CN1055184C - 移动通信卫星有效负载 - Google Patents

移动通信卫星有效负载 Download PDF

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CN1055184C
CN1055184C CN93119051A CN93119051A CN1055184C CN 1055184 C CN1055184 C CN 1055184C CN 93119051 A CN93119051 A CN 93119051A CN 93119051 A CN93119051 A CN 93119051A CN 1055184 C CN1055184 C CN 1055184C
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coupled
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satellite payload
frequency band
input
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CN1124892A (zh
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E·赫施菲尔德
Ｃ·－Ｈ·Ａ·赵
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Maxar Space LLC
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
    • H01Q21/061—Two dimensional planar arrays
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
    • H01Q21/061—Two dimensional planar arrays
    • H01Q21/064—Two dimensional planar arrays using horn or slot aerials
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
    • H01Q21/061—Two dimensional planar arrays
    • H01Q21/065—Patch antenna array
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
    • H04B7/18569—Arrangements for system physical machines management, i.e. for construction operations control, administration, maintenance
    • H04B7/18571—Arrangements for system physical machines management, i.e. for construction operations control, administration, maintenance for satellites; for fixed or mobile stations
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/204—Multiple access
    • H04B7/2041—Spot beam multiple access
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B64G1/1007—Communications satellites
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B64G1/1085—Swarms and constellations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
    • Y02D30/00—Reducing energy consumption in communication networks
    • Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks

