CN106275467B - 用于整合平视显示器和下视显示器的系统和方法 - Google Patents
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Abstract
一种可以用于航空器或其他车辆的方法或系统。所述系统可以包括或所述方法可以使用设置在遮光板之上和之下的波导。所述波导可以为平视显示器(HUD)的部分。所述波导可以设置为至少部分地覆盖下视显示器，以提供整合的显示。
Description
背景技术
显示器用于各种各样的应用。例如，航空电子系统和其它车辆系统使用下视显示器(HDD)系统和平视显示器(HUD)系统，包括但不限于诸如头戴显示器(HMD)系统的可穿戴显示器。在航空器应用中，HUD和HDD系统以图像的和字母数字的格式有利地显示来自航空器系统和传感器的信息。显示信息可包括来自视觉系统(例如，相机或其它成像传感器(诸如可见光成像传感器、红外成像传感器、毫米波雷达成像器，或它们的组合))的增强视觉图像。显示信息还可以或可替代地包括来自合成视觉系统的合成视觉图像(例如，基于地形和结构数据库的计算机生成的图形)。
HUD通常包括设置在遮光板上方的叠像镜，并且可以通过挡风玻璃提供与环境视野保形的信息。由于遮光板和在遮光板之后的设备不透明，常规的HUD不能用于通过遮光板保形地观看信息。现代的驾驶舱正在合并大区域的下视显示器(LAD或LAHDD)系统。LAD可提供全景和大区域，以在航空器的遮光板之下显示信息。然而，这样的LAD不提供HUD能力。此外，在遮光板之下的LAD的设置难以提供与飞行员的环境视野连续的图像。
因此，需要一种显示系统，其提供连续的外部环境视野，而不管LAD的存在。进一步，需要增加用在航空器和其它车辆中使用的显示系统的竖直视野。更进一步，需要整合HDD和HUD上提供的图像。再进一步，需要在驾驶舱或控制中心中整合有LAD或其他HDD的HUD。再进一步，需要用于与LAD使用的紧凑的HUD。进一步，需要一种显示系统，其可提供扩展的竖直视野。更进一步，需要在HDD上的虚拟视窗图像，其与通过HUD的叠像镜的视图相匹配。再进一步，需要与来自HUD的叠像镜的视图整合的视觉系统图像或合成视觉图像。
发明内容
在一个方面中，本文公开的发明概念针对可以与航空器或其它车辆使用的方法或装置。该装置可以包括或该方法可以使用至少部分地设置在遮光板的顶表面之上的波导。波导可以为平视显示器(HUD)的部分。波导可以扩展至遮光板的下方，以部分地或完全地覆盖LAD，以提供整合的显示
在另一个方面中，本文描述的发明概念针对在驾驶舱中使用的并且用于从图像源提供光的显示系统。显示系统包括波导和下视显示器。波导至少部分地设置在遮光板的顶表面的上方并且具有在第一端处的第一联接器和在第二端处的第二联接器。波导定位为叠像镜并且允许查看外侧镜像以及来自图像源的信息。下视显示器设置在遮光板的顶表面的下方。波导设置为至少部分地覆盖下视显示器。
在又一方面中，本文公开的发明概念针对将第一图像和第二图像提供给飞行员的方法。该方法包括在至少部分地设置在遮光板的顶表面的上方的波导叠像镜上提供第一图像，以及在所述遮光板的所述顶表面的下方的下视显示器的屏幕前方的所述波导叠像镜上提供第二图像。所述第二图像包括与通过波导组合器上的第一图像的环境视野连续的视觉图像或合成视觉图像。
在又一方面中，本文公开的发明概念针对平视显示器。平视显示器包括包括输入光栅和输出光栅的波导叠像镜。光通过全内反射从输入光栅行进至输出光栅。波导叠像镜具有设置在遮光板的顶表面之上的顶边缘和设置在遮光板的顶表面之下的底边缘。平视显示器构造为将图像从顶边缘提供至底边缘
附图说明
从下面的结合附图的详细描述，本公开将变得更充分地理解，其中同样的参考数字表示同样的组件，并且：
