公开(公告)号：US20140330458A1

公开(公告)日：2014-11-06

申请号：US14268816

申请日：2014-05-02

Applicant: THALES

Inventor： Guillaume MEULLE ,  Thomas CAUSSAT ,  Arnaud BEAUFILS ,  Christophe PIERRE

IPC: G01P5/00 ,  B64C19/00

CPC classification number: G01P5/00 ,  B64C19/00

Abstract: A method and system for determining an airspeed of an aircraft, known as assisted aircraft, comprises: a) determining a position; b) measuring a ground speed; c) receiving a plurality of messages from a plurality of other assisting, aircraft, each message containing a first item of information, indicating a position of an assisting aircraft, and a second item of information, indicating a wind speed at the position; d) estimating a wind speed at the position of the assisted aircraft by interpolating the wind speed values at the positions of the assisting aircraft obtained in step c); and e) computing a true speed of the assisted aircraft by using the vector difference between its ground speed, measured in step b), and the wind speed estimated in step d). The method can check operation of an anemometric subsystem aboard an aircraft, to compensate for any malfunction and/or to enable automatic piloting.

Abstract translation: 一种称为辅助飞行器的用于确定飞机空速的方法和系统，包括：a）确定位置; b）测量地面速度; c）从多个其他辅助飞机接收多个消息，每个消息包含指示协助飞机的位置的第一信息项和指示该位置的风速的第二信息项; d）通过在步骤c）中获得的辅助飞行器的位置处插入风速值来估计辅助飞机位置处的风速; 以及e）通过使用在步骤b）中测量的地面速度与步骤d）中估计的风速之间的矢量差来计算辅助飞行器的真实速度。 该方法可以检查飞机上的气象学子系统的操作，以补偿任何故障和/或实现自动驾驶。

公开(公告)号：US20220254259A1

公开(公告)日：2022-08-11

申请号：US17629737

申请日：2020-07-23

Applicant: THALES

Inventor： Dorian MARTINEZ ,  Christophe PIERRE ,  Jori FERRUS ,  Philippe FRANCEZ

IPC: G08G5/00 ,  G06N3/04

Abstract: Devices and computer-implemented methods for analyzing aircraft trajectories, the method includes the steps of receiving data associated with a plurality of aircraft trajectories; breaking the trajectories down into a plurality of vectors, a vector comprising one or more sequences of enumerators; aligning multiple vectorized trajectories by shifting sequences of enumerators by one or more positions; and detecting one or more anomalies in one or more trajectories by unsupervised classification (e.g. DBSCAN). Developments describe the supervised determination of trajectory anomaly detection models, the use of density-based algorithms, the use of one or more neural networks and/or decision trees, one or more display steps, notably displaying root causes (explainable or understandable artificial intelligence), the processing of avionics data flows, etc. System (e.g. computing) and software aspects are described.

公开(公告)号：US20230017760A1

公开(公告)日：2023-01-19

申请号：US17861986

申请日：2022-07-11

Applicant: THALES

Inventor： Damien GOUBINAT ,  Christophe PIERRE ,  Guillaume GOUTTEBROZE

IPC: G08G5/00

Abstract: A method for determining a trajectory of an aircraft intended to fly over a field of operation with a view to performing an action on a target at a given time is provided. The method comprises a step of computing a set of sections between a starting point, intermediate points and the target. A first type of section has a rectilinear overall shape so as to limit the time spent by the aircraft in non-secure areas. A second type of section has a sinusoidal shape so as to allow a time reserve to adjust a position of the aircraft over the target at said given time with a view to performing the action.

公开(公告)号：US20220068148A1

公开(公告)日：2022-03-03

申请号：US17414902

申请日：2019-12-19

Applicant: THALES

Inventor： Michel ROGER ,  Hervé GOUTELARD ,  Christophe PIERRE

IPC: G08G5/00 ,  G01C21/20

Abstract: A computer-implemented method for optimizing a mission of an aircraft, the aircraft having a predefined flight plan between a starting point and an arrival point, the flight plan comprising a set of waypoints. The method comprises steps of: calculating, for the aircraft, a reference trajectory between the starting point and the arrival point, the reference trajectory comprising a set of segments and of intermediate points linking the segments of the reference trajectory; defining a search area in the reference trajectory between an initial position and a final position to be reached for this area; determining, in the search area, all possible shortcuts between the initial position and the final position, a shortcut being able to take into account any type of point, points of the flight plan and/or intermediate points of the reference trajectory; and identifying the combination of shortcuts corresponding to an optimum path according to an optimization criterion, the optimum path optimizing the mission of the aircraft in the search area.

公开(公告)号：US20180010916A1

公开(公告)日：2018-01-11

申请号：US15642238

申请日：2017-07-05

Applicant: THALES

Inventor： Michel ROGER ,  Christophe PIERRE ,  Hervé GOUTELARD

IPC: G01C21/20 ,  G01S19/49 ,  G01C23/00 ,  G08G5/00 ,  G01C21/16

CPC classification number: G01C21/20 ,  G01C21/16 ,  G01C23/00 ,  G01C23/005 ,  G01S19/48 ,  G01S19/49 ,  G05D1/02 ,  G08G5/003

Abstract: A method is provided for calculating the estimated navigation performance prediction for a trajectory associated with a list of segments of a flight plan. A method for displaying the navigation performance in a corridor trajectory so as to guarantee compliance with the navigation performance requirements while offering immediate viewing of the navigation latitude in a corridor is also provided.

