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公开(公告)号：US20090177400A1
公开(公告)日：2009-07-09
申请号：US12162467
申请日：2007-02-13
IPC分类号： G08G1/16
CPC分类号： G05D1/0646
摘要： The invention concerns a system (1) comprising guiding means (3) which, when guiding the aircraft along a low-altitude flight path, and upon a climb command, continue guiding the aircraft along the lateral path of said low-altitude flight path, and subject the aircraft in the vertical plane to a climb along a climb gradient which is not less than a maximum gradient of said flight path.
摘要翻译： 本发明涉及一种系统（1），其包括引导装置（3），当引导飞机沿着低空飞行路径，并且在爬升命令时，沿着所述低空飞行路径的横向路径继续引导飞行器， 并使飞机在垂直平面上沿着不小于所述飞行路径的最大坡度的爬升梯度爬升。
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公开(公告)号：US08751070B2
公开(公告)日：2014-06-10
申请号：US12162467
申请日：2007-02-13
IPC分类号： G05D1/06
CPC分类号： G05D1/0646
摘要： Disclosed is a method and system for aiding the piloting of an aircraft to climb to a safety altitude situated above an existing low-height flight trajectory comprised of a lateral trajectory and a vertical trajectory, in which the safety altitude is the altitude of the aircraft that avoids collision of the aircraft with surrounding terrain. The aircraft is guided along the existing lateral trajectory of the low-height flight trajectory in a horizontal plane; and the aircraft is brought to the safety altitude by subjecting the aircraft to a climb mode in a vertical plane, which causes the aircraft to climb according to a climb slope which is greater than or equal to a maximum slope according to the existing vertical trajectory of the low-height flight trajectory.
摘要翻译： 公开了一种用于帮助飞行员驾驶爬升到位于由横向轨迹和垂直轨迹组成的现有低高度飞行轨迹之上的安全高度的方法和系统，其中安全高度是飞行器的高度 避免飞机与周围地形的碰撞。 飞机在水平面内沿着低高度飞行轨迹的现有横向轨迹引导; 并且通过使飞机在垂直平面上进行爬升模式而将飞机带到安全高度，这使飞机根据现有的垂直轨迹的大于或等于最大坡度的爬坡而爬升 低高度的飞行轨迹。
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3.发明授权System for piloting an aircraft, at least for piloting the aircraft during an autonomous approach for the purpose of landing 有权至于在为了着陆目的而进行自主进近的飞机时，驾驶飞机的系统公开(公告)号：US09587960B2
公开(公告)日：2017-03-07
申请号：US12095250
申请日：2007-01-10
申请人： Vincent Markiton , Franck Laine , Edith Renault
发明人： Vincent Markiton , Franck Laine , Edith Renault
CPC分类号： G01C23/00 , G01S19/15 , G05D1/0676 , G08G5/025
摘要： A system for piloting an aircraft during an autonomous approach for the purpose of landing. The piloting system has a flight guidance computer that directly computes, with the aid of a position indication and of information characterizing a virtual approach axis, linear deviations. Another computer computes aircraft piloting instructions using the linear deviations.
摘要翻译： 一种在自主进场期间为着陆目的驾驶飞机的系统。 导引系统具有飞行引导计算机，借助于位置指示和表征虚拟进近轴的信息直接计算线性偏差。 另一台计算机使用线性偏差计算飞机驾驶指导。
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4.发明申请METHOD FOR MONITORING THE INTEGRITY OF AN AIRCRAFT POSITION COMPUTED ON BOARD 有权监控船上计算机飞行员位置的完整性的方法公开(公告)号：US20080046141A1
公开(公告)日：2008-02-21
申请号：US11841061
申请日：2007-08-20
申请人： Stephane Dattler , Vincent Markiton
发明人： Stephane Dattler , Vincent Markiton
CPC分类号： G01C21/20 , G01C21/165
摘要： A method for monitoring the integrity of an aircraft position computed on board including on-board means for monitoring the aircraft position that are able to detect common-mode failures. Dissimilar computing channels of the aircraft position are utilized, the dissimilar channels being on-board in the aircraft. Each aircraft position primary computing channel is supplemented by a dissimilar computing channel, which allows the coherence of the primary aircraft position, the position computed by the primary computing channels, to be verified. Mechanisms for verifying the reliability of the results from dissimilar computing channels are implemented to limit a loss of performance from the utilization of dissimilar computing channels, which are less performing than primary computing channels.
摘要翻译： 一种用于监测在船上计算的飞行器位置的完整性的方法，包括用于监视能够检测共模故障的飞行器位置的机载装置。 使用飞机位置的不相似的计算通道，飞机中不同的通道在板上。 每个飞机位置主计算通道由不同的计算通道补充，允许主飞机位置的相干性，由主计算通道计算的位置被验证。 用于验证来自不同计算通道的结果的可靠性的机制被实现以限制来自使用不同于主计算通道的不同计算通道的不同计算通道的性能损失。
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公开(公告)号：US07899586B2
公开(公告)日：2011-03-01
申请号：US12280126
申请日：2007-03-26
CPC分类号： G01C23/005
摘要： A guidance system includes a device to generate an alphanumeric identification characteristic, enabling identification of a data item which is used for a selected guidance mode of an aircraft. The system also includes a display unit which automatically shows the alphanumeric identification characteristic on a display screen.