图1是根据一些实施方式的，包括显示系统的航空器控制中心或驾驶舱的立体图；
图2是根据一些实施方式的，可用作图1的航空器控制中心中的显示系统的用于显示图像的显示系统的示意性的总体框图；
图3是根据一些实施方式的，图1中图示的显示系统的更详细的局部主视平面图，其示出了由显示系统提供的更详细图像；
图4A是根据一些实施方式的，用于图3中图示的显示系统的叠像镜的简化的侧视图；
图4B是根据一些实施方式的，用于图3中图示的显示系统的叠像镜的简化的俯视图；
图5是根据一些实施方式的，图1中图示的显示系统的更详细的局部主视平面图，其示出显示系统上提供的更详细的图像；
图6是根据一些实施方式的，示出使用图1中图示的显示系统，以在进场至跑道时获得增加的竖直视野的航空器的图示；以及
图7是根据一些实施方式的，使用图1中图示的显示系统的航空器的图示，其示出与使用增加的竖直视野相关联的探测高度的增加，增加的竖直视野通过使用显示系统而达到。
具体实施方式
在详细描述具体的改进系统和方法之前，应该观察到的是，本发明包括但不局限于常规数据/信号处理以及光学元件和通信电路的新颖结构组合，并且不受限于其特定的细节配置。相应地，在大多数情况下，已经在附图中通过易于理解的方框图和示意图图示了各种部件的结构、方法、功能、控制和排列，软件以及电路，以避免本公开与从这里的描述中获益的本领域技术人员清楚知道的结构细节相混淆。进一步地，本文所公开的本发明概念并不局限于示例性附图中描绘的特定实施方式，而是应该依照权利要求中的文字来解释。
根据一些示范性实施方式，显示系统给环境提供了虚拟视窗，而不管下视显示器(HDD)或其他结构的阻挡效果。在一些实施方式中，平视显示器(HUD)与HDD重叠以增加竖直视野。在一些实施方式中，HUD和HDD可被整合到单个单元中。结合HUD操作，显示系统允许感测的(来自增强的视觉系统(EVS))和生成的(来自合成的视觉系统(SVS))真实世界的特征和/或代表图标显示给机组人员。有利地，一些实施方式的系统和方法使保形视图向下扩展在驾驶舱显示器之前或者航空器中的在飞行员之前的HDD之前。
在一些实施方式中，该系统和方法扩大了HUD叠像镜的竖直区域，以向下扩展至或经过大格式HDD的上边缘，并且覆盖在大格式显示器上的图像的顶部的或替代该大格式显示器上的图像的波导的保形(例如，准直的)图像。在一些实施方式中，大格式显示器之前的HUD叠像镜上的图像也显示驾驶舱的那个区域的保形符号/图像，并且继续呈现在HUD的上部分的保形型图像。在一些实施方式中，当与真实世界特征的EVS或SVS图像链接时，此区域变为虚拟视窗，好似飞行员通过驾驶舱显示面板直接观看。在一些实施方式中，将此虚拟视窗与HUD视野通过HUD叠像镜的上部分组合，提供超过扩展的竖直视野的无缝的可视性和操作。
在一些实施方式中，向下扩展保形竖直视野有利地允许在更长时间段以及在特定低能见度条件下更早地将真实世界的线索呈现给飞行员。在一些实施方式中，使用显示系统的相对于地平面的倾斜范围有利地允许EVS传感器早于通过HUD和航空器挡风玻璃观看的相同的倾斜范围描绘真实世界的线索。
参考图1，提供了一种用于航空器11的显示系统10，显示系统10包括驾驶舱或航空器控制中心12。虽然关于航空器11讨论，但是根据一些实施方式，显示系统10可以在各种应用中使用，包括其它运输应用(例如地面车辆、海洋、太空等)、机器人或无人操作应用、医疗应用等。
航空器控制中心12包括HDD20、叠像镜24、叠像镜26、HDD 28和HDD 30。HDD20、28和30以及叠像镜24和26可以用于将信息提供给机组人员，从而增加可视范围并提高决策能力。叠像镜24和26与HUD系统和用于这样的系统的至少一个投射器相关联。在一些实施方式中，HDD28和30可为大区域格式的HDD。
