公开(公告)号：US20150198954A1

公开(公告)日：2015-07-16

申请号：US14592262

申请日：2015-01-08

申请人： THALES

发明人： Marc RIEDINGER ,  Sylvain LISSAJOUX

IPC分类号： G05D1/06 ,  G08G5/00

CPC分类号： G05D1/0676 ,  G01C23/00 ,  G08G5/0021 ,  G08G5/025

摘要： A method for securing a ground speed used for guiding landing of an aircraft by determining a ground speed of the aircraft and determining a landing guidance instruction based on the determined ground speed. Next, estimate the vertical speed of the aircraft and limit, during guidance along a glide path having a descent angle, the determined ground speed as a function of the estimated vertical speed. The guidance instruction is based on the limited ground speed. Further, measure the height of the aircraft and compare it with a threshold height. If the measured height is greater than the threshold height, limit the ground speed as a function of acceleration measurements. If the measured height is below the threshold height, limiting the ground speed as a function of the estimated vertical speed and as a function of acceleration measurements of the aircraft taken once threshold height has been crossed.

摘要翻译： 一种用于通过确定飞行器的地面速度来确定用于引导飞行器着陆的地面速度的方法，并且基于所确定的地面速度确定着陆引导指令。 接下来，估计飞行器的垂直速度，并且在沿具有下降角的滑行路径的引导期间限制所确定的地面速度作为估计垂直速度的函数。 指导指导是基于有限的地面速度。 此外，测量飞机的高度并将其与阈值高度进行比较。 如果测量的高度大于阈值高度，则将地面速度限制为加速度测量的函数。 如果测量的高度低于阈值高度，则将地面速度限制为估计的垂直速度的函数，并且作为临时高度已经越过的飞机所采用的加速度测量的函数。

公开(公告)号：US20230205204A1

公开(公告)日：2023-06-29

申请号：US17923488

申请日：2021-05-03

申请人： THALES

发明人： Laurent LALUQUE ,  Sylvain LISSAJOUX ,  Patrick GOUHIER ,  Bruno CAPELLE

IPC分类号： G05D1/00 ,  B64U10/00

CPC分类号： G05D1/0055 ,  G05D1/0088 ,  B64U10/00 ,  B64U2201/10

摘要： Method for controlling an unmanned aircraft piloted by a fully autonomous control system including a first decision module and a simplex piloting control module including a high-performance controller, a high-safety controller and a second decision module, the high-performance and high-safety controllers determining piloting commands for the robot-aircraft, according to which: —as long as a set of conditions is verified, implementation by the first decision module of a nominal piloting mode with delivery to the output of the automatic control system of the piloting commands delivered to the output of the simplex piloting control module; —otherwise, switching to an emergency piloting mode, an emergency piloting command is delivered to the output of the automatic control system for execution by the robot-aircraft, the first decision module preventing the delivery to the output of the automatic control system of the piloting commands delivered to the output of the simplex module.

公开(公告)号：US20190389565A1

公开(公告)日：2019-12-26

申请号：US16447533

申请日：2019-06-20

申请人： THALES

发明人： Sylvain LISSAJOUX ,  François MICHEL ,  Chris DESEURE ,  Denis BONNET

IPC分类号： B64C19/02 ,  B64D45/00 ,  G08G5/00 ,  B64C13/02

摘要： Methods and systems for assisting the piloting of an aircraft are provided. The system includes at least one avionics type system and at least one non-avionics type system. The method includes steps involving receiving avionics type data associated with a flying context of the aircraft; forwarding the avionics type data to a non-avionics type system or computer; determining, in the non-avionics computer, one or more adjustment recommendations for equipment based on the received flying context and/or on predetermined data; displaying one or more recommendations. Various developments are described, in particular the conditions for requesting and/or computing recommendations (e.g. ongoing adjustment of the avionics, similar previous configuration, etc.), the selection and the categorization of recommendations, the handling of adjustment data for the avionics, etc. Software aspects are described.

