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1.发明申请METHOD FOR PREDICTING A SHORT TERM FLIGHT PATH OF AN AIRCRAFT, COMPUTER PROGRAM PRODUCT, ASSOCIATED PREDICTION DEVICE, GUIDANCE METHOD, GUIDANCE SYSTEM AND AIRCRAFT 有权用于预测飞机短程飞行路径的方法，计算机程序产品，相关预测装置，指导方法，指导系统和飞机公开(公告)号：US20150364046A1
公开(公告)日：2015-12-17
申请号：US14739303
申请日：2015-06-15
Applicant: THALES
Inventor： Sylvain Lissajoux , Alexandre Badatcheff , Matthieu Claybrough
IPC: G08G5/00
CPC classification number: G08G5/0047 , G01C23/00 , G05D1/101
Abstract: A method for predicting a short-term flight path of an aircraft, a computer program product, an associated prediction device, a guidance method, and a guidance system of an aircraft are disclosed. In one aspect, the flight path of the aircraft is associated at each time moment with a vector including at least one component from among a position of the aircraft, attitudes of the aircraft and order 1 and 2 time derivatives of the position and attitudes. The short-term flight path is the flight path of the aircraft for a time period of up to 30 seconds from a computation time of the flight path. The method includes acquiring a control signal representative of a displacement of a primary control member of the aircraft and predicting, at a subsequent prediction time, at least one component of the short-term flight path of the aircraft. The prediction step can be carried out at the computation time.
Abstract translation: 公开了一种用于预测飞行器的短期飞行路径的方法，计算机程序产品，相关联的预测装置，引导方法和飞行器的引导系统。 在一个方面，飞行器的飞行路径在每个时刻与包括从飞机的位置，飞行器的姿态以及位置和态度的顺序1和2时间导数之间的至少一个分量的矢量相关联。 短程飞行路径是从飞行路线的计算时间起飞机飞行时间长达30秒的飞行路线。 该方法包括获取表示飞行器的主控制构件的位移的控制信号，并且在随后的预测时间预测飞行器的短期飞行路径的至少一个分量。 预测步骤可以在计算时进行。
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公开(公告)号：US10055999B2
公开(公告)日：2018-08-21
申请号：US15319489
申请日：2015-06-05
Applicant: THALES
Inventor： Sylvain Lissajoux , Eric Guillouet , Christophe Garnavault , Joël Bosson
CPC classification number: G08G5/0039 , G01C23/005 , G05D1/0061 , G05D1/0202 , G08G5/0052 , G08G5/045
Abstract: 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.
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公开(公告)号：US09045221B2
公开(公告)日：2015-06-02
申请号：US13679956
申请日：2012-11-16
Applicant: THALES
Inventor： Marc Riedinger , Sylvain Lissajoux , Anne-Sophie Bely
CPC classification number: B64C13/16 , G05D1/0204
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US09856032B2
公开(公告)日：2018-01-02
申请号：US14729509
申请日：2015-06-03
Applicant: THALES
Inventor： Sylvain Lissajoux , Matthieu Claybrough , Christophe Garnavault
Abstract: 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.
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5.发明授权Method and device for determining a control set point of an aircraft, associated computer program and aircraft 有权用于确定飞机，相关联的计算机程序和飞行器的控制设定点的方法和装置公开(公告)号：US09472107B2
公开(公告)日：2016-10-18
申请号：US14737362
申请日：2015-06-11
Applicant: THALES
Inventor： Sylvain Lissajoux , Bruno Aymeric , Thibaut Debard
CPC classification number: G08G5/0047 , G01C23/00 , G05D1/0202 , G05D1/0607 , G08G5/0021
Abstract: 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.
Abstract translation: 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。
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Patent Agency Ranking
公开(公告)号：US09377783B2
公开(公告)日：2016-06-28
申请号：US14592262
申请日：2015-01-08
Applicant: THALES
Inventor： Marc Riedinger , Sylvain Lissajoux
CPC classification number: G05D1/0676 , G01C23/00 , G08G5/0021 , G08G5/025
Abstract: 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.
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公开(公告)号：US11420730B2
公开(公告)日：2022-08-23
申请号：US16447533
申请日：2019-06-20
Applicant: THALES
Inventor： Sylvain Lissajoux , François Michel , Chris Deseure , Denis Bonnet
Abstract: 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.
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公开(公告)号：US10235891B2
公开(公告)日：2019-03-19
申请号：US15201258
申请日：2016-07-01
Applicant: THALES
Inventor： Matthieu Claybrough , Bruno Aymeric , Sylvain Lissajoux
Abstract: 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.
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公开(公告)号：US10036651B2
公开(公告)日：2018-07-31
申请号：US15176682
申请日：2016-06-08
Applicant: THALES
Inventor： Sylvain Lissajoux , Bruno Aymeric , Didier Poisson
CPC classification number: G01C23/005 , B64D43/02
Abstract: 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.
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公开(公告)号：US09824594B2
公开(公告)日：2017-11-21
申请号：US14739303
申请日：2015-06-15
Applicant: THALES
Inventor： Sylvain Lissajoux , Alexandre Badatcheff , Matthieu Claybrough
CPC classification number: G08G5/0047 , G01C23/00 , G05D1/101
Abstract: A method for predicting a short-term flight path of an aircraft, a computer program product, an associated prediction device, a guidance method, and a guidance system of an aircraft are disclosed. In one aspect, the flight path of the aircraft is associated at each time moment with a vector including at least one component from among a position of the aircraft, attitudes of the aircraft and order 1 and 2 time derivatives of the position and attitudes. The short-term flight path is the flight path of the aircraft for a time period of up to 30 seconds from a computation time of the flight path. The method includes acquiring a control signal representative of a displacement of a primary control member of the aircraft and predicting, at a subsequent prediction time, at least one component of the short-term flight path of the aircraft.
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