在一些实施方式中，HDD 20、28和30以及叠像镜24和26提供与天气显示、气象雷达显示、通讯显示、飞行数据显示、发动机仪器信息显示、海图显示、地图显示、飞行计划显示、地形显示，或其他飞行仪表相关的图像。此外，在一些实施方式中，HDD 20、28和30以及叠像镜24和26包括合成的视觉系统(SVS)图像、增强的视觉系统(EVS)图像(例如，EFVS图像)、雷达图像、传感器图像或来源于SVS图象、雷达图像、传感器图像和EVS图像中的任何两个或多个的合并的图像。例如，在一些实施方式中，HDD 20、28和30以及叠像镜24和26构造为显示地形和/或天气信息的三维或立体图像。也可以提供地形和/或天气信息的其他视图(例如，平面图、水平视图、俯视图，或它们的组合)。
HDD 20、28和30以及叠像镜24和26可以使用任何各种显示技术实施，包括阴极射线管(CRT)、液晶显示器(LCD)、有机LED显示器、基于激光的，和其他显示技术。叠像镜24和26可以是用于提供保形图像的任何类型的设备，包括但不限于，波导叠像镜、反射型叠像镜、全息叠像镜等。
在一些实施方式中，显示系统10构造为提供一个或多个图像38、42、44、48、56、58、66和68。在一些实施方式中，HDD 28包括图像38和图像42。在一些实施方式中，叠像镜24上的图像56至少部分地提供在叠像镜24上的HDD28上的图像38之上。在一些实施方式中，图像58提供在叠像镜24上的图像56之上。图像38、56和58可提供为整合的视图。在一些实施方式中，图像42在HDD28上提供在图像38的右侧。在一些实施方式中，图像38通常从左至右具有与叠像镜24上的图像56和58相同的宽度。图像56和58可包括飞行仪器信息、罗盘、导航飞行和危险信息。HDD 30包括与叠像镜26上的图像66和68结合提供的图像38和42类似的图像44和48。
在一些实施方式中，图像56从遮光板32的顶表面31穿过HDD28的顶边缘71提供至HDD28的底边缘39并且与图像38重叠。在一些实施方式中，图像56扩展经过底边缘39。在一些实施方式中，叠像镜26从顶表面21穿过HDD30的顶边缘至HDD30的底边缘49相似地重叠HDD30。在一些实施方式中，在叠像镜26上的图像66重叠图像48。
在一些实施方式中，图像58是包括飞行控制符号和/或其他HUD符号，以及具有或不具有保形地提供在组合器24上的视觉系统图像或SVS图像的图像。在一些实施方式中，图像58不包括飞行控制符号和/或其他HUD符号，并且包括视觉系统图像和/或SVS图像。图像56包括以与图像58上的视觉系统图像或SVS图像连续的方式提供的视觉系统图像或SVS图像。在一些实施方式中，图像56具有通过遮光板32和HDD28与虚拟视图相关联的区域。在一些实施方式中，显示系统10提供SVS或EVS图像作为图像56，而不提供图像28。
HDD 20、28和30被提供在遮光板32的顶表面31的下方。在一些实施方式中，与图像56相关联的叠像镜24的部分从飞行员的眼睛位置73的视角扩展至遮光板32的顶表面31至HDD28的底边缘39。类似地，图像66从副驾驶的眼睛位置的视角扩展至遮光板的顶表面31至HDD30的底边缘49。在一些实施方式中，叠像镜24和26可以分别接触、抵靠、相邻或接附至HDD28和30的顶边缘71和69或底边缘39和49。在一些实施方式中，顶边缘71和69以及底边缘39和49包括壳体结构或其他边缘材料。
在一些实施方式中，叠像镜24和26至少部分设置在遮光板32的下方。在一些实施方式中，叠像镜24和26可以通过遮光板32中的孔、遮光板32中的凹陷设置或设置在遮光板32的前方。在一些实施方式中，叠像镜24和26构造为从驾驶舱眼睛参考点(例如，位置73)提供准直光束图像(例如，图像56、58、66和68)，以提供足够的真实世界视野。