公开(公告)号：US20170323571A1

公开(公告)日：2017-11-09

申请号：US15319489

申请日：2015-06-05

申请人： THALES

发明人： Sylvain LISSAJOUX ,  Eric GUILLOUET ,  Christophe GARNAVAULT ,  Joël BOSSON

IPC分类号： G08G5/00 ,  G01C23/00 ,  G05D1/02

CPC分类号： G08G5/0039 ,  G01C23/005 ,  G05D1/0061 ,  G05D1/0202 ,  G08G5/0052 ,  G08G5/045

摘要： This method makes it possible to generate a resulting setpoint trajectory of an aircraft, a guiding system controlling the trajectory of the aircraft relative to the resulting setpoint trajectory.The generating method is implemented by an electronic device and comprises selecting at least one mode from among several operating modes, acquiring a setpoint trajectory prepared by a flight management system, obtaining an alternative setpoint trajectory from an element from among a module for computing a trajectory and an external generating system, and generating the resulting setpoint trajectory, which includes one or several segments of the alternative setpoint trajectory for the period of time corresponding to the selection of another mode.

公开(公告)号：US20150360767A1

公开(公告)日：2015-12-17

申请号：US14740023

申请日：2015-06-15

申请人： THALES

发明人： Sylvain LISSAJOUX ,  Eric Guillouet ,  Thibaut Debard

IPC分类号： B64C13/22 ,  B64C13/04 ,  B64D31/04 ,  B64C13/18 ,  B64D31/06

CPC分类号： B64C13/22 ,  B64C13/04 ,  B64C13/18 ,  B64D31/00 ,  B64D31/04 ,  B64D31/06 ,  G05D1/0061

摘要： A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated.

摘要翻译： 公开了一种用于从飞行控制设定点，马达控制设定点和飞行器引导设定点，相关的计算机程序产品和飞行器产生至少一个设定点的方法和装置。 在一个方面，该方法包括相对于至少一个对应的主控制构件获取机械性能，并从一个或多个主要设定点和一个或多个辅助设定点计算至少一个设定点。 该方法还包括基于在对应的主控制构件获取的机械特性，在其中产生一个或多个主要设定点的第一模式和第二模式之间产生所计算的设定点和切换中的至少一个 其中生成一个或多个次要设定点。

公开(公告)号：US20130206922A1

公开(公告)日：2013-08-15

申请号：US13679956

申请日：2012-11-16

申请人： Thales

发明人： Marc RIEDINGER ,  Sylvain LISSAJOUX ,  Anne-Sophie BELY

IPC分类号： B64C13/16

CPC分类号： B64C13/16 ,  G05D1/0204

摘要： Guidance for an aircraft correcting a trajectory deviation due to wind computes a roll command during trajectory alignment according to imposed alignment passing through a determined point, via a current angular divergence between a line through the point and aircraft and direction of alignment and of a current estimated ground speed of the aircraft with respect to a frame of reference. The current estimated ground speed is computed via a current air speed and stored wind speed. The stored wind speed is obtained via at least one wind speed computed via a first value of a first speed equal to the speed of the said aircraft with respect to a frame of reference originating from a satellite navigation system and a second value of a second speed equal to the air speed. The first and second value are simultaneously accounted earlier than or at the instant at the alignment phase.

摘要翻译： 用于校正由于风引起的轨迹偏差的飞行器的指导根据通过确定点的施加的对准，经由点与飞行器的线和对准方向之间的当前角度发散以及估计的当前电流在轨迹对准期间计算滚动命令 相对于参考框架的飞机的地面速度。 当前估计的地面速度是通过当前的空气速度和存储的风速来计算的。 所存储的风速通过至少一个风速获得，所述至少一个风速是通过相对于源自卫星导航系统的参考系的第一速度的第一速度等于所述飞机的速度而计算的，第二值是第二速度 等于空气速度。 第一个和第二个值同时考虑在比较阶段的时间或在定位阶段的瞬间。

公开(公告)号：US20170004713A1

公开(公告)日：2017-01-05

申请号：US15201258

申请日：2016-07-01

申请人： THALES

发明人： Matthieu CLAYBROUGH ,  Bruno AYMERIC ,  Sylvain LISSAJOUX

IPC分类号： G08G5/00 ,  G02B27/01

CPC分类号： G08G5/0065 ,  G01C21/20 ,  G01C23/00 ,  G02B27/0101 ,  G02B2027/0141 ,  G02B2027/0183

摘要： A method and device for displaying vertical constraints of an aircraft, an associated program produce and aircraft are disclosed. In one aspect, the vertical constrains are displayed on a display device of the aircraft, the display device being part of an aircraft piloting system, the method being implemented by an electronic device that is part of the aircraft piloting system. The method includes acquiring at least one vertical constraint of the aircraft, computing a representative slope value associated with the vertical constraint, and displaying a symbol depicting the vertical constraint at the representative slope value associated with the vertical constraint on a slope scale

