CN102741655B - 高空长航时无人驾驶飞机及其操作方法 - Google Patents
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Abstract
发明名称:高空长航时无人驾驶飞机及其操作方法。摘要。实施方案包括一个或多个具有一个或多个电磁(IR/可视光/RF)传感元件或套件(112,337)、能够持久定位的高空长航时(HALE)无人驾驶飞机(110),以进行测量和/或信号采集。实施方案包括一个或多个具有可定向激光器(331)、能够持久定位的高空长航时(HALE)无人驾驶飞机(110)。实施方案包括一组配置为GPS转发器的四个或更多个高空长航时(HALE)无人驾驶飞机(611-614)。
Description
说明书
相关申请的交叉引用
本申请要求以下申请的优先权和权益:于2009年12月18日提交的美国临时专利申请序列号61/288,238;于2009年12月18日提交的美国临时专利申请序列号61/288,249;以及,于2009年12月18日提交的美国临时专利申请序列号61/288,254;为了所有目的,包括附录在内的所有专利通过引用以其全文结合在此。
技术领域
本发明在其多个实施方案中总体上涉及飞机及其组件系统,并且更具体地涉及具有高空定位能力的高空长航时(HALE)无人驾驶飞机及使用HALE无人驾驶飞机的方法。
发明背景
基于太空的通信系统和基于太空的监控系统与地面系统和/或低空飞机的交互可能受第三方辐射故意消弱和/或大气影响。例如,全球定位系统(GPS)信号接收器在已知频率上接收来自GPS卫星的相对微弱的信号。因此,GPS接收器可能会受第三方的信号频率功率干扰。此外,地球的大气特性限制了基于地面的太空监控望远镜的性能,该监控望远镜带有用于观察轨道内目标的电光和红外或基于雷达的轨道成像系统。由于大气衰减且难以获得在外国进行基于太空监控系统的外交许可,导致国内单位在选择支持来自表面站点——地面或海面的太空操作时受限。
基于地面的太空系统典型地受地理和/或国家边界限制。当轨道力学结合其地面位置时,这些基于地球的站点只能看到上面的轨道。此外,基于地球的站点的操作常进一步受可用的有限基础设施和长期后勤支持的约束。由于物理限制以及潜在局限性,缺乏太空态势感知,基于地面的太空监控系统产生了地面操作局限性及缺陷,该地面操作可能高度依赖轨道系统提供的太空效应。
卫星可以采用大功率的数码相机以对地球表面感兴趣的区域成像。这些相机在大型光学系统后使用不同的可视和红外传感器。其传感器被设计成对来自地球表面感兴趣区域的光的总量敏感。卫星相机敏感光谱范围的或其内部的聚焦的强光会导致闪光盲并阻止相机对感兴趣目标区域的成像。基于地面的强光源受相对于目标卫星相机的物理位置的挑战,并进一步受大气衰减的挑战。
披露
在此披露了多个增强通信信道(包括全球定位系统(GPS)信号增强)的高空长航时(HALE)无人驾驶飞机的示例性方法和系统实施方案,以及多个禁止观测和/或轨道资产(比如卫星)通信的HALE无人驾驶飞机的示例性方法和系统实施方案。示例性HALE飞机可在平均海平面上(AMSL)65000英尺徘徊,在AMSL55000至70000英尺的平流层中徘徊,在65000英尺且其密度是海平面密度的7.4%的大气层徘徊。在65000英尺,只有相对海平面1.4%的空气分子。与地面传感器相比,稀薄的空气会转化为更小的光或广播功率衰减。HALE无人驾驶飞机的回转半径为通信中继设备提供相对静止的机载位置以重播内置的GPS信息。全球定位系统(GPS)信号增强示例性方法可包括:(a)部署一组四个或更多个高空长航时(HALE)无人驾驶飞机,每个无人驾驶飞机包括GPS天线、GPS接收机和GPS转发器;(b)通过该四个以上HALE无人驾驶飞机中的至少四个接收来自对应的GPS卫星的GPS信号;以及(c)分别通过该至少四个HALE无人驾驶飞机中的每一个形成用于传输的可重复接收的GPS信号。该示例性方法可进一步包括,通过至少该四个HALE无人驾驶飞机中的每一个传输对应的可重复接收的GPS信号。可选地,该示例性方法可进一步包括,通过该至少四个HALE无人驾驶飞机的每一个,在规定的地理边界内传输该可重复接收的GPS信号。此外,之前的实施方案可包括一组四个或更多个HALE无人驾驶飞机中的每一个以一个或多个定位模式在第一规定的地面区域上方的平流层中飞行。此外,该方法可进一步包括,通过该组四个或更多个HALE无人驾驶飞机重新定位从而以一个或多个定位模式在第二规定的地面区域上的平流层中飞行。
