公开(公告)号：US20130307741A1

公开(公告)日：2013-11-21

申请号：US13474084

申请日：2012-05-17

Applicant: Behzad Tavassoli Hozouri

Inventor： Behzad Tavassoli Hozouri

IPC: H01Q13/00

CPC classification number: H01Q13/06 ,  H01Q13/00

Abstract: A wide beam radio frequency (RF) antenna includes a waveguide and one or more electrically conductive protrusions. The waveguide has at least one electrically conductive interior wall surface, a boresight defined by a longitudinal axis, and an aperture plane, transverse to the longitudinal axis, disposed at a distal end of the waveguide. A first proximal portion of each protrusion is electrically coupled to the electrically conductive interior wall surface, a distal portion of the protrusion being outside the aperture plane.

Abstract translation: 宽波束射频（RF）天线包括波导和一个或多个导电突起。 波导具有至少一个导电内壁表面，由纵向轴线限定的视轴和横向于纵向轴线的孔平面，设置在波导的远端。 每个突起的第一近端部分电耦合到导电内壁表面，突出部的远端部分在孔平面之外。

公开(公告)号：US20130006585A1

公开(公告)日：2013-01-03

申请号：US13170813

申请日：2011-06-28

Applicant: Peter S. Simon

Inventor： Peter S. Simon

IPC: G06F17/50 ,  H01Q19/10

CPC classification number: G06F17/5018 ,  G06K7/00 ,  H01Q13/0208

Abstract: An RF feed element for an antenna system required to comply with a set of specified secondary pattern characteristics is designed by performing a quantitative optimization of the RF feed element directly with respect to the secondary pattern characteristics. The quantitative optimization may include pre-computing a plurality of partial secondary pattern complex field values. Each partial secondary pattern may be associated with an RF feed element modal beamlet. A value of at least one to-be-optimized feature is optimized by iteratively adjusting the value of the to-be-optimized feature(s) within an optimization loop that iteratively computes secondary pattern characteristics and compares them to the specified secondary pattern characteristics. The computed secondary pattern characteristics result from performing a linear superposition on the pre-computed partial secondary pattern complex field values, using complex modal coefficients of the RF feed element, determined taking into account current value(s) of the to-be-optimized feature(s).

Abstract translation: 通过相对于次级图案特性直接执行RF馈送元件的定量优化来设计用于符合一组特定二次图案特性的天线系统的RF馈送元件。 定量优化可以包括预先计算多个部分二级模式复数域值。 每个部分二次图案可以与RF馈送元件模式子束相关联。 通过迭代地调整迭代地计算次级图案特性并将它们与指定的二次图案特性进行比较的优化循环内的待优化特征的值来优化至少一个待优化特征的值。 所计算的次级图案特性是由于使用RF馈送元件的复数模态系数对预先计算的部分二次图案复场值执行线性叠加而产生的，其考虑了待优化特征的当前值 （s）。

公开(公告)号：US20120293294A1

公开(公告)日：2012-11-22

申请号：US13068655

申请日：2011-05-17

Applicant: Varouj Baghdasarian

Inventor： Varouj Baghdasarian

IPC: H01H85/02

CPC classification number: B64G1/222 ,  B64G1/44 ,  B64G1/66 ,  H01H85/0047 ,  H01H85/0052 ,  H01H85/046

Abstract: Redundant fuse wire apparatus and redundant release devices, such as those used to release deployable appendages, such as solar array and reflectors disposed on satellites, and the like. An exemplary redundant release device comprises a restraint release mechanism having one or more restraint release arms, a redundant release device comprising a segmented spool having a plurality of segments that are constrained from separating by spring restraint tape releasably secured to the restraint release arms, a redundant fuse wire assembly comprising primary and redundant positive contacts, a common negative contact, primary and redundant fuse wires respectively connected between the primary positive and common negative contacts and the redundant positive and common negative contacts that respectively wrap around the opposed positive contact and the restraint release arms, and an electrical power source for heating and severing the fuse wires.

