公开(公告)号：US20150356874A1

公开(公告)日：2015-12-10

申请号：US14730088

申请日：2015-06-03

Applicant: THALES

Inventor： Vincent SAVARIT ,  François HOOFD ,  Emmanuel DEWAS

IPC: G08G5/00

CPC classification number: G08G5/0034 ,  G05D1/0202 ,  G08G5/0039 ,  G08G5/0047

Abstract: A method determines the optimal turn direction of an aircraft among two directions, right and left, following a lateral trajectory to join an arrival straight charted by an angle of arrival, based on a departure point and angle of departure defining a departure straight oriented along movement of the aircraft, the direction defined by a respectively positive or negative optimal turn sign, comprising: determining a conventional departure sign of the departure point; determining a centred value of an angle of change of course equal to the difference between the angle of arrival and angle of departure referred back between −180° and +180°, the centred value exhibiting a logical sign corresponding to the centred value sign of the angle of change of course; determining the sign of the optimal turn based on comparison between the departure sign and the logical sign, the sign of the optimal turn defining optimal turn direction.

Abstract translation: 一种方法基于出发点和离开角度定义沿着运动定向的出发直线，确定飞机在左右两个方向之间的最佳转向方向，沿着横向轨迹连接到达到达的直线的方向 所述飞行器的方向由相应的正或负最佳转向标志限定，包括：确定出发点的常规出发标志; 确定变化角度的中心值当然等于-180°至+ 180°之间所指的到达角和出发角之间的差异，该中心值表现出对应于中心值符号的逻辑符号 变化的角度; 根据出发符号和逻辑符号之间的比较确定最佳转弯的符号，最佳转向的符号确定最佳转向方向。

公开(公告)号：US20220282976A1

公开(公告)日：2022-09-08

申请号：US17637301

申请日：2020-08-21

Applicant: THALES

Inventor： Johan BOYER ,  Emmanuel DEWAS ,  Geoffrey DURAND

IPC: G01C21/20 ,  G01C21/00

Abstract: This method for determining a flight distance over a discontinuity segment comprises the steps of determining an altitude of entry to said trajectory portion and an altitude of exit from said trajectory portion, discretization of an altitude interval delimited by the altitude of entry and the altitude of exit into a plurality of elementary intervals, each elementary interval being defined using an elementary step and, for each elementary interval, determining an elementary slope of the aircraft.
This method further comprises a step of determining the flight distance over the discontinuity segment as a function of a direct distance between the framing segments, the elementary slopes, the elementary steps and the total extent of said trajectory portion.

公开(公告)号：US20150276411A1

公开(公告)日：2015-10-01

申请号：US14671943

申请日：2015-03-27

Applicant: THALES

Inventor： Vincent SAVARIT ,  Emmanuel DEWAS ,  Yohann COMBES

IPC: G01C21/00

CPC classification number: G01C21/00 ,  G05D1/0202 ,  G08G5/0013 ,  G08G5/065

Abstract: A method of computing an aircraft trajectory, between a departure point and an arrival point, comprises: loading the departure point and a departure angle; determining two waypoints; loading the arrival point and an arrival angle; determining two departure circles of respectively left and right type, which are tangent to the oriented departure straight line respectively on the left and on the right, and passing respectively through the waypoint of left type and through waypoint of right type; determining two arrival circles of respectively left and right type which are tangent to the oriented arrival straight line respectively on its left and on its right and passing through the arrival point; determining a plurality of continuous geometric lateral trajectories comprising an initial portion comprising a portion of a departure circle, a final portion equal to a portion of an arrival circle, and an intermediate portion.

