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公开(公告)号：EP3418204A1
公开(公告)日：2018-12-26
申请号：EP18178440.6
申请日：2018-06-19
发明人： WU, Gordon , ALLEY, Philip , MARLOW, David
摘要： A spacecraft (100) includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls (116,117), disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors (130). At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array.(160). The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector (130) is disposed, undeployed, forward of the respective feed array (160), proximate to and outboard of one of the plurality of sidewalls (116, 117). In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.
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公开(公告)号：EP3340490A1
公开(公告)日：2018-06-27
申请号：EP17202873.0
申请日：2017-11-21
发明人： FANG, Jun
CPC分类号： H04B7/18521 , H04B7/18584 , H04B7/195
摘要： A constellation of satellites (10, 12, 14, 16; S; 300) form a communication system that includes communication between satellites (10, 12, 14, 16; S; 300) and ground terminals (ST, GW) as well as communication between satellites (10, 12, 14, 16; S; 300). The inter-satellite communication is implemented via wireless network comprising a first set of rings (202, 204, 206, 208, 210, 212, 214) in a first orientation and a second set of rings (230, 232, 234, 236, 238) in a second orientation. Each ring of the first set of rings (202, 204, 206, 208, 210, 212, 214) and the second set of rings (230, 232, 234, 236, 238) comprises two ringlets (202a, 202b) transmitting in opposite directions. Each satellite of the plurality of satellites (10, 12, 14, 16; S; 300) is configured to communicate in a ring of the first set of rings (202, 204, 206, 208, 210, 212, 214) and communicate in a ring of the second set of rings (230, 232, 234, 236, 238).
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13.发明公开
公开(公告)号：EP3293894A1
公开(公告)日：2018-03-14
申请号：EP17189303.5
申请日：2017-09-05
发明人： Turgeon, Ghislain , Gallagher, Vijaya , Wang, Leah
IPC分类号： H04B10/11 , H04B10/112 , H04B10/118
摘要： Described herein are ground based subsystems (200), and related methods, for use in transmitting an optical feeder uplink beam (102u) to a satellite (100) that includes a multiple element antenna feed array and that is configured to accept the optical feeder uplink beam (102u) and in dependence thereon use the multiple element antenna feed array to produce and transmit a plurality of radio frequency (RF) service downlink beams (106d, 110d, 114d) to service terminals (STs). Certain embodiments are related to a ground based beamformer (GBBF) (230) for inclusion in a ground based subsystem (200), and methods for use therewith. Beneficially, embodiments described herein allow for flexible antenna beam forming for large signal bandwidth without the limitation associated with the available gateway uplink and downlink spectrum at RF frequencies. Also described herein are space based subsystems for use with such ground based subsystems (200).
摘要翻译： 本文描述了用于将光馈送器上行链路波束（102u）发送到卫星（100）的基于地面的子系统（200）和相关方法，所述卫星（100）包括多元件天线馈送阵列并且被配置为接受光馈送器上行链路 （102u）并且依赖于其使用该多元件天线馈送阵列来产生多个射频（RF）业务下行链路波束（106d，110d，114d）并将其发送到服务终端（ST）。 某些实施例涉及用于包含在基于地面的子系统（200）中的基于地面的波束形成器（GBBF）（230）以及与其一起使用的方法。 有利的是，本文描述的实施例允许针对大信号带宽形成灵活的天线波束，而没有与RF频率处的可用网关上行链路和下行链路频谱相关联的限制。 本文还描述了用于与这种基于地面的子系统（200）一起使用的基于空间的子系统。
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公开(公告)号：EP2795723B1
公开(公告)日：2018-02-14
申请号：EP12809003.2
申请日：2012-12-06
发明人： BURR, Douglas G.
CPC分类号： H01Q25/007 , H01Q1/288
摘要： A spacecraft has a high efficiency multi-beam antenna (MBA) system that serves a coverage region on the Earth. The coverage region subtends an angle, when viewed from the spacecraft, of at least ten degrees. The antenna system provides, within the coverage region, at least sixteen spot beams. A signal provided by the MBA system to each spot beam has a carrier to interference ratio (C/I) of no less than 20 dB. The system enables use of a three color frequency reuse scheme without recourse to signal encoding.
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公开(公告)号：EP3270463A1
公开(公告)日：2018-01-17
申请号：EP17176140.6
申请日：2017-06-14
发明人： BURR, Douglas G. , TABATABAEI, Seyed A. , SOWERS, James J. , GELON, Walter S. , SIMON, Peter S.