Abstract translation: 冗余熔丝装置和诸如用于释放可部署附件的冗余保险丝装置和冗余释放装置，例如设置在卫星上的太阳能阵列和反射器等。 示例性的冗余释放装置包括具有一个或多个约束释放臂的约束释放机构，包括具有多个段的分段卷轴的冗余释放装置，所述多个段通过可释放地固定到限制释放臂的弹簧约束带限制而分离， 保险丝组件包括初级和冗余正极触点，共同的负极触点，分别连接在初级正极和公共负极触点之间的主要和冗余熔丝，以及分别围绕相对的正触点和约束释放的冗余正和负的触点 臂和用于加热和切断熔丝的电源。

公开(公告)号：US20120228436A1

公开(公告)日：2012-09-13

申请号：US13044278

申请日：2011-03-09

Applicant: Colin M. FRANCIS

Inventor： Colin M. FRANCIS

IPC: B64G1/66 ,  G05G1/00 ,  B64G1/22

CPC classification number: H01Q15/161 ,  B64G1/222 ,  B64G1/66 ,  H01Q1/288 ,  Y10T74/20

Abstract: A spacecraft payload element is rotated by a mechanism about virtual pivot point (VPP) substantially distant from the mechanism. The mechanism couples the payload element to a spacecraft main body structure, and has a four-bar linkage configured to rotate the payload element about a virtual pivot point (VPP). The VPP may be proximate to the focus or center of gravity (cg) of the payload element. Rotation of the payload element about the VPP may be controlled by linear or rotary actuators which drive the four-bar linkage. The four-bar linkage may be configured to provide a mechanical advantage to the actuator.

Abstract translation: 航天器有效载荷元件通过与该机构基本上远的虚拟枢轴点（VPP）的机构旋转。 该机构将有效载荷元件耦合到航天器主体结构，并且具有配置成围绕虚拟枢轴点（VPP）旋转有效载荷元件的四杆连杆。 VPP可以接近有效载荷元件的焦点或重心（cg）。 关于VPP的有效载荷元件的旋转可以由驱动四杆连杆的线性或旋转致动器来控制。 四杆联动装置可被配置成为致动器提供机械优点。

公开(公告)号：US20120094593A1

公开(公告)日：2012-04-19

申请号：US13093669

申请日：2011-04-25

Applicant: Douglas G. Burr

Inventor： Douglas G. Burr

IPC: H04B7/185

CPC classification number: H04B7/18515 ,  H04B7/2041

Abstract: A broadband satellite having a payload subsystem configured to provide dual frequency conversion and bandwidth aggregation is communicatively coupled (i) to at least one gateway by a feeder link operating at a first frequency band; and (ii) to a plurality of user terminals by user links operating at a second frequency band. The payload subsystem has a first and a second frequency converter a satellite feeder link antenna feed, and a satellite user link antenna feed. The first frequency converter down converts, to a third frequency band, as an aggregated block, signals received at the satellite feeder link antenna feed from the gateway via the feeder link. The third frequency band is substantially lower than both the first and second frequency band. The down converted signals are routed to the second frequency converter for up converting to the second frequency band for transmission over the user link to the user terminals.

Abstract translation: 具有被配置为提供双频率转换和带宽聚合的有效载荷子系统的宽带卫星通过在第一频带上工作的馈线链路与至少一个网关通信耦合（i） 以及（ii）通过在第二频带操作的用户链接到多个用户终端。 有效载荷子系统具有第一和第二频率转换器，卫星馈线链路天线馈送和卫星用户链路天线馈送。 第一个频率转换器向第三个频带转换为一个聚合块，在卫星馈线链路天线接收的信号通过馈线链路从网关馈送。 第三频带基本上低于第一和第二频带。 下变频信号被路由到第二频率转换器，用于上变频到第二频带，以便通过用户链路传送到用户终端。