全球定位系统(GPS)信号增强系统的一个示例性系统实施方案可包括,一组四个或更多个高空长航时(HALE)无人驾驶飞机,每个飞机包括GPS天线、GPS接收机和GPS转发器;其中,每个HALE无人驾驶飞机可被配置为接收来自对应的GPS卫星的GPS信号,并形成可重复接收GPS信号用于传输。在一些系统实施方案中,至少四个HALE无人驾驶飞机的每一个进一步可被配置为在规定的地理边界内发射该可重复接收的GPS信号。此外,在一些实施方案中,该组四个或更多个HALE飞机中的每一个HALE无人驾驶飞机被配置为以一个或多个定位模式在第一规定的地面区域上的平流层中飞行。在一些系统实施方案中,该组四个或更多个HALE飞机中的每一个HALE无人驾驶飞机可被配置为以一个或多个定位模式在第二规定的地面区域上的平流层中重新定位和飞行。一些示例性系统实施方案可包括,每个HALE无人驾驶飞机被配置为在两个或更多个二十四小时周期内持续位于高空,并被配置为着陆进行再补给和/或修理,也就是,飞机和/或机载元件修理;以及然后回到平流层。
实施方案包括通信禁用和/或被动监控禁用。例如,一种卫星传感器禁用方法,可包括:(a)部署第一高空长航时(HALE)无人驾驶飞机,该无人驾驶飞机包括卫星跟踪器和与该卫星跟踪器配合的可定向电磁(EM)辐射发射器;(b)通过该卫星跟踪器获取具有机载EM传感器的卫星;(c)通过该卫星跟踪器跟踪该获取的卫星;以及(d)通过该可定向EM辐射发射器向该跟踪的卫星发射禁用EM辐射。该示例性方法可进一步包括,在该第一HALE无人驾驶飞机发射步骤之前:(a)部署包含卫星跟踪器的第二HALE无人驾驶飞机;(b)由该第一HALE无人驾驶飞机向第二HALE无人驾驶飞机发送该被跟踪卫星位置的信号;(c)通过该第二HALE无人驾驶飞机的卫星跟踪器获取被该第一HALE无人驾驶飞机跟踪的卫星;以及(d)通过该第二HALE无人驾驶飞机的卫星跟踪器跟踪由该第一HALE无人驾驶飞机跟踪的卫星。该方法可进一步包括,通过该第二HALE无人驾驶飞机,该第二HALE无人驾驶飞机向该第一HALE无人驾驶飞机传输禁用评估。可选地,该示例性方法的第二HALE无人驾驶飞机可进一步包括与该第二HALE无人驾驶飞机的卫星跟踪器配合的可定向电磁(EM)辐射发射器。该方法可进一步包括,由该第二HALE无人驾驶飞机的可定向EM辐射发射器基于禁用评估向该被跟踪的卫星发射禁用EM辐射,该禁用评估属于以下内容中的至少一个:该第一HALE无人驾驶飞机和该第二HALE无人驾驶飞机。对于一些实施方案,该示例性方法的第一HALE无人驾驶飞机的可定向EM辐射发射器可包括安装了转台的激光器。在一些实施方案中,该第一HALE无人驾驶飞机的卫星跟踪器可包括提供与跟踪处理器通信的光电传感器的陀螺式稳定可伸缩平台。
卫星传感器禁用系统实施方案可包括第一高空长航时(HALE)无人驾驶飞机,该无人驾驶飞机包括卫星跟踪器和与该卫星跟踪器配合的可定向电磁(EM)辐射发射器,其中,该卫星跟踪器可被配置为获取和跟踪具有机载EM传感器的卫星;以及,其中该可定向EM辐射发射器可被配置为向该被跟踪卫星的EM传感器发射禁用EM辐射。该系统实施方案可进一步包括,第二HALE无人驾驶飞机,该无人驾驶飞机可包括卫星跟踪器,其中该第二HALE无人驾驶飞机可被配置为通过由该第一HALE无人驾驶飞机发送信号或通过地面站发送信号来接收该被跟踪卫星的位置;其中,该第二HALE无人驾驶飞机的卫星跟踪器可被配置为获取由该第一HALE无人驾驶飞机跟踪的卫星;以及,其中,该第二HALE无人驾驶飞机的卫星跟踪器可进一步被配置为跟踪由该第一HALE无人驾驶飞机跟踪的卫星。一些系统实施方案的第二HALE无人驾驶飞机可进一步被配置为向该第一HALE无人驾驶飞机发射禁用评估。一些系统实施方案的第二HALE无人驾驶飞机可进一步包括与该第二HALE无人驾驶飞机的卫星跟踪器配合的可定向电磁(EM)辐射发射器。一些系统实施方案的第二HALE无人驾驶飞机的可定向EM辐射发射器可进一步被配置为基于第一HALE无人驾驶飞机和/或第二HALE无人驾驶飞机的禁用评估向被跟踪的卫星发射禁用EM辐射。对于一些系统实施方案,该第一HALE无人驾驶飞机的可定向EM辐射发射器可包括安装了转台的激光器。一些系统实施方案的第一HALE无人驾驶飞机的卫星跟踪器可包括提供与跟踪处理器通信的光电传感器的陀螺式稳定可伸缩平台。