Abstract translation: 一种在出发点和到达点之间计算飞行器轨迹的方法包括：装载出发点和出发角; 确定两个航点; 装载到达点和到达角度; 分别确定左右两侧分别与定向出发直线相切的两个离开圈，分别通过左侧航路点和右侧航点; 确定分别在左侧和右侧通过到达点的与定向到达直线相切的两个左右类型的到达圆; 确定多个连续的几何横向轨迹，其包括初始部分，所述初始部分包括出发圆的一部分，等于到达圆的一部分的最终部分和中间部分。

公开(公告)号：US20130317740A1

公开(公告)日：2013-11-28

申请号：US13902634

申请日：2013-05-24

Applicant: THALES

Inventor： Emmanuel DEWAS ,  Pierre-Alain DUBOURG ,  Loic CHARLES

IPC: G01C21/00

CPC classification number: G01C21/00 ,  G01C21/005 ,  G01C21/20 ,  G08G5/0052

Abstract: A flight management system of an aircraft is provided allowing notably the calculation of a trajectory over the terrestrial globe. The calculation of a trajectory is carried out with respect to a true North, true North being a navigation term referring to the direction of the geographical North pole with respect to a given position. When the current or estimated position of the aircraft is level with the pole, it then becomes impossible to define true North, true North being defined in all the directions or in no direction, depending on the calculation facilities used. The flight management system makes it possible to use a single calculation procedure whatever the current position or the position to be reached of the aircraft on the terrestrial globe.

Abstract translation: 提供飞机的飞行管理系统，可以显着地计算地球仪上的轨迹。 相对于真正的北方进行轨迹的计算，真正的北方是指相对于给定位置的地理北极方向的导航术语。 当飞机的当前位置或估计的位置与极点平齐时，根据所使用的计算设备，无法定义真正的北部，正方向或全向无定义。 飞行管理系统使得可以使用单个计算程序，无论当前位置或地面上飞机的位置如何。

公开(公告)号：US20230274649A1

公开(公告)日：2023-08-31

申请号：US18014730

申请日：2021-07-20

Applicant: THALES

Inventor： Emmanuel DEWAS ,  Geoffrey DURAND

IPC: G08G5/00

CPC classification number: G08G5/0021 ,  G08G5/003 ,  G08G5/0047

Abstract: The present invention relates to a device and a method for assisting aircraft guidance. The method for assisting aircraft guidance is operated by a computation platform for aircraft and comprises steps:



of acquisition of state variables characterizing an aircraft in flight, of environment variables characterizing the environment of the aircraft and of trajectory variables characterizing a reference trajectory of the aircraft;
of calculation of a predicted real trajectory for an upcoming change of direction of the aircraft, based on said state variables, on said environment variables and on said reference trajectory variables;
of determination of conformity to determine if the predicted real trajectory which is calculated conforms or does not conform to the reference trajectory; and
of configuration of a trajectory deviation alert, when the predicted real trajectory does not conform to the reference trajectory.

公开(公告)号：US20150005992A1

公开(公告)日：2015-01-01

申请号：US14316666

申请日：2014-06-26

Applicant: THALES

Inventor： François COULMEAU ,  Jérôme SACLE ,  Emmanuel DEWAS

IPC: G08G5/02

CPC classification number: G08G5/02 ,  G05D1/0676 ,  G08G5/0039 ,  G08G5/025

Abstract: A method for calculating a flight plan used by a flight management system of an aircraft in a runway approach phase comprises: loading an initial procedure ending at a first end point not corresponding to a threshold of the runway and a first associated missed approach procedure; determining an additional procedure and a second associated missed approach procedure; concatenating the initial procedure and the additional procedure in order to generate a continuous concatenated flight plan comprising the initial procedure, the first missed approach procedure, the additional procedure and the second missed approach procedure; loading the concatenated flight plan into an active flight plan; selecting a second procedure from a set comprising the first missed approach procedure and the additional procedure; activating the selected second procedure.

Abstract translation: 用于计算在跑道接近阶段中的飞行器的飞行管理系统使用的飞行计划的方法包括：加载在不对应于跑道的阈值的第一终点处终止的初始过程和第一相关联的错过的接近程序; 确定附加过程和第二相关联的错过接近程序; 连接初始过程和附加过程，以便产生包括初始过程，第一次错过接近程序，附加过程和第二次错过接近程序的连续级联飞行计划; 将连接的飞行计划加载为主动飞行计划; 从包括所述第一错过的过程和附加过程的集合中选择第二过程; 激活所选择的第二过程。