公开(公告)号：US08135338B1

公开(公告)日：2012-03-13

申请号：US12344064

申请日：2008-12-24

Applicant: Walter Gelon ,  William Nations ,  Douglas Burr

Inventor： Walter Gelon ,  William Nations ,  Douglas Burr

IPC: H04B7/185

CPC classification number: H04B7/18521 ,  H04B7/18582

Abstract: High data rata communications services are provided via a satellite system. Data is received from a user at a data rate greater than 30 Mbps over a communications link between the user and a first satellite, where the first satellite is one of a number of satellites within the satellite system; the data is forwarded over a crosslink from the first satellite to at least a second satellite within the satellite system; and the data is forwarded from the second satellite by a feeder link to a gateway located on the earth, said gateway being communicatively coupled to a terrestrial data network. The data is received from the user terminal by an antenna on the first satellite adapted for operation at a frequency associated with the feeder link.

Abstract translation: 通过卫星系统提供高数据比特率通信服务。 在用户和第一卫星之间的通信链路上以大于30Mbps的数据速率从用户接收数据，其中第一卫星是卫星系统内的若干卫星之一; 数据通过交联从第一卫星转发到卫星系统内的至少第二卫星; 并且数据通过馈线链路从第二卫星转发到位于地球上的网关，所述网关通信地耦合到地面数据网络。 数据通过第一卫星上的天线从用户终端接收，适于以与馈线链路相关联的频率进行操作。

公开(公告)号：US07787819B2

公开(公告)日：2010-08-31

申请号：US11467490

申请日：2006-08-25

Applicant: John L. Walker ,  Rolando Menendez ,  Douglas Burr ,  Gilles Dubellay

Inventor： John L. Walker ,  Rolando Menendez ,  Douglas Burr ,  Gilles Dubellay

IPC: H04B15/00

CPC classification number: H04B7/2041

Abstract: Methods, systems and apparatus for ground-based beamforming of a satellite communications payload (200) within a satellite communications network (100). An embodiment of the invention comprises a satellite (11) communicatively coupled to at least one gateway (12) via a feeder link (13) and further coupled to a plurality of user terminals (16), each communicatively coupled with the satellite by a user link (17). A ground based beam forming system (400) measures and corrects amplitude and phase errors of a plurality of return path signals (452) traveling from the user terminals (16) via the satellite (11) to the at least one gateway (12), and measures and corrects amplitude and phase errors of a plurality of forward path signals (457) traveling from the at least one gateway (12) via the satellite (11) to the user terminals (16).

Abstract translation: 卫星通信网络（100）内卫星通信有效载荷（200）的基于地面波束成形的方法，系统和装置。 本发明的实施例包括通过馈线链路（13）通信地耦合到至少一个网关（12）并进一步耦合到多个用户终端（16）的卫星（11），每个用户终端（16）由用户与卫星通信地耦合 链接（17）。 基于地面的波束形成系统（400）测量并校正从用户终端（16）经由卫星（11）行进到至少一个网关（12）的多个返回路径信号（452）的振幅和相位误差， 并且测量并校正从至少一个网关（12）经由卫星（11）行进到用户终端（16）的多个前向路径信号（457）的幅度和相位误差。

公开(公告)号：US06898428B2

公开(公告)日：2005-05-24

申请号：US09871075

申请日：2001-05-31

Applicant: Michael Thorburn ,  Craig Ziegler ,  Stephen C. Holme

Inventor： Michael Thorburn ,  Craig Ziegler ,  Stephen C. Holme

IPC: H04B7/204 ,  H04Q7/20

CPC classification number: H04B7/2045

Abstract: A communication system having gateway filter and switching networks in forward and return channels of a frequency reuse communication satellite. The system couples subscriber terminals to the Internet or other terrestrial network by way of one or more gateways. The system cross-straps gateway-to-user beam connectivity provided by the communication satellite to allow full coverage of all user beams with a subset of the gateways having reduced frequency reuse. An exemplary system comprises a communication satellite having a return channel and a forward channel. One or more gateways are coupled to the Internet or other terrestrial network and communicate with subscriber terminals by way of the return and forward channels provided by the satellite. The return and forward channels each comprise a filter and switching network that selectively couple signals between the one or more gateways and the subscriber terminals. The filter and switching networks selectively couples signals between selected gateways and selected subscriber terminals using predetermined beams.