附图简要说明
图1描绘了一个位于卫星发射器和地面发射器之间的平流层中的高空长航时(HALE)无人驾驶飞机;
图2描述了赤道上的HALE无人驾驶飞机及其朝地球的视图;
图3描绘了配置为跟踪卫星和/或禁用卫星传感器的HALE无人驾驶飞机;
图4描绘了一组位于卫星发射器与地面发射器之间平流层中的HALE无人驾驶飞机;
图5描绘了两个中继转发地面RF发射器与地面RF接收器间通信的HALE无人驾驶飞机;
图6描绘了一组配置成为面对相互连接的地面RF发射器的地面接收器转发GPS信号的HALE无人驾驶飞机;以及
图7描绘了配置成为面对GPS功率干扰器的地面接收器转发或增强GPS信号的一组HALE无人驾驶飞机中的一个成员。
最佳模式
图1描绘了一个高空长航时(HALE)无人驾驶飞机110,该飞机包括具有外壳的机身111。该机身容纳了通信套件,且可具有一个或多个前向电磁(IR/可视/RF)传感器套件112。包括多个传感器元件121-126的电磁辐射传感器阵列被描绘成布置在机身111的外壳上,其中,前传感器元件122和尾部传感器元件121规定了一个纵向传感器阵列基准线131。还描绘了规定横向传感器阵列基准线132的右舷翼尖传感器元件123和左舷翼尖传感器元件124。因此,该HALE无人驾驶飞机被描绘成配置为接收和处理来自示例性资产(比如卫星无线电频率(RF)发射器141、地面红外发射器142、地面可视波段发射器143、地面RF发射器144)的信号情报,当HALE在平流层150中飞行多个二十四小时周期,可能会这么做。
传感器不仅可以安装在机翼内部还安装在HALE飞机平台顶部。HALE飞机可包括坚固翼展的机翼,其中该长机翼可大部分是中空的,且HALE可包括一个长的尾桁。通过沿着和/或在机翼和/或尾桁末端布置的传感器,HALE飞机提供的几何体和距离使其成为进行电磁信号收集的理想近空资产。此外,HALE飞机可以几乎静止的飞行模式保持在高空,也就是,从地面观察员角度,在地面区域上空提供连日的实时持久的信号映射。
除布置在飞机顶部的传感器外,布置在HALE飞机平台下的传感器也会增加第三方信号辐射的接收和处理以及影响HALE飞机传感器组的电磁频谱映射。结合其他类似配置的HALE飞机或其他信号收集资产,对信号环境的透彻了解(以包括干扰检测或分析或其他广播)可提供太空和地面的操作。因此,正如来波时间分析法可用于翼尖布置的传感器之间,来波时间或其他形式的分析法可用于交叉布置在一群类似配置的HALE飞机的传感器之间。
通过一个或多个HALE飞机实施方案的定位可提高太空态势感知、通信信号增强和/或通信禁止。HALE飞机实施方案可在平流层情况下在一组定位飞行模式下重新定位,例如,在海平面上方65000英尺和/或海平面上方55000-70000范围之内,在一些实施方案中达到100000英尺,因此可用多个平台在广阔范围内提供全球持久性。在平流层情况下,HALE飞机实施方案不受天气状况影响,但对操作期内昼夜变化非常敏感。参照于2007年10月16日发布给MacCready等人的名称为“氢动力飞机(HydrogenPoweredAircraft)”的美国专利号7,281,681,和于2005年8月16日发布给Cox等人的名称为“飞机控制方法(AircraftControlMethod)”的美国专利号6,913,247,这些专利通过引用以其全文结合在此。