Abstract

提供用户装置和可与世界公用电话电报网相连的地面门道局之间有效通信的通信卫星有效负载。该负载对于使用全双工通讯的用户装置在上行和下行两线路上同时维持若干独立天线波束。该负载还维持地面门道局和卫星之间相同数量的全双工通道。该负载由位于近地轨道星座中许多这种卫星中一个卫星运载，以提供世界范围的通信。下行波束成形发生在发射信号的末级放大之前，因而减小了在波束成形设备中的损失。

Description

移动通信卫星有效负载
本发明总地说来涉及通信系统，尤其是涉及由卫星平台运载的通信设备。
当设计用于空间平台的通信设备时主要考虑设备的重量、复杂性和电力消耗。进一步考虑涉及最大限度地减小从(上行线路)接收和发射到(下行线路)地面站的信号损失。例如对于使用相控天线阵的常规发射机，在连接在功率放大器的输出和相控天线阵的输入之间的波束形成系统内就存在明显的信号损失。
因此本发明的一个目的是相对于现有的技术系统提供减小复杂性和提高功耗实效的卫星通信有效负载。
本发明的另一个目的是提供束形成发生在发射信号的最后放大之前的卫星通信有效负载，从而减少在束成形设备中的损耗。
本发明又一个目的是提供使用多元件相控接收天线阵和多元件相控发射天线阵的卫星通讯有效负载，其中每个相控阵的每个元件用于多个接收或发射束中单独的一个。
本发明的另一目的是提供使用多元件相控接收天线阵和多元件相控发射天线阵的卫星通信有效负载，其中给于特定下行束的有效功率依据要求随上行功率而变化、而无需命令或控制逻辑。
通过使用依据本发明教导而构造和运行的通讯卫星有效负载，上述和其他问题得到克服，本发明的目的得以实现。
本发明的教导针对在(例如)多个手持蜂窝式电话或其他无线电话和地面门道局之间提供有效通讯的通讯卫星有效负载，门道局可以连接至世界范围的公用电话和电报(PTTS)网络。本发明的卫星有效负载在使用全双工通信的蜂窝式电话的上行和下行线路上同时支持例如12或16束的若干个独立天线射束。该卫星有效负载还支持在地面门道局和卫星之间相同数量的全双工信道。在本发明提出的一个最佳实施例中打算通信卫星有效负载由在近地(low earth)轨道(LEO)星座中若干这种卫星中一个卫星所运载，以提供全世界的通信。
依照本发明提供用于通信系统的卫星有效负载。该有效负载包括具有接收第一频带内RF(射频)信号的若干个(n)接收元件的相控接收天线阵。多个(m)上行波束成形器的每一个有一个与多个接收元件的每一个相连的输入端，以便从由相控接收天线阵所接收的RF信号中形成m个上行波束。
该有效负载包括地面站通信电路，该电路的输入端与上行波束形成器的输出端相连，用于将m个上行波束转换为第二频带内的RF信号。地面站通信电路还包括用于向地面站发送RF信号和从地面站接收RF信号的电路和天线。所发送和接收的RF信号在第二频带范围内。
该有效负载还包括下行波束形成器，该形成器的输入端与地面站通信电路的输出端相连(从而将从地面站接收的RF信号形成m个下行波束。所形成的m个下行波束在第三频带范围内。相控发射天线阵有若干个发射元件用以将m个下行波束作为第三频带内RF信号发送。每个发射元件有功率放大器与之相连。每个功率放大器有输入端与下行波束形成器的输出端相连、而其输出端与其中一个发射元件相连。这样，下行波束的形成发生在最后放大之前。
在目前的该最佳实施例中，第一频带是在L波段内，第二频带在C波段内，而第三频带则在S-波段内。
依照本发明的一个实施例，每个接收元件有若干个接收放大器与之相连，而每个接收放大器的输入耦合至其中之一个接收元件的自由空间。同样，每个功率放大器的输出耦合至发射相控天线阵的发射元件之一的自由空间内。
而且依照本发明，m个上行波束中每一束具有对应的下行束，此下行束照射源自上行束的相同区域。下行束中对应的一束的功率大小随该上行束的功率大小而变。
在本发明的另一实施例中，接收机和发射机相控天线阵中每个均是使用多层电路技术制成的，而接收和发射元件中每个均是在多层印刷电路板的表面上提供有导电接线板。双腔滤波器与每个接线板电气耦合，该滤波器在多层印刷电路板的下面几层内构成。
结合附图详细说明本发明，将能更清楚地看到本发明的上述和其他特点。附图如下：
图1表示运用本发明教导的一种类型的通信系统；
图2a说明本发明的卫星通信有效负载的主要功能部件；
图2b是依照本发明教导而构造和运行的图2a所示移动卫星通信有效负载的方块图；
图3a-3c更详细地示出图2的发射相控阵的其中一个辐射器，更具体地说图3a是其中一个发射相控阵到元件的侧视图，图3b是俯视图，而图3c表示互相间隔90°的四个放大器的使用示意图；