在一些实施方式中，没有来自叠像镜24和26的图像的HDD 28和30提供与航空器11相关联的环境图像(例如，进场和着陆过程中)或提供与滑行跑道相关联的环境图像(例如在滑行时)。在一些实施方式中，叠像镜24和26中的一个用通过遮光板32的虚拟视窗显示扩展的视图，而另一个没有。在一些实施方式中，叠像镜24和26分别跨过HDD28和30的查看屏幕的至少部分显示环境的扩展的视图。在一些实施方式中，环境的扩展的视图来源于EVS数据、雷达数据、SVS数据。在一些实施方式中，当提供图像56和66时，图像38和40具有黑色或暗色的背景。在一些实施方式中，尽管图像56和58被描述为分开的图像，但在一些实施方式中图像56和58为单个整合的图像。在一些实施方式中，图像56和58可由相同电子器件和光学硬件提供。在一些实施方式中，图像66和68为单个整合的图像。在一些实施方式中，当在HDD28和30上提供图像38和48时，图像56和66具有清晰的背景。
参考图2，显示系统100可被用作图1中的显示系统10，用于将图像提供至HDD28和30以及叠像镜24和26中的任一个。在一些实施方式中，显示系统100包括处理器125，处理器125包括的HDD帧模块126、图像渲染器128、HUD帧模块136和图像渲染器138。在一些实施方式中，处理器125联接到用于叠像镜24和26的投射系统150并联接到HDD 28和30。在一些实施方式中，显示系统100包括存储器152，用于存储来自合成视觉系统(SVS)111的合成的视觉帧，以及存储器153，用于存储来自视觉系统(VS)112的视觉帧。在一些实施方式中，处理器125用于通过叠像镜24或通过叠像镜26提供遍布视野的保形图像。
显示系统100与VS 112(例如，增强的视觉系统)和SVS 111通讯。在一些实施方式中，SVS 111是可选的。在一些实施方式中，VS 112是可选的。在一些实施方式中，VS 112是由罗克韦尔柯林斯(Rockwell Collins)制造的增强的视觉系统(例如，EVS 3000系统)，或合适的替代。在一些实施方式中，SVS是由罗克韦尔柯林斯制造的合成的视觉系统(例如，Pro Line 21系统)，或合适的替代。
根据一些实施方式，SVS 111可以是任何电子系统或装置，用于提供外部场景形貌的计算机生成的图像。该图像可以来自航空器驾驶舱的来源于航空器姿态、高精度的导航解决方案，和地形、障碍和相关的人文特征的数据库的视角。根据一个实施方式，VS112可以是用于提供外部场景形貌的感测到的图像的任何电子系统或装置。在一个实施方式，VS112可以是红外或视觉相机。
图像渲染器128利用来自HDD帧模块126和SVS 111和VS 112的显示器信息，以在HDD28和30上提供图像。可以利用图像渲染器128来提供任何类型的飞行信息。在一些实施方式中，图像渲染器128提供SVS或EVS图像作为在HDD 28上的图像38，并提供飞行信息作为在HDD28上的图像42。在一些实施方式中，可以在显示器30上提供类似的图像。在一些实施方式中，图像渲染器128使用存储在存储器152和153中的一个或两者中的视频帧数据，以提供图像38和48(图1)或可使用于自SVS111或VS112的这样的数据。
HUD帧模块136将信息(例如，HUD符号)提供至图像渲染器138，用于将图像56和58提供在叠像镜24和/或将图像66和68提供在叠像镜26上。图像渲染器138使用于自SVS 111或VS 112的数据或来自存储器152或153的数据，以提供图像56和58。HUD帧模块136还可提供其他飞行信息。在一些实施方式中，HUD符号提供在图像58(图1)中，而没有SVS或VS图像。