还参照于2005年9月13日发布给Cox的名称为“通信系统(CommunicationSystem)”的美国专利号为6,944,450,和于2007年4月3日发布给Lisoski等人的名称为“飞机控制系统(AircraftControlSystem)”的美国专利号7,198,225,这些专利通过引用以其全文结合在此。作为平流层持续监控平台,HALE无人驾驶飞机被放置为地球同步定位,并可以重新定位。图2描绘了赤道210上的一个HALE无人驾驶飞机(非等比例),通过其平流层位置,该无人驾驶飞机可支持具有倾斜角小于17度220高于100英里的卫星的获取。HALE飞机可着陆以加油、替换或更新设备,或临时退出以修理设备,然后重新回到平流层的定位。HALE在高空时可重定向到不同的地球同步位置。HALE飞机可包括与机身宽度相对的坚固翼展,和/或与机身宽度相对的坚固尾桁长度。因此,传感器可放置在具有足够间隔的外部位置,以通过紧急HALE飞机或HALE群的另一个成员支持光学三维视图或卫星干扰和/或强光的影响的评估。三维视图还可支持识别和评估近似友好太空资产的未识别太空资产。参照于2010年9月28日发布给Kendall等人的名称为“飞机控制系统(AircraftControlSystem)”的美国专利号7,802,756,和于2003年4月22日发布的MacCready等人名称为“液态氢平流层飞机(LiquidHydrogenStratosphericAircraft)”的美国专利号6,550,717,这些专利通过引用以其全文结合在此。
通过操作员指导大片水域(比如,国际海中航线和其他海域)上的HALE飞机,可提高态势感知,其中太空态势感知可通过集成在一个或多个HALE飞机平台顶部和/或内部的望远镜和电光和红外轨道成像传感器或雷达及相关设备获得。例如,支持太空态势感知的太空监控,可使用安装在HALE飞机机身顶部的电光/红外(EO/IR)传感器和/或雷达频率(RF)传感器。也就是说,卫星和太空监控的示例性传感器可被定向为观察太空以使用安装在HALE飞机顶部和/或底部的信号检测装置来支持太空态势感知,以进行电磁频谱映射或处理所接收到的第三方信号,例如,信号情报处理。图3描绘了一个HALE无人驾驶飞机110,用剖面展示了多个不同波长激光器331、332、向陀螺式固定望远镜335提供激光的光组合器333,该望远镜可安装在双轴转台336上。图3还描绘了与跟踪器处理器338配合的EO/IR传感器337。因此,该HALE无人驾驶飞机可观测到卫星340和/或使卫星传感器丧失其观测能力或使其目眩,和/或干扰卫星340的通信接收。
支持太空态势感知的太空监控任务通过使用固定(即,大致与地球同步)HALE飞机的传感器仰望太空进行监控太空。物镜可用来跟踪和理解友好资产的战斗序列和潜在敌对资产的战斗序列—例如,从发射的时刻。面对地球的当前可用电光、红外和雷达传感器,也就是,被定向为接收来自地球的输入,可检测比当前在太空观看到更混乱和多变的表面。因此,示例性转台外壳传感器可安装在HALE飞机的转台上,每个转台通过已有传感器定制,这些传感器允许它们用红外、低光和电光传感器望向寒冷的太空,并在最小或不被大气失真的情况下看到卫星。因此,合成孔径雷达(SAR)有效载荷可包括示例性HALE飞机的传感器套件。
因此,图3描绘了单个HALE无人驾驶飞机,两个或更多个HALE无人驾驶飞机可用于干扰通信卫星,其中该HALE飞机可能已经指引向太空发射的无线频率干扰系统,和/或使用定向激光器使第三方光接收器失效,即,使用HALE飞机和射向太空的定向激光器系统使低地轨成像卫星失效或炫目。与该敏感光谱带或卫星传感器匹配的适当波长的一个激光器或多个激光器及光输出功率可安装在HALE飞机平台中,例如,在转台外壳内或贴近转台外壳。为执行眩晕或爆盲任务,示例性HALE飞机可配置有EO/IR传感器,例如,L3-Sonoma494或RaytheonMTS-B转台或其他用于高性能地面和飞机系统的雷达阵列。来自这些传感器的激光波束可通过光学系统结合,其输出可以是与望远镜耦合的光纤。部分望远镜实施方案可与EO/IR传感器转台类似,该传感器转台可修改为对着目标卫星投射多光谱激光器波束。望远镜系统还可以包括成像传感器,该传感器可用于跟踪目标卫星并确保所投射的激光波束照着目标。附加HALE飞机可用于提供针对干扰的额外透视,包括通过定向RF功率发射器的RF干扰,和/或会影响炫目,以及,一个或多个可用于观察干扰和/或炫目对目标影响的附加HALE飞机。