CPC分类号： H01Q15/14 , H01Q1/28 , H01Q1/288 , H01Q19/10 , H01Q19/17 , H01Q21/064 , H01Q21/22 , H01Q25/007
摘要： An imaging array fed reflector for a spacecraft is included in a spacecraft payload subsystem. The payload subsystem includes a multi-beam antenna including a reflector, a plurality of amplifiers, and a plurality of radiating feed elements, the feed elements configured as a phased array, illuminating the reflector, operable at a frequency having a characteristic wavelength (λ), and configured to produce, in a far field at the reflector, a set of contiguous abutting beams. The amplifiers are disposed proximate to the plurality of radiating feed elements. Each radiating feed element has a respective coupling with at least one respective amplifier of the plurality of amplifiers. Each radiating feed element, together with the at least one respective amplifier, is disposed in a closely packed triangular lattice such that separation between adjacent radiating feed elements is not greater than 1.5λ.
摘要翻译： 航天器有效载荷子系统中包括航天器的成像阵列馈源反射器。 有效载荷子系统包括多波束天线，该多波束天线包括反射器，多个放大器和多个辐射馈送元件，馈送元件被配置为相控阵列，照射反射器，以具有特征波长（λ）的频率工作， 并且被配置为在反射器的远场中产生一组连续的邻接梁。 放大器靠近多个辐射馈电元件设置。 每个辐射馈送元件分别与多个放大器中的至少一个相应的放大器耦合。 每个辐射馈电元件与至少一个相应的放大器一起被布置成紧密堆积的三角形格子，使得相邻辐射馈送元件之间的间隔不大于1.5λ。
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公开(公告)号：EP3333087B1
公开(公告)日：2020-11-25
申请号：EP17205544.4
申请日：2017-12-05
发明人： CHIANG, Jason J. , WU, Gordon
IPC分类号： B64G1/50
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公开(公告)号：EP3618306A1
公开(公告)日：2020-03-04
申请号：EP19192637.7
申请日：2019-08-20
IPC分类号： H04B7/185 , H04B7/204 , H04B10/118 , H04J14/02
摘要： A system described herein includes a ground based gateway subsystem configured to transmit an RF feeder uplink beam to a satellite, and a space based subsystem of the satellite configured to receive the RF feeder uplink beam (602) and produce in dependence thereon an optical ISL beam that is transmitted to another satellite (618). The ground based gateway subsystem can include a ground based beamformer used to produce the RF feeder uplink beam. The optical ISL beam, produced by the space based subsystem and transmitted to the other satellite, can comprise a wavelength division multiplexed optical signal (614) having RF frequencies within a same specified RF frequency range within which the other satellite is configured to transmit a plurality of RF service downlink beams, thereby eliminating any need for the other satellite to perform any frequency conversions when producing the plurality of RF service downlink beams in dependence on the optical ISL beam.
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公开(公告)号：EP3438003A1
公开(公告)日：2019-02-06
申请号：EP18186803.5
申请日：2018-08-01
摘要： A spacecraft, reconfigurable from a launch configuration to an on-orbit configuration, includes a main body structure (111), a manipulator(140), a first deployable rigid reflector (120) and an attachment arrangement (130), including at least one hold-down assembly (HDA). In the launch configuration, the HDA is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector (120) with the spacecraft main body structure (111) and prevents relative motion between the first reflector (120) and the spacecraft main body (111). Reconfiguring the spacecraft from the launch configuration to the on-orbit configuration includes (i) actuating the HDA from the fully engaged configuration to a partially engaged configuration; (ii) grasping and moving the first reflector, with the manipulator, a distance in the first direction; and (iii) moving the first reflector from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration.
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公开(公告)号：EP3391458A1
公开(公告)日：2018-10-24
申请号：EP16810178.0
申请日：2016-11-21
发明人： SIMON, Peter S. , ALIAMUS, Michael , TAVASSOLI HOZOURI, Behzad , JONES, Robert , GRALL, Michael
CPC分类号： H01Q5/28 , H01P5/024 , H01P5/12 , H01Q1/288 , H01Q3/36 , H01Q5/45 , H01Q19/17 , H01Q21/005 , H01Q21/064 , H01Q25/001
摘要： A spacecraft communications payload includes a beam forming network (BFN), wherein the BFN includes a first feed waveguide and a first set of branch waveguides, each branch waveguide in the first set operating in a frequency band having a characteristic waveguide wavelength λg1. A proximal portion of the first set of branch waveguides is communicatively coupled with the first feed waveguide. A distal portion of the first set of branch waveguides is communicatively coupled by way of an array of slots with a plurality of radiating elements. A separation distance between adjacent slots in the array is approximately equal to λg, and the array of slots is configured as a honeycomb-like triaxial lattice. In some implementations, a compact BFN may be configured to simultaneously operate at two different polarizations (“dual-polarized”) and/or frequency bands (“dual-band”).
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