公开(公告)号：US6121899A

公开(公告)日：2000-09-19

申请号：US293285

申请日：1999-04-16

申请人： Ricky J. Theriault

发明人： Ricky J. Theriault

IPC分类号： G01C23/00 ,  G08B23/00

CPC分类号： G02B27/01 ,  G01C23/00 ,  G02B2027/0141

摘要： Aircraft tail strike protection is provided by displaying to a pilot tail strike warning symbols during takeoff and approach to landing. In a takeoff scenario, a pitch margin indicator symbol referenced to a boresight symbol provides a pilot with anticipatory information and an awareness of the pitch attitude margin before a tail strike incident. In an approach to landing scenario, a TAILSTRIKE warning annunciation is referenced to a flight path symbol and alerts the pilot of an impending tail strike incident. The symbols displayed during either scenario center on the pilot area of focus for each task. They give the pilot an awareness of an impending tail strike incident and necessary reaction time to avoid it.

摘要翻译： 通过在起飞和着陆时显示飞行员尾部警戒符号来提供飞机尾部防护。 在起飞场景中，参考视轴符号的俯仰边缘指示符符号为驾驶员提供预期信息，并且在尾部撞击事件之前提供俯仰姿态余量的意识。 在着陆场景的方法中，TAILSTRIKE警告通知被引用到飞行路径符号，并提醒飞行员即将发生的罢工事件。 在任一情景中显示的符号在每个任务的焦点的导频区域上。 他们让飞行员意识到即将发生的罢工事件和必要的反应时间来避免这种情况。

公开(公告)号：US08774986B1

公开(公告)日：2014-07-08

申请号：US11809190

申请日：2007-05-31

申请人： Ricky J. Theriault ,  Shuncan Chen

发明人： Ricky J. Theriault ,  Shuncan Chen

IPC分类号： G05D1/00 ,  G05D1/06 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00

CPC分类号： G05D1/0661 ,  G01C23/005 ,  G08G5/0021

摘要： The present invention is directed to providing takeoff rotation guidance. A takeoff rotation guidance indicator, including an aircraft reference symbol and a guidance cue, is displayed on a HUD (Head-up Display) of a HGS (Head-up Guidance System). The guidance cue is positioned in relation to the aircraft reference symbol based on a takeoff rotation pitch guidance and a takeoff rotation roll guidance. Thus, pitch and roll guidance information is simply communicated to the pilot of an aircraft. The takeoff rotation pitch guidance and the takeoff rotation roll guidance are calculated differently at different points during takeoff. In an alternative embodiment, the takeoff rotation guidance indicator includes a slip-skid symbol. The slip-skid symbol is positioned relative to aircraft reference symbol, but is displaced by the lateral acceleration of the aircraft. Thus, slip/skid guidance information is simply communicated to the pilot of an aircraft.

摘要翻译： 本发明涉及提供起飞旋转引导。 在HGS（平视向导系统）的HUD（平视显示））上显示包括飞行器参考符号和引导提示的起飞旋转引导指示器。 引导提示基于起飞旋转俯仰引导和起飞旋转滚动引导而相对于飞行器参考符号定位。 因此，俯仰和滚动引导信息被简单地传送到飞机的飞行员。 在起飞期间的不同点，起飞旋转俯仰引导和起飞旋转滚动引导被不同地计算。 在替代实施例中，起飞旋转引导指示器包括防滑符号。 防滑标志相对于飞行器参考符号定位，但是被飞行器的横向加速度所取代。 因此，滑移/滑行指导信息简单地传达给飞机的飞行员。

公开(公告)号：US08749890B1

公开(公告)日：2014-06-10

申请号：US13250994

申请日：2011-09-30

申请人： Robert B. Wood ,  Ricky J. Theriault ,  Duane P. M. Pond ,  Lincoln J. Burns ,  Robert D. Brown

发明人： Robert B. Wood ,  Ricky J. Theriault ,  Duane P. M. Pond ,  Lincoln J. Burns ,  Robert D. Brown

IPC分类号： G02B27/14

CPC分类号： G02B27/0149 ,  G02B5/18 ,  G02B5/30 ,  G02B6/34 ,  G02B27/0101 ,  G02B2027/015

摘要： A head up display includes an image source, collimating optics, and a combiner. The collimating optics are disposed between the combiner and the image source. The combiner receives collimated light from the collimating optics at an input and provides the collimated light to an output. The collimating light travels from the input to the output within the combiner by total internal refraction. An input diffraction grating is disposed in a first area and an output diffraction grating is disposed in a second area. The first area is smaller than the second area.

摘要翻译： 抬头显示器包括图像源，准直光学元件和组合器。 准直光学元件设置在组合器和图像源之间。 组合器在输入端从准直光学器件接收准直光，并将准直光提供给输出。 准直光通过总内部折射从组合器中的输入传播到输出。 输入衍射光栅设置在第一区域中，输出衍射光栅设置在第二区域中。 第一个区域小于第二个区域。