典型地,现代通信卫星携带多个使用行波管放大器(TWTA)的Ku-波段转发器以在覆盖多边形的边缘提供50-60dBW有效等向辐射功率(EIRP)。此外,使用TWTA的C-波段转发器来提供在覆盖边缘39dBW的EIRP。根据功率和天线增益,在65000的近太空高度、在地球同步通信卫星的等效等向辐射功率(EIRP)范围内广播HALE飞机平台的发射机将干扰或有可能遮蔽来自卫星并由预期地面站点接收的信号。
目标卫星的当前卫星星历数据会是可用的和/或来自其他源(比如,远程地面站点)的数据可向HALE飞机平台特别是传感器套件提供行间导航,以目标获取来为可能的EO/IR或卫星的雷达成像确定位置和方位。HALE飞机平台的跟踪传感器可以是雷达或高分辨率图像,比如所有波长中HDTV分辨率或更好的。该HALE飞机可位于站点,而传感器和卫星间的视角(LOS)可以是45度内的最低点。
示例性获取过程:HALE飞机平台传感器可指向从目标卫星星历数据计算出的坐标轴,该星历数据可解析约0.1度的方位角及传感器能力范围的适当高度。一旦观测到,该系统将通过指向孔径采用视频跟踪算法以便将目标置于最佳干扰发射光束的中心。然后,该系统可指向/指导干扰器件孔径,以便将目标置于传感器视角内,跟踪和增加功率以改善所期望的干扰。该传感器可指向从目标卫星星历数据计算的坐标,因为该星历数据典型地期望解析方位和评估角度的0.1度,该值期望位于为实施方案选择的传感器的能力内。如果目标卫星不在初始视角内,该传感器可在初始指向周围区域内执行螺旋式搜索扫描直到发现该目标。然后,传感器套件可通过指向转台来使用视频跟踪算法以使目标位于传感器视角范围内的中心,即,将原因归结于目标上,例如,在水平和垂直的中心像素。然后,可指向/指引/定向转台的传感器套件,以便维持目标中心位于传感器视角内,跟踪和增加变焦或焦距以提高跟踪精度。
示例性传感器可包括设计有转台应用的当前可用电光和红外传感器,比如RaytheonMTS或Sonoma494转台。此外,HALE飞机顶部的雷达传感器可包括能够提供卫星度量标准和/或成像数据的SAR、GMTI或AESA类型阵列。这些传感器除安装或集成在与飞机载荷内设备相关联的机身上,还可安装在或集成在HALE飞机机翼或尾桁上。这些传感器(比如,天线,阵列,定向算法和当前用于其他飞机或卫星的设备)除安装或集成在与飞机载荷舱内设备相关联的机身上,还可安装在或集成在HALE飞机机翼或尾桁上。
与安装在HALE飞机顶部的可用三波段天线结合的相关发射装置机架提供足够的功率和增益以拒绝、降低和中断带有较低大气阻抗的卫星通信信号和信号传播,因为在轨HALE飞机上65000英尺或海平面55000至70000英尺范围内剩余少量大气。
目标卫星的当前卫星星历数据可向HALE飞机传感器提供行间导航以进行目标获取。该HALE飞机可位于站点,而传感器和卫星间的视角(LOS)可以位于COMSAT的EIRP内。
随着安装了HALE的激光器波束从其源端传播的越远,它会发散,且随着其发散,其能量会扩展到更大的区域。此外,随着其穿过当前大气,该波束会衰减。一旦激光波束到达卫星探测器,卫星照相机光学器件汇聚落到该物镜上的所有光,并将其聚焦到图像传感器的表面。这增强了传感器表面的激光辐射强度。
轨道目标可以使用的数字图像传感器可包括互补金属氧化物半导体(CMOS)和电荷耦合器件(CCD)传感器和其不同的阵列或组件。这些传感器具有称为像素的小型光敏区域,像素用来衡量落在它们上面的辐射能量。落到每个像素上的辐射能量的总和与该像素自身面积成正比。典型的面积范围从超过20微米到5微米以下。为进行讨论,假设本例子中每个像素的大小是9微米见方。因此,如果传感器上每平方厘米的激光辐射为0.43mw,该传感器是20mm见方,像素可以是9微米见方,则横穿传感器的宽和高有2222个像素(约5百万像素),且落到每个像素上的激光能量为0.3496纳瓦。换句话说,该卫星CCD(照相机)将失效。保守假设,激光辐射波长的量子效率为21%。因此,例如,600纳米波长(可视红色)的激光器,对通用CCD传感器的红色像素具有近似最高的灵敏度。然后,可计算每个光子的能量,为:Ep=η-λ/c,其中h是Planck常数,λ/c是激光频率波长除以光速。求解每个光子600nm为3.3093-19焦耳。因此,对于连续波激光器源,每秒每个像素有约1万亿光子。进一步假设,1毫秒测量时间,这类似于胶片照相机的快门或曝光时间,对于具有21%量子效率的CCD传感器,每个像素上会充上221,834个电子。典型CCD传感器的每个像素充满100,000个电子。因此,在本例中,卫星照相机将在所有红色像素(即,过度曝光)上失效。
