一部分。 航天器可选地还可以包括遥测和命令（T＆amp; C）子系统，T＆amp; C子系统包括命令接收器，命令解码器，遥测编码器和遥测发射器中的一个或多个。 数字信道器可以与命令接收器，命令解码器，遥测发射器和遥测编码器中的至少一个通信地耦合。
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