在一些实施方式中，模块126和136以及渲染器128和138可以为硬件组件(例如，处理器)或执行配置为提供扩展的视野和其它图像的软件的硬件组件。在一些实施方式中，存储器152和153是帧存储器或其他存储设备。
处理器125可以是雷达系统、SVS 111、VS 112、用于HDD20、28和30的HDD显示器计算机或用于投射系统150的HUD计算机的一部分，或与雷达系统、SVS 111、VS 112、用于HDD20、28和30的HDD显示器计算机或用于投射系统150的HUD计算机集成。在一些实施方式中，处理器125为独立平台。在一些实施方式中，处理器125与用于VS112的摄像机集成。
显示系统100还可以包括数据链接接收器或数据总线，用于从一个或多个飞行管理计算机和其他航空电子设备接收信息，用于接收飞行阶段标志。飞行阶段标志可以用于自动地选择着陆、靠近或起飞处的扩展的视野格式。
在一些实施方式中，系统和方法可用于在叠像镜24和26中的一个上具有扩展的视野，并且将HDD28和30和在叠像镜24和26中的另一个上的其它信息相关联。例如，在着陆期间，飞行员可查看扩展的视角，包括在叠像镜24上的图像56(图1)中的合成的视觉或增强的视觉信息，而副驾驶查看在叠像镜26上的图像68中的HUD符号，以及作为在叠像镜26和HDD30上的图像66和图像48的其他非合成的视觉或增强的视觉信息。在一些实施方式中，显示系统10有利地使用图像56和图像66以提供非合成视觉或增强的视觉信息。
HDD 20、28和30可以是任何类型的显示器，包括阴极射线管、液晶显示器(LCD)面板、有机发光二极管(OLED)面板或其他显示器类型。投射系统150可以是用于将图像提供至叠像镜24和26的任何投射系统150。在一些实施方式中，投射系统150可以将准直光束提供至叠像镜24和26。叠像镜24和26可以是任何种类的叠像镜，包括但不限于：波导叠像镜、全息叠像镜、半镀银镜、反射叠像镜等。在一些实施方式中，投射系统150和叠像镜24和26基于光学波导技术使用平玻璃或塑料作为叠像镜波导。在一些实施方式中，叠像镜24和26包括衍射光栅或其它联接器，以使来自投射系统150中的LED照亮的微显示器的光弯曲。尽管图1中示出为安装在遮光板32内的叠像镜，但是也可以使用高架安装的HUD或叠像镜。
参考图3，在一些实施方式中，环境200通过与图像58关联的叠像镜的一部分是可查看的。在一些实施方式中，与图像56关联的叠像镜24的一部分示出由SVS或EVS数据生成的环境200以及飞行数据。在一些实施方式中，来自HDD28的图像38和叠像镜24上的图像是可查看的。由于遮光板32和HDD28的存在，飞行员不能通过与图像56相关联的叠像镜24的部分查看真实世界中的环境200。在一些实施方式中，叠像镜24上的图像56包括SVS图像或EVS图像。在一些实施方式中，SVS图像或EVS图像从顶表面31提供至HDD28的底边缘39，以提供整合的并且更加扩展的竖直视野。
参考图4A-4B，遮光板32包括凹陷74，用于接收叠像镜24。在一些实施方式中，投射系统150(图2)可以被设置在遮光板32的顶表面31的下方。在一些实施方式中，来自投射系统150的光可射入到在遮光板32之下的叠像镜24中。
在一些实施方式中，叠像镜24可以由薄塑料或玻璃(例如，1/4英寸)板制造，以减小凹陷74的尺寸。在一些实施方式中，叠像镜24是具有上叠像镜板82和下叠像镜板84的两片式叠像镜。在一些实施方式，光从投射系统150(例如，在图4A中一个投射系统150用于板82和83的每个)射入到下叠像镜板84的顶端和上叠像镜板82的底端中。在一些实施方式中，光射入到叠像镜82和84各自的边缘。在一些实施方式中，叠像镜板82和84不共面。在一些实施方式中，下叠像镜板84与HDD28的屏幕共面，并且上叠像镜板82关于下叠像镜板84成角度。在一些实施方式中，上叠像镜板82朝向飞行员成角度。叠像镜26可具有与叠像镜24相似的结构。