然而,卫星照相机具有覆盖全部可视频谱和几个红外波段的传感器。在多个IR波段敏感的传感器具有类似的标定点,这些标定点在其对应的波段达到最高。为了使可视CCD传感器完全失效,需要结合来自红色、绿色和蓝色激光器的光。合理的波长可分别是450nm、530nm和600nm。还需要增加具有适当IR波长的附加激光器。这些波长的激光器和感兴趣功率范围可以是现有技术且可集成在HALE飞机平台。
可通过全球定位卫星(GPS)、惯性数据包和恒星跟踪(如果需要)确定HALE飞机位置精度,其中,仪器的选项、数量和质量可根据可接受的系统信号衰减和其他性能参数变化而变化。干扰功率和类型可由目标卫星转发器、信道、信号极化和发射功率来驱动,以确保集成在HALE飞机中反通信设备的锁定和干扰效率。图4描绘了一组三个HALE无人驾驶飞机411-413,每个与另外一个通信,其中这组飞机以定位模式在平流层水平面飞行,但都在地面发射器的波束宽带内,比如红外发射器421、可视波段发射器422和/或RF发射器423。图4还描绘了与卫星450通信的一组HALE无人驾驶飞机中的至少一个411。一个或多个地面发射器可以是一个使用行间向量(IRV)进行观测的卫星跟踪站,因此它们的发射可包括用于支持值行间导航的IRV数据。
HALE飞机可在受GPS干扰的感兴趣区域上的最大高度包层内徘徊。HALE飞机可配置成作为机载假卫星(或“伪卫星”)来操作,该假卫星提供高功率GPS信号以控制干扰机。因此,HALE飞机的机翼,每一个都被配置为伪卫星系统的一部分,可具有GPS卫星星体的低轨道子集功能。例如,完整的导航解决方案需要四个伪卫星,就像今天需要四个GPS卫星一样。该示例性HALE机载伪卫星首先从GPS卫星确定/发现它们各自的位置,即使有干扰。由于它们位于远离地面基站干扰器的高海拔,和/或通过形成天线的波束和降低干扰效应的信号处理器,因此它们得以实现。然后,HALE星群以更高的功率和比卫星可实现的更近范围向地面发射类似GPS的信号(重播)。因此,该信号可以抑制干扰器并允许多个用户来克服干扰并继续导航。
结合该HALEUAV性能和当前领域Ku-波段软件定义的无线电系统以及相关联的路由器具有传送数据范围从10.71Mbps到45Mbps的多个安全链路的指引能力。274Mbps技术可处于一年内使用与当前能力一样的相同硬件SWAP的范围内。类似地,如果在紧急期间内地面系统不可用,则警察、消防和其他紧急第一反应器使用的蜂窝电话技术、VHF和其他地面支持无线电、蜂窝电话和其他通信系统需要具有应急能力。一旦兼容电子器件可位于在HALE飞机,该平台可作为对第一反应器的通信中继和广播源,就像伪卫星平台或手机发射塔。
HALE飞机可被配置为借助或不借助机载星体跟踪器来接收和处理GPS信号。一旦该GPS信号由HALE飞机的一个或多个无线接收器接收,该信号会转换到Ku波形,会嵌入到已有数据通信链路,并重播至集成在其他平台中的接收器,因此在不经受干扰的情况下来避开GPS调谐干扰环境。
面对干扰和/或通信卫星失效,两个或更多个HALE无人驾驶飞机可增加或本地替换卫星通信。例如,图5描绘了通过定位模式511在平均海平面上55000-70000英尺高空和地面RF发射器520波束宽带内定位第一HALE无人驾驶飞机510。该第一HALE无人驾驶飞机510被描绘成接收地面RF发射器520的传输,并中继或另外向第二HALE无人驾驶飞机530发射该通信。该第二HALE无人驾驶飞机530可被配置为向附加HALE无人驾驶飞机中继该通信,或如图5所描绘,向地面RF接收器540传输该通信。