公开(公告)号：US20140012500A1

公开(公告)日：2014-01-09

申请号：US13936034

申请日：2013-07-05

Applicant: THALES

Inventor： Vincent SAVARIT ,  Emmanuel DEWAS ,  François COULMEAU

IPC: G01C21/00

CPC classification number: G01C21/00 ,  G08G5/0021 ,  G08G5/0039

Abstract: In the field of the definition of a flight plan for an aircraft, a method is provided for determining an offset lateral trajectory from an initial lateral trajectory comprising a set of initial waypoints. The initial lateral trajectory and the offset lateral trajectory have two junction points in common, namely a point of entry and a point of exit. At least one of the junction points is distinct from the initial waypoints and from the current position of the aircraft. This first junction point can notably be defined so that the flight duration or the flight distance between the first and second junction points corresponds to a defined value.

Abstract translation: 在飞行器飞行计划的定义领域中，提供了一种用于从包括一组初始航路点的初始横向轨迹确定偏移横向轨迹的方法。 初始侧向轨迹和偏移侧向轨迹具有共同的两个连接点，即入口点和出口点。 至少有一个交汇点不同于初始航点和飞机的当前位置。 可以明显地定义该第一连接点，使得第一和第二连接点之间的飞行持续时间或飞行距离对应于定义的值。

公开(公告)号：US20130238174A1

公开(公告)日：2013-09-12

申请号：US13789595

申请日：2013-03-07

Applicant: THALES

Inventor： Emmanuel DEWAS ,  Vincent SAVARIT ,  Francois COULMEAU

IPC: G05D1/06

CPC classification number: G05D1/0676 ,  G05D1/101

Abstract: In the field of the calculation of the approach trajectory of an aircraft, and relating to a method for determining a corrected lateral approach trajectory as a function of the energy to be reabsorbed before the landing, and also to a flight management system making it possible to determine the corrected lateral trajectory, a method comprises: determining an energy of the aircraft Eaero upon crossing the runway threshold on the basis of a predetermined approach trajectory and of a current state of the aircraft, said state comprising at least one current altitude, a current ground speed and a mass of the aircraft; comparing the energy Eaero with a predetermined maximum energy Emax, and when the energy Eaero is greater than the energy Emax, determining the corrected lateral approach trajectory as a function of the difference between the energy of the aircraft Eaero and the maximum energy Emax.

Abstract translation: 在计算飞行器的进场轨迹的领域中，涉及一种用于确定作为在着陆之前要被吸收的能量的函数的校正的横向进场轨迹的方法，并且还涉及一种飞行管理系统， 确定校正的横向轨迹，方法包括：基于预定的进场轨迹和飞行器的当前状态，在越过跑道阈值时确定飞机Eaero的能量，所述状态包括至少一个当前高度，当前高度 地面速度和飞机的质量; 将能量Eaero与预定的最大能量Emax进行比较，并且当能量Eaero大于能量Emax时，确定作为飞行器Eaero的能量与最大能量Emax之间的差异的函数的校正的横向进场轨迹。

公开(公告)号：US20220282975A1

公开(公告)日：2022-09-08

申请号：US17637299

申请日：2020-08-20

Applicant: THALES

Inventor： Johan BOYER ,  Emmanuel DEWAS ,  Geoffrey DURAND

IPC: G01C21/20 ,  G01C21/00

Abstract: This method comprises a step of determining a reference profile along a lateral trajectory precalculated comprising searching, in the precalculated lateral trajectory, at least one segment of discontinuity comprising a lateral discontinuity, determining a required distance corresponding to a minimum flight distance between the two segments bordering the discontinuity segment and integrating each required distance into the reference profile.
This method further comprises a step of determining, on the basis of the reference profile, vertical predictions relating to a vertical trajectory of the aircraft and a step of determining, on the basis of the vertical predictions, a resulting lateral trajectory comprising, for each discontinuity segment, determining a substitution segment connecting the two corresponding bordering segments in a continuous manner.

公开(公告)号：US20170301244A1

公开(公告)日：2017-10-19

申请号：US15476486

申请日：2017-03-31

Applicant: THALES

Inventor： Marc RIEDINGER ,  Emmanuel DEWAS ,  Alexandre DARBOIS

IPC: G08G5/00

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.