参考图5，在一些实施方式中，通过与图像58关联的叠像镜24的一部分能够查看到环境250。在一些实施方式中，与图像56相关的叠像镜24的一部分示出由SVS或EVS数据生成的环境250以及飞行数据。在一些实施方式中，当提供了图像56时，没有图像提供在HDD28上。
参考图6，进场的航空器300可通过叠像镜24(图1)查看在视准线304处的跑道308。在一些实施方式中，对于视准线304，飞行员不能查看诸如跑道灯312、314、316、318和320的跑道设施。然而，在一些实施方式中，使用与图像关联的虚拟视窗，沿着视准线302，飞行员能够查看更多的跑道设施，诸如跑道灯312、314和316。在一些实施方式中，通过叠像镜24使用真实世界视野，视准线304提供负15度的竖直视角并且视准线302通过叠像镜24使用与真实世界视野视野连续的图像38和56提供负35度的视角。
参考图7，使用具有扩展的竖直视野的显示系统10(图1)，航空器400具有视准线404。在进场时，航空器402不包括扩展的视野并且不能够看到与跑道308相关的视准线406上的跑道灯316和318，而航空器400查看视准线404上的跑道灯340。根据一些实施方式，航空器402具有扩展至负15度的竖直视野，并且使用显示系统10，航空器404具有扩展至负35度的竖直视野。
显示系统100可有利地增加的航空器400的决策高度。例如，如果该航空器400是在200英尺的检测高度，其EVS传感器的倾斜范围是约773英尺。由于增加的竖直视野，对于航空器400，该相同的倾斜范围可以检测在443英尺的检测高度处的跑道灯340。使用下式计算检测高度(DA)
DA＝SR*SinθVFOV
其中DA是检测高度，SR是倾斜范围并且θVFOV是竖直视野。因此，对于一个连续不断的能见度模糊的环境，VS 112(图2)具有在海拔高于常规系统243英尺检测进场灯(并且由此在进场时早于常规系统)的可能。从宽范围沿着航空器航线(例如，跑道308和跑道灯312、314、316、318、320和322或其他基础设施)查看真实世界队列的能力是有利的，并且由于由旋翼机执行的飞行动作的类型而特别有利于旋翼应用。
使用本文所描述的虚拟视窗操作可实现更宽的范围。虚拟视窗操作或扩展的视野操作可基于飞行阶段自动地接合或通过由飞行员控制的手动选择。
虽然详细的附图、具体示例、详细的算法，和给出的具体的构造描述了优选的和示范性的实施方式，但它们仅用作示例的目的。本文所揭示的发明概念不限于所示的具体形式。例如，该方法可以以任何各种步骤序列或根据任何各种数学公式来执行。示出并描述的硬件和软件配置可根据图像和处理设备的所选择的性能特征和物理特性而不同。例如，系统组件的类型及它们的相互连接可以不同。所描绘和描述的系统和方法不限于所公开的精确的细节和条件。流程图仅示出示例性操作。具体的数据类型和操作以非限制性的方式示出。此外，在不脱离如所附权利要求中阐明的本发明的范围的情况下，可以在示例性实施方式的设计、操作条件和布置中进行其它的替换、修改、改变和省略。
Claims (20)
1.一种显示系统包括：
波导，其至少部分地设置在遮光板的顶表面的上方，所述波导构造为允许查看外侧景象和来自图像源的第一信息，其中所述波导包括用于由用户查看所述外侧景象和所述第一信息的第一表面的至少第一部分，其中所述波导构造为设置为使得所述第一表面在所述用户和挡风玻璃之间；以及