公开(公告)号：US20180012503A1

公开(公告)日：2018-01-11

申请号：US15642248

申请日：2017-07-05

Applicant: THALES

Inventor： Michel ROGER ,  Christophe PIERRE ,  Hervé GOUTELARD

IPC: G08G5/00

CPC classification number: G08G5/0047 ,  G01C23/005 ,  G05D1/02 ,  G05D1/101 ,  G08G5/0021 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0052

Abstract: A method is provided for calculating the prediction of required navigation performance for a trajectory associated with a list of segments of a flight plan. A method is also provided for displaying the navigation performance as a corridor trajectory and adapted to guarantee compliance with the navigation performance requirements while offering immediate viewing of the navigation latitude in a corridor.

公开(公告)号：US20160210867A1

公开(公告)日：2016-07-21

申请号：US14992929

申请日：2016-01-11

Applicant: THALES

Inventor： Christophe PIERRE ,  Rémy AULETTO ,  Benoît DACRE-WRIGHT

IPC: G08G5/00 ,  G01W1/02 ,  G06F7/72 ,  G01C21/20

CPC classification number: G08G5/0039 ,  G01C21/20 ,  G01W1/02 ,  G06F7/724 ,  G08G5/0034 ,  G08G5/0052 ,  G08G5/0091

Abstract: A navigation aid method for an aircraft flying a reference trajectory between a point of departure and a point of arrival subject to a field of wind vectors comprises: decomposing the reference trajectory into a plurality of discrete waypoints Pi, loading meteorological data comprising the field of wind vectors, iterating the following steps N times, to generate an improved trajectory: for each waypoint Pi named current point, determining a reference plane, determining an orthonormal reference frame, determining a wind curl ((∇W)Pi), determining a sign of the projection of the wind curl on axis zi ((∇W)zi Pi), determining a direction of displacement from the current point Pi to a new current waypoint Pi′, determining a line of displacement, determining a displacement distance, determining the new current waypoint, determining a new trajectory, assigning the new waypoints Pi′ determined in the preceding iteration to the waypoints Pi for the next iteration.

Abstract translation: 一种用于飞行在出发点与受到风向量场的到达点之间的参考轨迹的飞行器的导航辅助方法包括：将参考轨迹分解为多个离散航路点Pi，加载包括风场的气象数据 向量，迭代以下步骤N次，以产生改进的轨迹：对于每个路点Pi命名当前点，确定参考平面，确定正交参考帧，确定风卷曲（（∇W）Pi），确定 确定从当前点Pi到新的当前路点Pi'的位移方向，确定位移线，确定位移距离，确定新的当前点Pi 确定一个新的轨迹，将上一次迭代中确定的新路点Pi'分配给下一次迭代的路点Pi。

公开(公告)号：US20160210866A1

公开(公告)日：2016-07-21

申请号：US14991704

申请日：2016-01-08

Applicant: THALES

Inventor： Christophe PIERRE ,  Rémy AULETTO ,  Benoît DACRE-WRIGHT

IPC: G08G5/00 ,  G01C21/00

Abstract: A navigational aid method of an aircraft, carried out by a flight management system, for comparing a reference trajectory of the aircraft subjected to a wind vector field with a new trajectory between the same starting and end points, respectively, the method comprises: determining the reference trajectory, determining the new trajectory, loading meteorological data, determining a directional surface, delimited by a directional closed curve, consisting of the new trajectory, from the starting point to the end point, closed by the opposite of the reference trajectory from the end point to the starting point, determining a wind curl on the basis of the wind vector field, determining a flow of the wind curl through the surface, a positive value of flow indicating that the new trajectory makes better use of the wind load, a negative value of flow indicating that the new trajectory makes less effective use of the wind load.

Abstract translation: 一种由飞行管理系统执行的用于将经过风矢量场的飞行器的参考轨迹与相同起点和终点之间的新轨迹进行比较的飞行器的导航辅助方法，包括：确定 参考轨迹，确定新的轨迹，加载气象数据，确定由方向性闭合曲线限定的方向表面，由新的轨迹组成，从起始点到终点，与从末端到参考轨迹的相反闭合 指出起点，根据风矢量场确定风卷曲，确定通过表面的卷曲流动，表示新轨迹更好地利用风荷载的流量正值，负值 流量值指示新的轨迹使得风力负荷的使用效果较差。

公开(公告)号：US20140012436A1

公开(公告)日：2014-01-09

申请号：US13934854

申请日：2013-07-03

Applicant: THALES

Inventor： Francois COULMEAU ,  Xavier BLANCHON ,  Christophe PIERRE

IPC: B64C19/00

CPC classification number: B64C19/00 ,  G05D1/0607 ,  G05D1/101 ,  G08G5/0021 ,  G08G5/0034

Abstract: A method for aiding navigation is provided, implemented in a flight management system, for the construction of a vertical trajectory of an aircraft following a predetermined lateral trajectory between a departure point and an arrival point; the departure point and arrival point furthermore being characterized by predefined altitudes, respectively Hd and Ha, and predefined speeds, respectively Vd and Va. The method comprises the steps of: selection of a transition manoeuvre in terms of altitude and speed from a predetermined list of manoeuvres; determination of a manoeuvre point PM on the lateral trajectory, of altitude Hd and of speed Vd, from which the transition manoeuvre must be initiated so as to allow the aircraft to reach at the arrival point the predefined speed Va and the predefined altitude Ha.

Abstract translation: 提供了一种在飞行管理系统中实现的用于辅助导航的方法，用于在出发点和到达点之间的预定横向轨迹之后构建飞机的垂直轨迹; 出发点和到达点的特征还在于预定的高度，分别为Hd和Ha，以及预定速度，分别为Vd和Va。该方法包括以下步骤：从高度和速度的预定列表中选择过渡机动 机动 确定侧向轨迹上的机动点PM，高度Hd和速度Vd，从其开始转换机动，以允许飞机在到达点到达预定速度Va和预定高度Ha。