图3d是表示使用两个接收放大器的单个相控接收天线阵元件的俯视图；
图4a和4b更详细地表示出图2的发射相控阵的总体结构；
图5表示12束相控天线阵复盖纵断面；
图6a是表示双通道功率组合器/分配器的典型实施例的顶部立面(top elevational)视图；
图6b是由若干个图6a的功率组合器/分配器构成的波束形成网络的方块图；
图7表示使用用于接收和发射相控天线阵的辐射连接板(radiating patchs)的本发明的实施例；
图8是图7的一部分辐射板的多层电路实施例的部件分解的立面视图，更具体示出辐射板和相连的双腔滤波器；
图9是多层电路实施例的横截面图，表明图8的辐射板和双腔滤波器以及提供与相关支持电路连接的附加层。
图1说明本发明的通信卫星有效负载所打算运用的典型环境。通信系统10从概念上可以又划为1、2、3和4段。本文中1段称为空间段，2段是用户段，3段是地面段，而4段作为电话系统下部结构段。本发明特别针对空间段1，尤其是由近地轨道卫星星座中其中特定的卫星12a所运载的通讯有效负载12。
用户段2包括适于与卫星12a通信的若干类型的用户设备。例如，这种用户设备包括，但不限于无线电话14，移动无线电话15和传呼/通知型装置16的若干种不同类型的用户装置13。用户装置13可从能够以全双工模式运行，并通过L波段RF链路(上行)和S波段RF链路(下行)与卫星有效负载12a通信。上行L波段RF链路运行在1.61GHE至1.6265GHZ的频段内，频带宽度为16.5MHZ，并按照扩展频谱技术用话音信号和/或无线电定位卫星服务(RDSS)信号调制。下行S波段RF链路运行在2.4835GHZ至2.5GHZ的频段内，频带宽度为16.5MHZ。上行和下行RF链路17按照扩展频谱技术用话音信号和/或无线电定位卫星服务(RDSS)信号调制。
地面段3包括通过运行在中心频率为5GHZ的频段内的全双工C波段RF链路19与卫星12a通信的若干个门道局18。门道局18用于将卫星12a的通信有效负载12耦合到电话下部结构段4。电话下部结构段4包含现有的电话系统，还包括蜂窝式门道局20、区域贝尔运行中心(RBOC)22、长途载波机24、国际载波机26、专用网络28和公用电话和电报系统30。通信系统10用于提供在用户段2和电话下部结构段4的电话32之间的通信，还用于使用户段2的用户装置中的特定装置之间能通过门道局18进行通信。
再阅图1，作为地面段3的一部分的是遥测控制系统34，它包括卫星运行控制中心(SOCC)36和网络控制中心(NCC)38。为互连地面段3的门道局18、SOCC36和NCC38而设有通信路经39。通信系统10的这一部分提供卫星控制功能，而且与本发明的通信有效负载12的运行并不直接有关。
图2a和2b是图1的其中一个卫星有效负载12的方块图。卫星有效负载12包含以下主要功能部件。
L波段接收天线40和S波段发射天线42分别将上行和下行链路耦合至用户段2的用户装置。天线40和42的每一个是由例如61个元件(40a、42a)组合的相控阵。这些元件拼合为一般六角形结构，例如，接收天线40的最大宽度约为40英寸，而发射天线42的最大宽度约为25英寸。每个元件40a的直径约为4.4英寸，而每个元件42a的直径约为2.7英寸。每个天线40和42运用例如12或16束的相同数量的波束，并将61个元件的每一个用于该波束中的每一个。
图4说明典型的12束天线复盖构型，其中未图示的下部是已图示的上部的镜象。使用12束提供大约110°的复盖区域(10°仰角)。单个的其中一束可以服务于大约200个用户段2中用户装置，这样使用12束结构服务于大约2400个用户装置，使用16束结构则服务于大约3600个用户装置。为了容纳这个数量的用户装置，有效负载12运用CDMA(码分多址)利用频率再用，以提供每个带宽为1.25MHZ的13个子波段。
直接与接收天线40的61个元件40a相连的是用于接收L波段上行信号的低噪声放大器(LNAs)44。直接与发射天线42的61个元件42a相连的是用于发射S波段下行信号的大功率放大器(HPAs)46。HPAs46能以几个不同功率大小发射。LNAs44和HPAs46设计为运行在输出信号正比于输入信号的线性区。线性运行维护了所发射信号的保真度，也提供了每个天线元件同时运载多个独立束的能力。
当卫星12a从一组用户装置上面经过时，对卫星12a的存取沿与卫星运动相反的方向从束至束地移动。这样，用于从卫星12a的S波段下行的发射功率的需要也必须以对应的方式从束至束地移动。