下视显示器，其设置在所述遮光板的所述顶表面的下方，其中所述波导的所述第一表面包括底边缘，所述底边缘在所述遮光板的所述顶表面的下方扩展并且其中所述第一表面的至少第二部分在所述下视显示器的第二表面和所述用户之间，其中所述第二表面用于向所述用户提供来自所述下视显示器的第二信息，其中所述波导的所述第一表面是所述波导的顶边缘和所述波导的所述底边缘之间的连续查看表面，其中所述波导的所述顶边缘在所述挡风玻璃的一部分的前方，所述外侧景象通过所述挡风玻璃的所述部分是可查看的，并且所述连续查看表面的顶部在所述挡风玻璃的所述部分的前方，所述外侧景象通过所述挡风玻璃的所述部分是可查看的，并且所述连续查看表面的底部在所述下视显示器的前方或下方。
2.根据权利要求1所述的显示系统，其中所述第一表面的所述第二部分完全地覆盖所述第二表面。
3.根据权利要求1或2所述的显示系统，其中所述第一表面是平面。
4.根据权利要求1所述的显示系统，进一步包括：
处理电子器件，其构造为将包括第一图像数据和第二图像数据的所述第一信息提供至所述波导，其中所述第一图像数据为用于通过挡风玻璃查看的保形图像数据，并且所述第二图像数据为涉及眼睛位置的虚拟图像数据。
5.根据权利要求4所述的显示系统，其中与所述虚拟图像数据相关联的所述虚拟图像连续穿过所述波导的所述连续查看表面并且设置在所述波导的所述第一表面的所述第一部分和所述波导的所述第一表面的所述第二部分中。
6.根据权利要求4或5所述的显示系统，其中所述下视显示器为大区域显示器并且其中所述下视显示器的下视显示器图像具有匹配所述波导的宽度的宽度。
7.根据权利要求6所述的显示系统，其中所述波导包括第一板和第二板，所述第一板和所述第二板相对于彼此成角度，其中所述第一表面设置在所述第一板和所述第二板上。
8.根据权利要求7所述的显示系统，其中响应于飞行阶段提供第二图像数据。
9.根据权利要求1、2、4和5中的任一项所述的显示系统，其中所述波导包括第一板和第二板，所述第一板和所述第二板相对于彼此成角度，所述第二板具有与所述下视显示器的第二表面平行的第一表面，所述第一板和所述第二板包括衍射光栅，用于将光射入所述图像源或从所述图像源射出。
10.一种平视显示器，包括：
波导叠像镜，其包括顶边缘和底边缘，其中所述波导叠像镜构造为设置在遮光板的顶表面的上方和下方，所述遮光板具有底表面，其中所述波导叠像镜构造为在所述顶边缘和所述底边缘之间的第一表面的第一部分上提供图像，其中所述第一表面是从所述第一表面的顶部到所述第一表面的底部的连续查看表面，其中所述顶部在挡风玻璃的一部分的前方，环境通过所述挡风玻璃的所述部分是可查看的，其中所述第一表面在用户和所述挡风玻璃之间并且在所述遮光板的下方扩展，并且所述第一表面设置在所述遮光板的在所述遮光板的所述顶表面和所述遮光板的所述底表面之间的部分的至少一个边缘的前方，其中所述连续查看表面的顶部在所述挡风玻璃的所述部分的前方并且设置在所述遮光板的在所述遮光板的所述顶表面和所述遮光板的所述底表面之间的所述部分的前方，所述环境通过所述挡风玻璃的所述部分是可查看的。
11.根据权利要求10所述的平视显示器，其中所述波导叠像镜的所述底边缘邻近下视显示器的底边缘设置。
12.根据权利要求10或11所述的平视显示器，其中所述波导叠像镜提供合成的视觉图像或增强的视觉图像。
13.根据权利要求12所述的平视显示器，进一步包括：
处理电子器件，其构造为在所述下视显示器上提供与所述合成的视觉图像或所述增强的视觉图像连续的第二图像。
14.一种平视显示器，包括：
波导，其至少部分地设置在遮光板的顶表面的上方，所述波导构造为叠像镜以允许查看外侧景象和来自图像源的第一信息，其中所述波导包括用于由用户查看所述外侧景象和所述第一信息的第一表面的至少第一部分，其中所述波导构造为设置为使得所述第一表面在所述用户和挡风玻璃之间；
