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21. 发明授权

US09092976B2 Systems and methods for providing runway-entry awareness and alerting 有权
标题翻译：提供跑道入口意识和警报的系统和方法
公开(公告)号：US09092976B2
公开(公告)日：2015-07-28
申请号：US13616782
申请日：2012-09-14
申请人： Ratan Khatwa , Chris Hamblin
发明人： Ratan Khatwa , Chris Hamblin
IPC分类号： G01C21/00 , G08G5/00 , B64F1/20 , G08G5/02 , G08G5/06 , G05D1/06
CPC分类号： G08G5/0065 , G05D1/0653 , G08G5/0013 , G08G5/0021 , G08G5/025 , G08G5/065
摘要： Systems and methods for providing runway entry awareness and alerting. An exemplary system includes a processing device that determines pilot intent based on one of a manual runway selection, automatic runway selection, aircraft information received from one or more sensors or received clearance information; receives at least one of aircraft position or motion information; determines if a no access condition exists based on the received information, the stored airport information and the determined pilot intent; and generates at least one of a hold-short gate still image or animation, if the no access condition exists.
摘要翻译：提供跑道入口意识和警报的系统和方法。示例性系统包括：处理装置，其基于从一个或多个传感器接收的手动跑道选择，自动跑道选择，飞行器信息或接收到的间隙信息中的一个来确定飞行员意图; 接收飞机位置或运动信息中的至少一个; 基于接收到的信息，所存储的机场信息和确定的导频意图来确定是否存在无访问条件; 并且如果存在无访问条件，则生成保持短门静止图像或动画中的至少一个。

22. 发明申请

US20110121140A1 AUTOMATIC TAKEOFF APPARATUS FOR AIRCRAFT, AUTOMATIC LANDING APPARATUS FOR AIRCRAFT, AUTOMATIC TAKEOFF AND LANDING APPARATUS FOR AIRCRAFT, AUTOMATIC TAKEOFF METHOD FOR AIRCRAFT, AUTOMATIC LANDING METHOD FOR AIRCRAFT AND AUTOMATIC TAKEOFF AND LANDING METHOD FOR AIRCRAFT 有权
标题翻译：用于飞机的自动起落架装置，用于飞机的自动起落装置，用于飞机的自动起落架和装置，用于飞机的自动起落方法，用于飞机的自动着陆方法和用于航空器的自动起落方法
公开(公告)号：US20110121140A1
公开(公告)日：2011-05-26
申请号：US12954244
申请日：2010-11-24
申请人： Akihiro Yamane , Mitsuru Kono , Takahiro Kumamoto
发明人： Akihiro Yamane , Mitsuru Kono , Takahiro Kumamoto
IPC分类号： G05D1/00
CPC分类号： G05D1/0653 , B64C13/18
摘要： An automatic takeoff apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a takeoff command inputting section; and a control device for controlling a propulsion device and an control surface of the aircraft, wherein the control device includes: a takeoff run control section for realizing a takeoff run by controlling the propulsion device to provide a maximum output and by controlling the control surface to maintain the attitude angle and the traveling direction constant, in response to the takeoff command; a rotation control section for controlling the control surface to rotate when the airspeed exceeds a predetermined speed; and an ascending flight control section for controlling the propulsion device and the control surface to perform an ascending flight up to a target altitude with a predetermined speed maintained, when the altitude exceeds a predetermined altitude.
摘要翻译：用于飞行器的自动起飞装置包括：高度传感器; 空速传感器; 姿态角传感器; 方向传感器; 起飞指令输入部; 以及用于控制所述飞行器的推进装置和控制面的控制装置，其中，所述控制装置包括：起飞行程控制部，其通过控制所述推进装置来实现起飞运行，以提供最大输出，并且通过将所述控制面控制到响应于起飞指令，保持姿态角和行驶方向恒定; 旋转控制部，其在空速超过预定速度时控制所述控制面旋转; 以及升降飞行控制部分，用于当所述高度超过预定高度时，控制所述推进装置和所述控制表面以保持预定速度执行上升飞行直到目标高度。