依照本发明的一个方面，有效负载12供给分配给特定下行束的可使用功率，该特定下行束与使用中的上行束照射相同的地面积，之所以发生这种情况是因为下行链路HPAs46与每个下行线路馈给元件42a相关联，这样每个元件42a分享每束。因此，功率按要求在门道局18的协同下自动分配，而无需指令或逻辑控制。
更详细地说，相控天线阵40和42分别由多束形成网络48和50构成的，它们建立每束相对于卫星12a所指的方向。在图示的实施例中有16个上行线路和下行线路束，也就有16个上行束形成器48和16个下行束形成器50。为了同时产生16个上行束，每个接收天线元件40a的输出在经LNAs44放大后分成送至束形成器48的16个路径，因而建立每个上行线路束的方向和形状。对于下行线路束是相同的，其中16个输入被合并，后经HPAs46放大以供发射。这种分割为多路径的工作是通过上行线路功率分配器52和下行线路功率组合器或加法器54而实现的。
有61个上行线路功率分配器52。每个上行线路功率分配器52有与其中一个LNAs44相连的一个输入端和16个输出端，输出端中各个端与16个束形成器48中的一个相连。同样，有61个下行线路功率组合器54。每个下行功率加法器54有与16个束形成器50的其中一个的输出端相连的16个输入端和与其中一个HPAs46相连的一个输出端。
图6表示典型的双通道功率分配器组合器53。功率组合器/分配器53包括第一地平面53a、第二地平面53b和由插入在第一和第二地平面53a和53b之间的介质材料53c组成的区域。导电电路53d也被包含在介质材料53c之内，并包括绝缘电阻53e。当进行功率分配时，输入信号加在标有A的端口上，而从标为B和C的端口取出信号。当组合功率时，待组合的输入信号加在端口B和C上，而两个信号之和从端口A取出。这些不同元件的尺寸和厚度随关心的频率和材料53c的介电常数而变。16通道或61通道分配器/组合器以类似方式构成，或者可以通过将若干个双通道分配器/合并器53进行级联而实现。
例如，图6b表示由功率组合器/分配器53的总共6级级联在一起构成的束形成网络(48、50)之一。P1、P2、...P61表示不同路径长度，从而在每个天线元件上产生不同的相位。功率组合器/分配器53的未用端口最好用合适负载端接。
正如以上所述，通信系统10使用门道局18来接收由卫星12a收集的信号，并将这些信号传送入相关PTT(公共电话电报)网络。门道局18还接收来自PTT网络的待被发射回去再通过卫星有效负载12送至用户装置的信号。门道局18和卫星12a之间的传输是借助C波段RF链路19。
为了适应这种操作方式，由16束接收的L波段信号是频分多路(FDM)以供在C波段频率上发射。再参看图2b，这是通过若干个(16个)放大混频器56来实现的，该混频器运行于将L波段信号向上变换为C波段信号。每个FDM频道的频率是由本机振荡器60以及放大混频器56和滤波器62建立的。多个(8)信道在加法网络64和66其中特定的一个中被分别组合，并分别供给功率放大器(SSPAs)68和70。功率放大器68和70的输出通过天线分离滤波器72和74加到正交信道，以从天线76发射至门道局18。正交信道由极化器78建立。
圆极化正交信号从门道局18返回通过天线76到达，被极化器78分离。来自门道局18的上行线路和下行线路信号处于不同波段，并由天线分离滤波器72和74分离。上行线路门道信号分别通过低噪声放大器LNAs80和82放大，并供给功率分配器84和86。功率分配器84和86的输出供给16个滤波器88和放大混频器90，该混频器和本机振荡器92一起将C波段门道发送进行下行变换，以确定至束成形网络50的S波段返回信道。放大混频器90的输出滤波器94耦合至束成形网络50。
为驱动束成形网络50所必须的增益由LNAs80和82以及放大混频器90来确立。来自束成形网络50的信号在n路(本例中n＝16)功率加法器54中被集合，并供给发射相控天线阵42的特定元件42a。
如以上所述，本发明的教导提供了一种有效的装置，用于将有效负载功率应用于需要之处，而无需控制系统或不必要时间延迟。即，通过使用线性放大器和使用供16束中每一束的每个相控天线阵用的所有元件，每个L波段上行线路束的信号功率通过接收电路、C波段上行变换、S波段下行变换和通过最后对发射相控天线阵42的放大而保持不变。因此，每个S波段下行束的信号功率是随相应的L波段上行束的信号功率而变。L波段上行束的信号功率是该束所服务的用户装置数目的一个函数。
