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Patent Agency Ranking
公开(公告)号：US11385073B2
公开(公告)日：2022-07-12
申请号：US16675726
申请日：2019-11-06
Applicant: THALES
Inventor： Marc Riedinger , Jean-Pierre Arethens , Philippe Chaix
Abstract: The invention relates to a method and a system for aircraft navigation along a predetermined airway, including an on-board navigation system supplying a positioning integrity of the aircraft during flight relative to said airway respecting an expected position precision performance level, and at least one on-board radio receiver on the aircraft suitable for communicating with at least one land-based radio beacon suitable for supplying a distance of the aircraft relative to said radio beacon. The system includes a module configured to obtain, from a current position of the aircraft and stored data, a tuple of radio beacons to be used, a module configured to obtain a distance measurement of the aircraft relative to each of the N radio beacons of said tuple, a module configured to compute an integrity position from distance measurements obtained by a predetermined computing method, and a module configured to use the computed integrity position as current integrity position.
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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：US10546504B2
公开(公告)日：2020-01-28
申请号：US15476486
申请日：2017-03-31
Applicant: THALES
Inventor： Marc Riedinger , Emmanuel Dewas , Alexandre Darbois
Abstract: A method for manipulating aircraft flight plan segments is provided. A result of an avionics calculation, such as a flight plan sequencing, is selected from among a plurality of results determined by a plurality of systems executed in parallel and placed in competition, each system communicating to at least part of the other systems conditions to be satisfied by the result of a calculation, the method comprises the steps of a given system from among the plurality of systems shares its own calculation result with at least one other system only if its own calculation result satisfies the conditions received from at least one other system. Developments describe various modalities of negotiation and/or selection of the results, the switch to independent and/or the deactivation of a system, voting and/or weighting mechanisms. Software and system aspects are described.
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公开(公告)号：US09418564B2
公开(公告)日：2016-08-16
申请号：US14625739
申请日：2015-02-19
Applicant: THALES
Inventor： Matthieu Claybrough , François Colonna , Marc Riedinger
CPC classification number: G08G5/045 , G05D1/0061 , G05D1/0607 , G05D1/0825 , G06F17/10 , G08G5/0021
Abstract: This method for determining an obstacle avoidance guidance law for an aircraft is implemented by a system for determining said guidance law. The aircraft comprises a collision avoidance system adapted to detect a collision risk with the obstacle and said determination system. This method comprises determining one or more set points from among flight path angle and speed set points, at least one set point depending on at least one vertical speed limit value, at least one set point comprising a vertical component in a vertical direction, each limit value being provided by the collision avoidance system following the detection of a collision risk with the obstacle; and computing the avoidance guidance law as a function of the determined set points. During the determination step, at least one determined set point comprises a longitudinal component in a longitudinal direction perpendicular to the vertical direction.
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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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