23. 发明授权

US06761336B2 Aircraft tailstrike avoidance system 有权
标题翻译：飞机尾巴回避系统
公开(公告)号：US06761336B2
公开(公告)日：2004-07-13
申请号：US10043401
申请日：2002-01-08
申请人： Wendi M. DeWitt , David P. Eggold , Monte R. Evans , Mithra M. K. V. Sankrithi , Stephen L. Wells
发明人： Wendi M. DeWitt , David P. Eggold , Monte R. Evans , Mithra M. K. V. Sankrithi , Stephen L. Wells
IPC分类号： G05D108
CPC分类号： G05D1/0808 , B64C13/503 , B64D45/04 , G05D1/0653
摘要： An aircraft flight control system is provided for reducing the likelihood of an aircraft tailstrike. The flight control system includes a pitch command provided to a pitch control device for altering the aircraft's pitch attitude. The improvement is a system of altering the pitch command to avoid an aircraft tailstrike. The improvement includes determining a current tailskid closure rate and a current tail height; comparing the current tailskid closure rate with a threshold closure rate to determine an excess closure rate amount; and adding an incremental nose-down pitch command with the pitch command to avoid a potential aircraft tailstrike. The threshold closure rate is dependent upon the current tailskid height. The incremental nose-down pitch command is calculated as a function of the excess closure rate amount. An alternative embodiment is provided in which the current height is compared with a threshold height (that is a function of the current tailskid closure rate) to determine an excess height amount. The excess height is then used to form an incremental nose-down pitch command. Another embodiment is described using both height and rate thresholds to calculate the incremental nose-down pitch command. Alternative arrangements may be used in which other non-derivative and derivative values are used, e.g., pitch angle margin and pitch rate.
摘要翻译：提供飞机飞行控制系统，以减少飞机尾停的可能性。飞行控制系统包括提供给俯仰控制装置的俯仰指令，用于改变飞机的俯仰姿态。改进是改变俯仰命令以避免飞机尾迹的系统。改进包括确定当前尾部关闭速率和当前尾部高度; 将当前tailskid关闭率与阈值关闭率进行比较以确定过多关闭率; 并用俯仰指令添加增量的下降俯仰指令，以避免潜在的飞机尾迹。阈值关闭率取决于当前的tailskid高度。根据过度闭合率量的函数计算增量下降音调指令。提供了一个替代实施例，其中将当前高度与阈值高度（即当前尾部关闭速率的函数）进行比较以确定过高高度量。然后使用多余的高度来形成增量的向下俯仰间距指令。使用高度和速率阈值来描述另一个实施例来计算增量的向下俯仰俯仰指令。可以使用替代布置，其中使用其他非导数和导数值，例如俯仰角余量和俯仰速率。

24. 发明授权

US3588477A Actual slope computer 失效
标题翻译：实际斜坡计算机
公开(公告)号：US3588477A
公开(公告)日：1971-06-28
申请号：US3588477D
申请日：1968-04-30
申请人： CSF
发明人： LAMI RENE , COLOMBET GEORGES
IPC分类号： G01S1/02 , G01S13/91 , G05D1/06 , G06G7/78 , G06F15/50 , G06G7/70
CPC分类号： G06G7/78 , G01S1/02 , G01S13/913 , G05D1/0653 , G05D1/0676
摘要： AN ACTUAL SLOPE COMPUTING SYSTEM FOR INDICATING, AT ANY MOMENT, ON BOARD AN AIRCRAFT, THE DEVIATION BETWEEN THE ACTUAL FLIGHT PATH OF THE AIRCRAFT AND A PRESELECTED NONHORIZONTAL NONLINEAR PATH INCLUDING A FIRST LINEAR PRESELECTED PATH AND A LAST LINEAR PRESELECTED PATH, SAID SYSTEM COMPRISING A COMPUTING UNIT FOR COMPUTING AT ANY MOMENT THE VALUE OF THE ALTITUDE H NECESSARY FOR SAID AIRCRAFT TO FOLLOW A NONHORIZONTAL LINEAR PATH, AS A FUNCTION OF GIVEN PARAMETERS OF SAID FIRST PATH, AND A MEMORY AND LOGIC CIRCUITS FOR FEEDING TO SAID COMPUTING UNIT, AT MOMENTS DETERMINED AS A FUNCTION OF THE POSITION OF SAID AIRCRAFT, SUCCESSIVELY THE PARAMETERS OF SAID FIRST PATH, OF SUCCESSIVE PROGRAMMED LINEAR PORTIONS OF SAID PRESELECTED PATH, AND OF SAID LAST PATH, SAID PROGRAMMED LINEAR PORTIONS BEING PROGRAMMED FOR INSURING A PROGRESSIVE MERGER OF THIS FIRST PATH SAID LAST PATH.

25. 发明授权

US3359793A Aircraft instruments 失效
公开(公告)号：US3359793A
公开(公告)日：1967-12-26
申请号：US41436864
申请日：1964-11-27
申请人： SMITH & SONS LTD S
发明人： KENDALL ERIC R , NEWPORT STANLEY B
IPC分类号： G05D1/06
CPC分类号： G05D1/0653 , G05D1/0661

26. 发明授权

US2249836A Remote control mechanism 失效
公开(公告)号：US2249836A
公开(公告)日：1941-07-22
申请号：US32531540
申请日：1940-03-22
申请人： LEAR AVIA INC
发明人： LEAR WILLIAM P
IPC分类号： G05D1/06 , H01Q1/30
CPC分类号： H01Q1/30 , G05D1/0653