下视显示器，所述下视显示器在所述遮光板的所述顶表面的下方，其中所述波导的所述第一表面包括底边缘，所述底边缘在所述遮光板的所述顶表面的下方扩展并且其中所述第一表面的至少第二部分在所述下视显示器的第二表面和所述用户之间，其中所述第二表面用于向所述用户提供来自所述下视显示器的第二信息，其中所述波导的所述第一表面是所述波导的顶边缘和所述波导的所述底边缘之间的连续查看表面，其中所述波导的所述顶边缘在所述挡风玻璃的一部分的前方，所述外侧景象通过所述挡风玻璃的所述部分是可查看的，并且所述连续查看表面的顶部在所述挡风玻璃的所述部分的前方，所述外侧景象通过所述挡风玻璃的所述部分是可查看的，并且所述连续查看表面的底部在所述下视显示器的前方或下方；以及
投射器，所述投射器构造为提供在所述波导上的第一图像和在所述波导上的第二图像，并且在所述下视显示器的屏幕的前方，所述第二图像包括与通过所述下视显示器的环境视野连续的视觉图像或合成视觉图像。
15.根据权利要求14所述的平视显示器，其中所述第一图像包括与通过所述波导的所述环境视野保形地映射的另一个增强的视觉图像或另一个合成视觉图像。
16.根据权利要求14所述的平视显示器，其中所述第一图像包括与通过所述波导的所述环境视野保形地映射的飞行符号。
17.根据权利要求14所述的平视显示器，其中所述波导具有扩展至或扩展经过所述下视显示器的底边缘的底边缘。
18.根据权利要求14所述的平视显示器，其中所述波导的所述底边缘至少部分地在所述遮光板的下方。
19.根据权利要求14所述的平视显示器，其中所述下视显示器包括大区域显示器。
20.根据权利要求14所述的平视显示器，其中所述下视显示器提供第三图像，并且响应于飞行阶段提供所述第二图像。
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| US14/754,368 US10108010B2 (en) | 2015-06-29 | 2015-06-29 | System for and method of integrating head up displays and head down displays |
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| US20150167868A1 (en) | 2013-12-17 | 2015-06-18 | Scott Boncha | Maple sap vacuum collection systems with chew proof tubing |
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| US10048647B2 (en) | 2014-03-27 | 2018-08-14 | Microsoft Technology Licensing, Llc | Optical waveguide including spatially-varying volume hologram |
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2015
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2016
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|---|---|
| US10108010B2 (en) | 2018-10-23 |
| US20160377862A1 (en) | 2016-12-29 |
| CN106275467A (zh) | 2017-01-04 |
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