Abstract translation: 一种在频率复用通信卫星的前向和后向信道中具有网关过滤器和交换网络的通信系统。 系统通过一个或多个网关将用户终端与互联网或其他地面网络相连接。 系统交叉绑定由通信卫星提供的网关到用户的波束连接，以允许所有用户波束的全覆盖，网子的子集具有减少的频率重用。 示例性系统包括具有返回信道和前向信道的通信卫星。 一个或多个网关被耦合到因特网或其他地面网络，并且通过卫星提供的返回和前向信道与用户终端进行通信。 返回和前向信道各自包括滤波器和交换网络，其选择性地耦合一个或多个网关与用户终端之间的信号。 滤波器和交换网络使用预定的波束选择性地在所选择的网关和选定的用户终端之间耦合信号。

公开(公告)号：US06854510B2

公开(公告)日：2005-02-15

申请号：US09841373

申请日：2001-04-24

Applicant: Lenny Low ,  Susan Sebata

Inventor： Lenny Low ,  Susan Sebata

IPC: B64G1/22 ,  B64G1/50 ,  F28F7/00

CPC classification number: B64G1/222 ,  B64G1/503 ,  B64G1/506

Abstract: A spacecraft, along with a spacecraft radiator system and spacecraft heat dissipation method are disclosed. The spacecraft comprises a body, a plurality of solar arrays, and the spacecraft radiator system. The spacecraft radiator system comprises first and second opposite facing payload radiators, first and second opposite facing deployable radiators, and one or more coupling or loop heat pipes cross coupling opposite facing payload and deployable radiators so that they function in tandem. By cross-coupling the opposite facing payload and deployable radiators, one of the two radiators acting in tandem is always in the shade during solstice seasons. Consequently, the solar load processed by the radiator system is minimized, thereby, increasing the thermal dissipation capability of the radiator system by approximately 15%.

Abstract translation: 公开了一种航天器，以及航天器散热器系统和航天器散热方法。 航天器包括一个主体，多个太阳能阵列，以及该航天器散热器系统。 航天器散热器系统包括第一和第二相对面的有效载荷辐射器，第一和第二相对的可展开散热器，以及一个或多个耦合或回路热管，其横向耦合在相对的有效载荷和可展开的散热器上，使得它们串联起作用。 通过交叉耦合相对的有效载荷和可部署的散热器，串联作用的两个散热器中的一个在至少季节期间总是处于阴影中。 因此，由散热器系统处理的太阳能负载最小化，从而将散热器系统的散热能力提高约15％。

公开(公告)号：US6141606A

公开(公告)日：2000-10-31

申请号：US123767

申请日：1998-07-28

Applicant: Keith J. Reckdahl

Inventor： Keith J. Reckdahl

IPC: B64G1/28 ,  B64G1/36 ,  G05D1/08 ,  G05D1/00

CPC classification number: B64G1/285 ,  B64G1/283 ,  B64G1/36 ,  G05D1/0883 ,  B64G2001/245

Abstract: A spacecraft attitude control system uses at least four reaction wheels In order to minimize reaction wheel speed and therefore power, a wheel speed control means system is provided. The wheel speed control means monitors the wheel speeds and controls wheel speed nullspace components to keep the wheel speeds as small as possible.

Abstract translation: 航天器姿态控制系统使用至少四个反作用轮为了最小化反作用轮速度和功率，提供了一种车轮速度控制装置系统。 车轮速度控制装置监视车轮速度并控制车轮速度零空间部件，以保持车轮速度尽可能小。