图6描绘了在平流层和地面GPS接收器620的波束宽带内以一组地球同步飞行模式的一组四个HALE无人驾驶飞机611-614。地面RF发射器630被描绘成为示例性GPS星群640互联和/或主动干扰GPS信号。精度导航和由基于HALE接收器接收的全球定位系统(GPS)信号定时的增强,可受路由信号穿过安装在HALE机身内的软件定义的无线电的影响,以在干扰环境下信号确认。因此,精度导航和全球定位系统(GPS)信号定时的增强可受重播GPS卫星RF信号到地面和来自HALE飞机的GPS转发器电子器件的机载接收器影响。HALE飞机可配置为具有代理通信卫星能力,为重构机载通信节点,以增强地面通信退化和/或卫星通信(SATCOM)信号退化或消失。
图7描绘了一组类似图6中的单个HALE无人驾驶飞机710。该单个HALE无人驾驶飞机710被描绘成包括GPS天线711和GPS接收器712以接收来自GPS星群750的GPS信号。该单个HALE无人驾驶飞机710还被描绘成包括收发器713,以发射到地面重复GPS信号和/或在辅助频带内向地面传输转换的GPS信号。如果地面GPS接收器720可能受到GPS功率干扰器760的干扰,然后HALE无人驾驶飞机710可通过GPS频率向地面GPS接收器720提供中继器传送,或可被配置为通过辅助RF信道(例如Ku波段传输)向与GPS接收器720配合的地面RF接收器730传输重复信息。通过在辅助RF信道内传输四个重复GPS信号,在由RF接收器730处理转换后,该GPS接收器可生成GPS方案。
监控的精度典型地依据准确位置和几何形状,并降低传感器性能。HALE飞机的位置精度可通过机载全球定位卫星(GPS)接收器和惯性指令包来确定,以及,如果需要,星体跟踪,其中仪器的选项、数量和质量随着可接受的系统信号衰减和其他性能参数变化而变化。此外,一旦可以相对于目标卫星或地面目标(由监控感兴趣区域或通过第三方源获得的地面数据)的大概当前卫星星历数据确定HALE飞机位置,则可以执行数据收集,其中可进一步确定和指出信号和正在接收的信号的源。
可以认识到可以对上述实施方案的特定特征和方面作出不同的组合和/或子组合,而仍属于本发明的范畴。因此,应当了解到本披露实施方案的不同特点和方面可以相互结合或替换以组成本披露发明的不同模式。进一步地,通过举例披露的本发明的范围不由以上描述的具体披露实施方案所限制。
Claims (14)
1.一种卫星传感器禁用方法,包括:
部署第一高空长航时无人驾驶飞机,该无人驾驶飞机包括卫星跟踪器和与该卫星跟踪器配合的可定向电磁辐射发射器,
通过该卫星跟踪器获取具有机载电磁传感器的卫星;
通过该卫星跟踪器跟踪该获取的卫星;以及
通过该可定向电磁辐射发射器向所跟踪的卫星发射禁用电磁辐射。
2.如权利要求1所述的方法,进一步包括:
在该第一高空长航时无人驾驶飞机发射步骤之前,部署包含卫星跟踪器的第二高空长航时无人驾驶飞机;
由该第一高空长航时无人驾驶飞机向第二高空长航时无人驾驶飞机发送该被跟踪卫星的位置的信号;
通过该第二高空长航时无人驾驶飞机的卫星跟踪器获取被该第一高空长航时无人驾驶飞机跟踪的卫星;以及
通过该第二高空长航时无人驾驶飞机的卫星跟踪器跟踪由该第一高空长航时无人驾驶飞机跟踪的卫星。
3.如权利要求2所述的方法,进一步包括,通过该第二高空长航时无人驾驶飞机,该第二高空长航时无人驾驶飞机向该第一高空长航时无人驾驶飞机传输禁用评估。
4.如权利要求2所述的方法,其中,该第二高空长航时无人驾驶飞机进一步包括与该第二高空长航时无人驾驶飞机的卫星跟踪器配合的可定向电磁辐射发射器。
5.如权利要求4所述的方法,进一步包括:由该第二高空长航时无人驾驶飞机的可定向电磁辐射发射器基于禁用评估向该被跟踪的卫星发射禁用电磁辐射,该禁用评估属于以下内容中的至少一个:该第一高空长航时无人驾驶飞机和该第二高空长航时无人驾驶飞机。
6.如权利要求1所述的方法,其中,该第一高空长航时无人驾驶飞机的可定向电磁辐射发射器是安装了激光器的转台。
7.如权利要求1所述的方法,其中,该第一高空长航时无人驾驶飞机的卫星跟踪器包括提供与跟踪处理器通信的光电传感器的陀螺式稳定可伸缩平台。
8.一种卫星传感器禁用系统,包括:
第一高空长航时无人驾驶飞机,该无人驾驶飞机包括:
卫星跟踪器和与该卫星跟踪器配合的可定向电磁辐射发射器,其中,该卫星跟踪器被配置为获取和跟踪具有机载电磁传感器的卫星;以及,其中,该可定向电磁辐射发射器被配置为向该被跟踪卫星的电磁传感器发射禁用电磁辐射。