一般说，束成形网络48和50在束成形过程中综合有幅度和相位两者的变化。然而在本发明中对束成形网络推荐的最佳装置使用只与相位有关的束成形。这使得每个天线元件和有关的放大器得以等幅驱动。这在保持天线元件之间的相位关系中是重要的，因为放大器的相位传输特性可能随驱动电平的变化而变化。通过以相同电平驱动所有放大器，避免了这个潜在问题。
此外，在功耗大的功率放大器46之前的信号路径中运用供发射相控天线阵42之用的束成形网络50，与束成形过程有关的损失要比常规技术有明显减小。
在放大之前束成形要求在所有元件42a处的末级放大器46在幅度和相位传输特性两方面均有高精度(在+/-2°和+/-0.5dB范围内)地相互重复，最好这是通过对HPAs46使用单片微波集成电路(MMICs)而达到的，因为MMICs恰恰可为各放大器提供可重复性能。
现参阅图3a、3b、3c和3d，以说明本发明的另一方面。本发明的这一方面有关LNAs44在接收天线元件40a中的安装方式，另外还有关HPAs46在发射相控阵元件42a中的安装方式。LNAs44的输入和HPAs46的输出直接耦合至自由空间。因此，在居中的电缆、波导或其他微波元件中不会引起损失。
图3a是其中一个发射相控阵元件42a的侧视图，图3b是俯视图，而图3c是表示相互间隔90°的4个HPAs46的使用示意图。单个辐射器元件42a由圆柱形构件42b构成，其尺寸允许电波可沿其垂直轴传播。构件42b构成运行频率下的短圆波导。HPAs46可以位于沿构件42b的周长以90°相位增量的至多4个位置，以激励所要求的圆形极化波。对于发射相控天线阵42，需要2个或4个探针42c和相关联的HPAs46，这取决于功率放大器的尺寸和所需要的功率级。
正如在图3d可看到的，对于接收元件40a的情况来说，设置有90°相位偏移和相隔90°的二个探针40b，以供接收圆形极化信号之用。
相控天线阵40和42的实际结构对有效负载12的有效性来说是一个重要的因素，因为最大限度地减小重量和总直流功耗对成本的影响很大。现在推荐的最佳结构方案示于图4a和4b中。
图4a是向61元件发送阵42内看的俯视图，和图4b是立视图。元件42a位于束成形网络多层板100之上，多层板100具体为三层板的圆盘。一共有一块叠在一块之上的16块束成形网络多层板100，从而实现图2的束成形器50。每块束成形网络板100有径向向外伸展的61个输出端102。从16块束成形网络板100的每一块的对应输出端102在16道功率组合器54中被相加。每个功率组合器54的相加后的输出通过同轴电缆104和有关的连接器104a接至61个元件42a。每个元件42a包括图3a-3c中所示的四个HPAs46。
用于实现天线阵元件40和42的一个可供选择实施例示于图7。在这实施例中，辐射元件由与通过膜孔112a与谐振腔114a耦合的导电板110构成。同样，谐振腔114a通过膜孔112b与谐振腔114b耦合。谐振腔114a和114b构成双极带通滤波器116。能量是通过相位差90°的导电路经118和120耦合至滤波器116或从滤波器116取出的。当这两路径在90°混合耦合器122中合并时，圆形极化波前是通过板辐射器110发射/接收。在这情况下每个元件可以用一个LNA/HPA供给。或者，这结构也可以与上述类似方式用二个或四个LNAs/HPAs供给，以产生圆极化辐射。本发明的这一实施例的优点是它可以运用多层印刷电路工艺构成，尽管电介质材料比上述的腔/喇叭辐射体中自由空间会有更大的损耗。然而，该印刷电路法的制造成本较低。
要注意图7中使用了两个C波段喇叭天线76a和76b，而天线分离滤波器72和74(图2b)被省去。
接收相控天线阵40的板110的代表尺寸设定在相邻板110之间的中心对中心距离为4.5英寸，而对于发射相控天线阵42其相邻板之间的中心对中心距离为3英寸。
现参阅图8和9，这二图更详细表明其中一个多层辐射板元件的结构细节。在图8中板110形成在介质材料表面110a上，并被导电绝缘平面110b所包围。板110和绝缘面110b由例如1/2盎斯的铜组成。在板110下面是实心铜平面，该平面有蚀刻孔用以界定膜孔112a。膜孔112a的铜平面可以在含有介质110a和板110的印刷电路层的背侧被蚀刻。在膜孔112a下面是含有介质材料12b的单面电路板，它有经蚀刻的铜方块用以构成滤波器114a。此经蚀刻的铜方块位于单面印刷电路板的底侧。在一块单面印刷电路板上设有第二膜孔112b，该膜孔也是在铜平面内蚀刻成的。滤波器114b是在有介质材料126的印刷电路板的底侧上蚀刻成的铜方块。位于滤波器114b下面的是实心铜接地平面122。膜孔112a、112b和滤波器114a、114b构成用于连接板110的双腔滤波器。涂以金属的通孔124从绝缘平面110b至地平面122，穿过所有这些层。