摘要翻译： 公开了一种用于显示飞行器，相关程序产品和飞行器的垂直约束的方法和装置。 在一个方面，垂直约束显示在飞行器的显示装置上，显示装置是飞行器驾驶系统的一部分，该方法由作为飞机驾驶系统一部分的电子装置实现。 该方法包括获取飞行器的至少一个垂直约束，计算与垂直约束相关联的代表性斜率值，并且以与斜率尺度上的垂直约束相关联的代表性斜率值显示描绘垂直约束的符号

公开(公告)号：US20160363459A1

公开(公告)日：2016-12-15

申请号：US15176682

申请日：2016-06-08

申请人： THALES

发明人： Sylvain LISSAJOUX ,  Bruno AYMERIC ,  Didier POISSON

IPC分类号： G01C23/00 ,  B64D43/02

CPC分类号： G01C23/005 ,  B64D43/02

摘要： This electronic device for aiding with the piloting of an aircraft includes: an acquisition module, configured to acquire a current value of the roll angle of the aircraft; a computing module configured to compute a roll angle limit corresponding to a beginning of stalling of the aircraft; and a display module, configured to display, on a screen, a first symbol indicating a current orientation of the aircraft. The computing module is configured to compute at least one roll margin, each roll margin depending on a corresponding roll angle limit and the current value of the roll angle, and the display module is configured, when the display condition is verified, to display, on the screen, at least one second symbol positioned relative to the first symbol, the deviation between each second symbol and the first symbol representing a respective roll margin.

摘要翻译： 用于辅助飞机驾驶的该电子设备包括：获取模块，被配置为获取飞行器的滚动角度的当前值; 计算模块，被配置为计算对应于飞行器停止开始的滚转角度限制; 以及显示模块，被配置为在屏幕上显示指示飞行器的当前方向的第一符号。 计算模块被配置为计算至少一个滚动边缘，每个滚动边距取决于相应的滚动角度限制和滚动角度的当前值，并且当显示条件被验证时，显示模块被配置为显示在 所述屏幕，相对于所述第一符号定位的至少一个第二符号，每个第二符号与所述第一符号之间的偏差表示相应的卷边距。

公开(公告)号：US20150364045A1

公开(公告)日：2015-12-17

申请号：US14737362

申请日：2015-06-11

申请人： THALES

发明人： Sylvain LISSAJOUX ,  Bruno Aymeric ,  Thibaut Debard

IPC分类号： G08G5/00

CPC分类号： G08G5/0047 ,  G01C23/00 ,  G05D1/0202 ,  G05D1/0607 ,  G08G5/0021

摘要： A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value.

摘要翻译： 公开了一种用于确定飞行器，相关联的计算机程序和飞机的控制设定点的方法和装置。 一方面，该方法包括以飞机的斜率值的形式计算性能量表，该性能量表包括斜率特征值，斜率特征值与相应的性能特征值相关联。 该方法还包括以相对于性能量表的斜率值的形式获取引导设定点并显示所获取的引导设定点。 该方法还包括确定与以斜率值形式显示的引导设定点相关联的斜率特征值，以及计算飞行器控制设定点，控制设定点是相对于与所确定的斜率特性对应的性能特征值计算的 值。

公开(公告)号：US20150360789A1

公开(公告)日：2015-12-17

申请号：US14729509

申请日：2015-06-03

申请人： THALES

发明人： Sylvain LISSAJOUX ,  Matthieu Claybrough ,  Christophe Garnavault

IPC分类号： B64D31/06 ,  B64D33/04 ,  B64C25/44

CPC分类号： B64D31/06 ,  B64C25/44 ,  B64D33/04 ,  G01C23/00

摘要： A method and device for controlling at least one actuator control system of an aircraft, an associated computer program product and aircraft are disclosed. In one aspect, the method includes determining a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, calculating a first control command signal to be sent to an engine control system in order to obtain the variation in thrust, and transmitting the first control command signal to the engine control system. The controlled variable can be an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector and the set point can be an acceleration set point along the direction.

摘要翻译： 公开了一种用于控制飞机，相关联的计算机程序产品和飞行器的至少一个致动器控制系统的方法和装置。 一方面，该方法包括确定用于控制与飞行器相对于设定点的变量的飞行器的推力变化，计算要发送到发动机控制系统的第一控制命令信号，以获得 推力，并将第一控制命令信号发送到发动机控制系统。 控制变量可以是沿着空气速度矢量和地面速度矢量之间的速度矢量所采取的方向的加速度，并且设定点可以是沿该方向的加速度设定点。