9.如权利要求8所述的系统,进一步包括:
第二高空长航时无人驾驶飞机,包括卫星跟踪器,其中该第二高空长航时无人驾驶飞机被配置为通过由该第一高空长航时无人驾驶飞机发送信号或通过地面站发送信号来接收该被跟踪卫星的位置;
其中,该第二高空长航时无人驾驶飞机的卫星跟踪器被配置为获取由该第一高空长航时无人驾驶飞机跟踪的卫星;以及,其中,该第二高空长航时无人驾驶飞机的卫星跟踪器进一步被配置为跟踪由该第一高空长航时无人驾驶飞机跟踪的卫星。
10.如权利要求9所述的系统,其中,该第二高空长航时无人驾驶飞机进一步被配置为向该第一高空长航时无人驾驶飞机发射禁用评估。
11.如权利要求9所述的系统,其中,该第二高空长航时无人驾驶飞机进一步包括与该第二高空长航时无人驾驶飞机的卫星跟踪器配合的可定向电磁辐射发射器。
12.如权利要求11所述的系统,其中,该第二高空长航时无人驾驶飞机的可定向电磁辐射发射器进一步被配置为基于禁用评估向被跟踪的卫星发射禁用电磁辐射,该禁用评估属于以下内容中的至少一个:该第一高空长航时无人驾驶飞机和该第二高空长航时无人驾驶飞机。
13.如权利要求8所述的系统,其中,该第一高空长航时无人驾驶飞机的可定向电磁辐射发射器是安装了激光器的转台。
14.如权利要求8所述的系统,其中,该第一高空长航时无人驾驶飞机的卫星跟踪器包括提供与跟踪处理器通信的光电传感器的陀螺式稳定可伸缩平台。
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- 2010-12-17 CN CN201080063267.5A patent/CN102741655B/zh active Active
- 2010-12-17 JP JP2012544929A patent/JP2013515242A/ja not_active Withdrawn
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- 2010-12-17 SG SG10202006739QA patent/SG10202006739QA/en unknown
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2016
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2017
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SG10202006739QA (en) | 2020-08-28 |
SG10201408310QA (en) | 2015-01-29 |
US9404750B2 (en) | 2016-08-02 |
US11299269B2 (en) | 2022-04-12 |
JP2013515242A (ja) | 2013-05-02 |
EP2513600A4 (en) | 2013-08-28 |
US20220194582A1 (en) | 2022-06-23 |
US20160311531A1 (en) | 2016-10-27 |
WO2011075707A1 (en) | 2011-06-23 |
US20140195150A1 (en) | 2014-07-10 |
CN106125094A (zh) | 2016-11-16 |
EP2513600A1 (en) | 2012-10-24 |
US20180086459A1 (en) | 2018-03-29 |
CN102741655A (zh) | 2012-10-17 |
AU2010330766A1 (en) | 2012-08-09 |
SG182554A1 (en) | 2012-08-30 |
CN106125094B (zh) | 2020-01-10 |
KR20120109563A (ko) | 2012-10-08 |
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