图9是表示位于其他层以上的图8中的板110和双腔滤波器的横截面图，其他层提供与MMIC放大器(对于接收相控阵40是MMIC LNA，对于发射相控阵42是MMIC SSPA)的连接。其他的六层提供另外三层地平面122以及相关的涂以金属穿过这六层的贯通引线122a。其中一层含有MMIC功率线迹128，其中一层含有MMIC控制线130，以及其中一层含有为MMIC输出的功率分配器132。完整的多层电路板140包括所需要粘结剂层，具有约为0.3英寸的总厚度。在本发明的一个最佳实施例中，单个的多层电路板140是这样构造的，使得总共具有61块板110及相连的双腔滤波器，支持电路和信号与功率线路。
导热层142(图7所示)位于多层电路板140下面，用于散去MMIC发出的热。导热层142可含有热管和/或其他合适的导热元件。
现已结合本文所提的最佳实施例详述了本发明。然而，应该明白在实施本发明时发射和接收元件数量、上行和下行线路束的数量和各个频率范围等并不局限于此。
因此，虽然现已结合本文推荐实施例已经具体图示和叙述了本发明。本专业的技术人员会明白在不脱离本发明范围和精神的情况下可以作出形式和细节上的各种变化。

Claims (15)

1.一种与通信系统配用的卫星有效负载，所述有效负载是具有带多个接收元件和接收功率放大装置的相控接收天线阵、第一波束形成装置、地面站通信装置、第二波束形成装置和带多个发射元件和发射功率放大装置的第二波束形成装置的那样一种有效负载，其特征在于，它包括：
具有n个接收元件的相控接收天线阵，用以接收第一频带范围内的射频信号；
第一束形成装置，其一个输入与所述n个接收元件中每一个相连，用于从由所述相控接收天线阵接收的射频信号中形成m个上行线路波束，其中n大于1，而m小于n；
地面站通信装置，该装置具有与所述第一波束形成装置的输出相耦合的输入，用于将所述m个上行线路波束转换为第二频带范围内的射频信号和将射频信号发射至地面站和从地面站接收射频信号，所发射和接收的射频信号在所述第二频带范围内；
第二波束形成装置，该装置具有与所述地面站通信装置的输出相耦合的输入，用于从所述地面站接收到的射频信号形成m个下行线路波束，所述m个下行线路波束在第三频带范围内形成；
具有n个发射元件的相控发射天线阵，用于将所述m个下行线路波束作为所述第三频带范围内的射频信号发射，每个所述发射元件有与之相关联的功率放大装置，每个所述功率放大器装置的输入与所述第二波束形成装置的输出相耦合，而其输出与其中一个所述发射元件相耦合，其中各所述n个发射元件给各所述m个下行线路波束发射射频能；
其中各所述m个上行线路波束具有对应的下行线路波束，它照射所述上行线路波束的同一发源部位，且所述相应的所述下行线路波束其中之一的功率级是所述上行线路波束的功率级的函数。
2.根据权利要求1的卫星有效负载，其特征在于，所述第一频带在L波段范围内，所述第二频带在C波段范围内，所述第三频带在S波段范围内。
3.根据权利要求1的卫星有效负载，其特征在于，所述n个接收元件中每一个有与之相耦合的多个接收放大器。
4.根据权利要求3的卫星有效负载，其特征在于，每个所述接收放大器的输入与一个所述接收元件的自由空间相耦合。
5.根据权利要求1的卫星有效负载，其特征在于，每个所述功率放大器的输出与一个所述发射元件的自由空间相耦合。
6.根据权利要求1的卫星有效负载，其特征在于，
所述第一波束形成装置包括：
n个功率分配器，各功率分配器有m个输出端，且一个输出端耦合到所述n个接收元件的一个输出端上；和
m个上行线路波束形成装置，各装置有m个输入端和一个输出端，各所述m个输入端耦合到各所述n个功率分配器的所述m个输出端之一上；且
所述地面站通信装置包括：
m个第一频率变换装置，各装置的一个输入端耦合到所述m个上行线路波束形成装置其中之一上，各所述m个第一频率变换装置的一个输出端供提供第二频带范围内的射频信号；
用以将所述m个频率变换装置的所述输出合并和发射m信道RF信号至地面站的装置，所发射的RF信号在所述第二频带范围内；
用以从地面站接收m信道RF信号的装置，所接收的RF信号在第二频带范围内；
m个第二频率变换装置，每个装置有与所述地面站接收装置的输出相耦合的输入，所述m个第二频率变换装置的每一个对所述接收到的m个信道中的一个作出响应，并具有用于提供第三频带范围内RF信号的输出；
所述第二波束形成装置包括：
m个下行线路波束形成装置，每个装置的具有与所述m个第二频率变换装置之一个的输出相耦合的输入；