摘要翻译： 引导系统包括用于产生字母数字识别特征的装置，使得能够识别用于飞行器的选定引导模式的数据项。 该系统还包括显示单元，其在显示屏幕上自动显示字母数字识别特性。
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6.发明申请Method and device for verifying a temperature value at a destination altitude of an aircraft 有权用于验证飞机目的地高度的温度值的方法和装置公开(公告)号：US20060056482A1
公开(公告)日：2006-03-16
申请号：US11046682
申请日：2005-02-01
CPC分类号： G01K13/028 , G01C23/00 , G01K1/04 , G01K7/42 , G01K13/02
摘要： The device comprises a means for measuring a dynamic temperature on the outside of the aircraft, a means for determining a static temperature around the aircraft, using said dynamic temperature, a means for determining, using said static temperature and a thermodynamic equation, a second temperature value corresponding to an estimated temperature at said destination altitude, a means for determining the difference between said first and second temperature values, and a means for emitting a warning signal when said difference is greater than a predetermined value.
摘要翻译： 该装置包括用于测量飞行器外部的动态温度的装置，使用所述动态温度确定飞机周围静态温度的装置，用于确定使用所述静态温度和热力学方程式的第二温度 对应于所述目的地高度处的估计温度的值，用于确定所述第一和第二温度值之间的差的装置，以及当所述差大于预定值时发出警告信号的装置。
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公开(公告)号：US20090043433A1
公开(公告)日：2009-02-12
申请号：US12280126
申请日：2007-03-26
CPC分类号： G01C23/005
摘要： The guidance system (1) comprises means (2, 6) for generating an alphanumeric identification characteristic, making it possible to identify a data item which must be used for a selected guidance mode of the aircraft, and display means (10) which automatically shows this alphanumeric identification characteristic on a display screen (12).
摘要翻译： 引导系统（1）包括用于产生字母数字识别特征的装置（2,6），使得可以识别必须用于飞行器的选定引导模式的数据项目，以及自动显示的显示装置（10） 这种字母数字识别特征在显示屏幕（12）上。
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8.发明申请Method and Device For Assisting the Flying of an Aircraft During an Autonomous Approach 有权在自主方法下协助飞机飞行的方法和装置公开(公告)号：US20080269966A1
公开(公告)日：2008-10-30
申请号：US12095229
申请日：2007-01-10
IPC分类号： G05D1/10
CPC分类号： G01C23/00 , G05D1/0676 , G08G5/025
摘要： The invention relates to a method and a device for assisting the flying of an aircraft, said method and device being used to determine an approach path and comprising a guidance system for helping to guide the aircraft along this approach path. The inventive method and device define a main approach path (AI) and a corrected approach path that has an extra vertical margin (ΔH) related to the ground over which the craft is flying as compared with a main approach path representing a category 1 precision approach. Said guiding system guides the aircraft following the corrected approach path.
摘要翻译： 本发明涉及一种用于辅助飞行器飞行的方法和装置，所述方法和装置用于确定进近路径，并且包括用于帮助沿着该进近路径引导飞行器的引导系统。 本发明的方法和装置定义了与代表1类精密方法的主进场路线相比，主飞行路线（AI）和修正的进场路径具有与飞行器所飞行的地面相关的额外的垂直边距（DeltaH） 。 所述引导系统引导飞机遵循校正的进近路径。
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9.发明申请METHOD AND DEVICE FOR DETERMINING A DECISION HEIGHT DURING AN AUTONOMOUS APPROACH OF AN AIRCRAFT 有权用于确定飞机自动方法中的决定高度的方法和装置公开(公告)号：US20080150785A1
公开(公告)日：2008-06-26
申请号：US11831671
申请日：2007-07-31
申请人： Vincent Markiton , Stephane Dattler
发明人： Vincent Markiton , Stephane Dattler
IPC分类号： G01S13/00
CPC分类号： G05D1/0676
摘要： The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.
摘要翻译： 本发明的主题是帮助飞行员（3）的驾驶的方法，其旨在在为了着陆的目的在对着陆跑道（P）的自主进场期间有助于飞行员的驾驶，所述飞行器包括在 至少一个定位装置（10,12），其中：a）确定所述飞机在跑道上的估计时刻; b）至少在该到达时刻确定飞机的所述定位装置的性能的预测; 和c）基于所述定位装置的所述性能和所述方法的特征，确定对应于该到达时刻的至少一个最小决定高度（Hmin），在此之上，保护飞机免受与 当它被自动引导到对应于所述方法的接近轴线（A）时的环境。 本发明还涉及一种用于实现该方法的装置。
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10.发明授权Method and device for verifying a temperature value at a destination altitude of an aircraft 有权用于验证飞机目的地高度的温度值的方法和装置公开(公告)号：US07334939B2
公开(公告)日：2008-02-26
申请号：US11046682
申请日：2005-02-01
CPC分类号： G01K13/028 , G01C23/00 , G01K1/04 , G01K7/42 , G01K13/02
摘要： The device comprises a means for measuring a dynamic temperature on the outside of the aircraft, a means for determining a static temperature around the aircraft, using said dynamic temperature, a means for determining, using said static temperature and a thermodynamic equation, a second temperature value corresponding to an estimated temperature at said destination altitude, a means for determining the difference between said first and second temperature values, and a means for emitting a warning signal when said difference is greater than a predetermined value.
摘要翻译： 该装置包括用于测量飞行器外部的动态温度的装置，使用所述动态温度确定飞机周围静态温度的装置，用于确定使用所述静态温度和热力学方程式的第二温度 对应于所述目的地高度处的估计温度的值，用于确定所述第一和第二温度值之间的差的装置，以及当所述差大于预定值时发出警告信号的装置。
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