27. 发明申请

WO2015142481A1 SHORT LANDING WARNING 审中-公开
标题翻译：短路警告
公开(公告)号：WO2015142481A1
公开(公告)日：2015-09-24
申请号：PCT/US2015/017145
申请日：2015-02-23
申请人： THE BOEING COMPANY
发明人： HENDERSON, Mark H.
IPC分类号： B64D45/04 , G05D1/06
CPC分类号： B64D45/04 , B64D45/08 , G05D1/0607 , G05D1/0653 , G05D1/0676 , G08G5/0047 , G08G5/04 , G08G5/045
摘要： A method can include determining that an aircraft is on approach to a runway. The method can include determining a flight path vector (FPV) location of the aircraft based at least in part on a projected landing location with respect to the runway and determining a current airspeed of the aircraft. The method can also include performing at least one of the following: issuing a landing short alert to a pilot of the aircraft if the FPV location is at or before the runway threshold, issuing an airspeed caution alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is below a landing short envelope, and determining not to issue an alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is at or above the landing short envelope.
摘要翻译：一种方法可以包括确定飞机正在接近跑道。该方法可以包括至少部分地基于相对于跑道的预计着陆位置来确定飞机的飞行路径向量（FPV）位置，并确定飞行器的当前空速。该方法还可以包括执行以下中的至少一个：如果FPV位置在跑道阈值之前或之前，向飞机的飞行员发出着陆短警报，如果FPV位置在跑道阈值之间，则发出空速警告警报目标跑道位置以及当前空速是否低于着陆短信号，并且如果FPV位置在跑道阈值和目标跑道位置之间以及当前空速是否在着陆短路之上或之上，则确定不发出警报信封。

28. 发明申请

WO02045048A1 LANDING AND NAVIGATING SYSTEM WITH VIRTUAL REPRESENTATION OF THE IMMEDIATE SURROUNDINGS 审中-公开
标题翻译：具有虚拟代表性的陆地和航行系统
公开(公告)号：WO02045048A1
公开(公告)日：2002-06-06
申请号：PCT/CH2001/000686
申请日：2001-11-26
IPC分类号： G01C23/00 , G01S7/20 , G01S13/86 , G05D1/10 , G08G5/02 , G08G5/00 , G01S7/51 , G01S17/89 , G01S17/93 , G08G5/04
CPC分类号： G08G5/0021 , G01C23/005 , G01S7/20 , G01S13/86 , G05D1/0653 , G08G5/0065 , G08G5/025
摘要： The invention concerns a landing system enabling navigation and landing by supplying a virtual image of the immediate surroundings, obstacles, other vehicles, ground navigating stations (VOR, NDB, and the like), standard reporting points, landing and take-off procedures with standard instruments and the trajectory to follow.
摘要翻译：本发明涉及通过提供直接环境，障碍物，其他车辆，地面导航站（VOR，NDB等），标准报告点，具有标准的着陆和起飞程序的虚拟图像来实现导航和着陆的着陆系统仪器和跟踪的轨迹。

29. 发明申请

WO1996006008A1 AIRCRAFT NAVIGATION SYSTEM 审中-公开
标题翻译：飞机导航系统
公开(公告)号：WO1996006008A1
公开(公告)日：1996-02-29
申请号：PCT/RU1994000196
申请日：1994-08-19
申请人： CONSILIOR LUFTFAHRTTECHNOLOGIE GMBH , SAFYAN, Dmitry Anatolievich
发明人： CONSILIOR LUFTFAHRTTECHNOLOGIE GMBH
IPC分类号： B64F01/18
CPC分类号： G05D1/0653 , B64F1/18
摘要： The proposed aircraft navigation system has a ground-air signal link which is independent of the radio link and synchronises the picture frequency of the television camera (12) in the on-board equipment with the frequency of the UV-visible and infrared flashing beacons (3) in the ground equipment; the purpose of this is to improve the precision with which take-off and landing taxiing corridors are formed and to increase the useful lifetimes of the beacons and reduce the cost of operating them. In the on-board equipment, a variable focal length objective (9) of a TV camera which can be moved by an automatically controlled drive monitors signals from the flashing beacons (3); these signals are processed in the selection unit (14) and in the unit (15) which calculates the parameters of the aircrafts motion. A synchroniser (13) co-ordinates the visual and numerical data on the aircraft's position in the take-off/landing space which reach the data display unit (16) for displaying the information needed by the objective drive control unit (11) and the external automatic course correction system.
摘要翻译：所提出的飞行器导航系统具有独立于无线电链路的地面空中信号链路，并与车载设备中的电视摄像机（12）的图像频率与UV-可见和红外闪烁信标的频率同步（ 3）在地面设备中; 其目的是提高形成起降滑行走廊的精度，增加信标的使用寿命，降低运行成本。在车载设备中，可通过自动控制的驱动器移动的电视摄像机的可变焦距物镜（9）监视闪光信标（3）的信号; 这些信号在选择单元（14）和计算飞机运动参数的单元（15）中进行处理。同步器（13）协调飞机在到达数据显示单元（16）的起飞/着陆空间中的位置上的视觉和数值数据，以显示目标驱动控制单元（11）所需的信息和外部自动校正系统。

30. 发明专利

JP6093539B2 飛行機の騒音低減手順のための方法有权
标题翻译：过程用于飞机噪声降低过程
公开(公告)号：JP6093539B2
公开(公告)日：2017-03-08
申请号：JP2012227562
申请日：2012-10-15
申请人：ゼネラル・エレクトリック・カンパニイ
发明人：マイケル・ジョン・ベッカー , ホアキム・カール・ウルフ・ホッチワース , ショーン・エドワード・フラネリー
IPC分类号： G08G5/00 , B64C13/18
CPC分类号： G05D1/0653 , G08G5/006

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