n个功率组合器，每个组合器有用于与所述m个下行线路波束形成装置的输出相耦合的m个输入和一个与所述相控阵发射天线的所述n个发射元件之一耦合的输出。
7.根据权利要求6的卫星有效负载，其特征在于，所述第一频带在L波段范围内，所述第二频带在C波段范围内和所述第三频带在S波段范围内。
8.根据权利要求6的卫星有效负载，其特征在于，所述n个接收元件的每一个至少有一个与之相连的接收放大器，而每个所述接收放大器的输入与一个所述接收元件的自由空间相耦合。
9.根据权利要求6的卫星有效负载，其特征在于，所述n个发射元件的每一个至少有一个与之相耦合的发射放大器，每个所述发射放大器的输出与所述发射元件之一的自由空间相耦合。
10.根据权利要求6的卫星有效负载，其特征在于，所述n个上行线路波束中每束有对应的照射与源自所述上行线路波束相同区域的下行线路波束，所述下行线路波束中所述对应束的功率级随所述上行线路波束的功率级而变。
11.根据权利要求1的卫星有效负载，其特征在于，所述组件具有一般为有纵轴的圆柱形状，所述n个发射元件位于所述圆柱形的一端，所述m个波束形成电路装置的每一个包括一般为圆形的电路板，其所述n个输出沿着所述电路板的圆周排列，所述n个m路功率组合装置中的特定个，各包括沿所述纵轴位置的有一长度的电路板，用于将所述m个波束形成电路装置中每一个耦合到对应输出。
12.根据权利要求1的卫星有效负载，其特征还在于，所述相控发射天线阵的所述n个发射元件按预定的形式配置，且各所述n个发射元件有一个导电板和n个双腔滤波器，导电板配置在多层电路板的表面上，n个双腔滤波器分别电耦合到所述n个导电板其中之一上，该滤波器在所述多层电路板的多层中形成，所述多层处在所述表面下。
13.根据权利要求1的卫星有效负载，其中所述相控接收天线阵的各所述n个接收元件的接收功率放大装置与所述n个接收元件有关，所述相控接收天线阵的特征在于：
各所述接收功率放大装置具有在与所述n个接收元件相关处耦合到自由空间的输入端；且
所述第二波束形成装置有m个波束形成电路装置，各电路装置在所述相控接收天线阵的所述n个接收元件下面一个高于另一个地堆置配置。
14.根据权利要求13的卫星有效负载，其特征在于，所述组件具有一般为有纵轴的圆柱形状，所述n个接收元件位于所述圆柱形的一端，所述m个波束形成电路装置的每一个包括一般为圆形的电路板，所述n个输入沿所述电路板的圆周排列，所述n个m路功率分配装置中的个别装置每个包括沿所述纵轴位置设置的有一长度的电路板，用以耦合所述m波束形成电路装置中每一个的对应输入。
15.根据权利要求1的卫星有效负载，其中所述相控接收天线阵各所述n个接收元件的其中之一所述接收功率放大装置与各所述n个接收元件有关，所述接收功率放大装置有两个空腔滤波器，且与一个多层电路板连接，所述相控接收天线阵的特征在于，各所述n个接收元件包括一个导电板和n个所述双腔滤波器，导电板配置在所述多层电路板的表面上，各n个所述双腔滤波器电耦合到所述导电板其中之一上，该滤波器在所述多层电路板的多层中形成，所述的多层是处在所述表面下的。
CN93119051A 1993-05-07 1993-10-20 移动通信卫星有效负载 Expired - Fee Related CN1055184C (zh)

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US5422647A (en) 1995-06-06
EP0624008B1 (en) 2002-03-13
DE69331693T2 (de) 2002-11-21
EP0624008A2 (en) 1994-11-09
IL116890A (en) 1997-01-10
IL106744A0 (en) 1993-12-28
KR100289355B1 (ko) 2001-05-02
EP1133076A1 (en) 2001-09-12
KR100324655B1 (ko) 2002-02-27
US5548292A (en) 1996-08-20
DE69331693D1 (de) 2002-04-18
UA34438C2 (uk) 2001-03-15
CN1124892A (zh) 1996-06-19
US5623269A (en) 1997-04-22
IL106744A (en) 1996-10-16
EP1133002A1 (en) 2001-09-12
RU2136107C1 (ru) 1999-08-27

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