公开(公告)号：US20200174502A1

公开(公告)日：2020-06-04

申请号：US16700790

申请日：2019-12-02

Applicant: THALES

Inventor： Michel ROGER ,  Adrien DE JAUREGUIBERRY ,  Guy DEKER

IPC: G05D1/10 ,  B64C39/02

Abstract: Automatic flight information determination device for automatically determining flight control information for an accompanying mobile machine accompanying a leader mobile machine, the said device being adapted for collecting the data pertaining to location of the leader mobile machine from among the data pertaining to the actual location derived from measurements relating to the current location of the leader mobile machine and the pertaining to the current trajectory of the accompanying mobile machine, and of determining, o the basis of the said location data collected, the information items for piloting the accompanying mobile machine as a function of a set of at least two values to be adhered to with respect to the location defined by the data collected, the said values to be adhered to being representative of the values included among: a minimum vertical/flight level separation value, a minimum longitudinal/along track separation value, and a minimum lateral/between tracks separation value.

公开(公告)号：US20170323573A1

公开(公告)日：2017-11-09

申请号：US15492693

申请日：2017-04-20

Applicant: THALES

Inventor： Guy DECKER ,  Michel ROGER

IPC: G08G5/00 ,  B64D31/02

CPC classification number: G08G5/0047 ,  B64D31/02 ,  G01C21/00 ,  G01C21/20 ,  G05D1/0607 ,  G08G5/003 ,  G08G5/0034 ,  G08G5/0039

Abstract: A method, computer program and system are provided for calculating in an automatic manner a trajectory for rejoining a reference vertical profile of an aircraft. A reference vertical profile comprises a set of vertical constraints, and a method comprises a step of selecting an altitude constraint to be complied with, a step of calculating a vertical-profile prediction making it possible to comply with the constraint, a step of validating the vertical-profile prediction, if the vertical-profile prediction is validated, a step of applying the vertical-profile prediction, otherwise a step of determining the existence of a following altitude constraint to be complied with; if a following altitude constraint exists: a step of selecting a following altitude constraint to be complied with; a return to the step of detecting non-compliance with an altitude constraint; otherwise, a step of applying an exit procedure.

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：US20140244077A1

公开(公告)日：2014-08-28

申请号：US14186681

申请日：2014-02-21

Applicant: THALES

Inventor： Enrique LASO-LEON ,  Amandine AUDOUY ,  Guillaume MEULLE ,  Michel ROGER

IPC: B64C19/00

CPC classification number: B64C19/00 ,  G01C21/20 ,  G05D1/0005 ,  G05D1/0607 ,  G08G5/0021 ,  G08G5/0034

Abstract: A method for creating a vertical trajectory profile of an aircraft by optimization of a criterion representative of a flight cost, comprises: performing a first iterative computation of a profile free of altitude constraints as long as a condition dependent on the criterion is not reached, replacing each free level of the constraint-free profile with a permitted level so as to generate an initial constrained profile comprising a plurality of permitted levels, and, for each level, an altitude change point and a plurality of speeds, and performing a second iterative computation of a profile in which the altitude levels to be reached remain constant, equal to the initial permitted levels of the initial constrained profile, as long as a condition dependent on the criterion is not reached.

Abstract translation: 一种用于通过优化表示飞行成本的标准来创建飞行器的垂直轨迹曲线的方法包括：只要没有达到取决于标准的条件，就执行没有高度约束的轮廓的第一迭代计算，替换 每个具有允许级别的无约束简档的空闲级别，以便产生包括多个允许级别的初始约束简档，并且对于每个级别，对于每个级别，高度变化点和多个速度，以及执行第二迭代计算 其中要达到的高度水平保持恒定，等于初始约束曲线的初始允许水平，只要不达到取决于准则的条件即可。

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：US20150262490A1

公开(公告)日：2015-09-17

申请号：US14627645

申请日：2015-02-20

Applicant: THALES

Inventor： Guy DEKER ,  Michel ROGER ,  Bruno AYMERIC

IPC: G08G5/00

CPC classification number: G08G5/0039 ,  G05D1/101 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0047 ,  G08G5/0052 ,  G08G5/0095

Abstract: A method and system, for flight management of an aircraft flying on a trajectory shifted with respect to a flight plan comprising a plurality of constrained waypoints, comprises a step of determining and displaying at least one point of the trajectory, termed decision point, beyond which the aircraft can no longer rejoin a constrained waypoint of the flight plan by determining a point of intersection between the trajectory and a rejoining trajectory steering towards the selected constrained waypoint, the rejoining trajectory complying with at least one predefined criterion.

Abstract translation: 一种用于对在相对于包括多个受限航路点的飞行计划移动的轨迹上飞行的飞行器的飞行管理的方法和系统包括确定和显示所述轨迹的至少一个点（被称为决策点）的步骤，超过该点 飞行器不能再通过确定轨迹与朝向选定的受限航路点转向的重合轨迹之间的交点，重新加入飞行计划的约束航点，该重合轨迹符合至少一个预定准则。

公开(公告)号：US20240363011A1

公开(公告)日：2024-10-31

申请号：US18578668

申请日：2022-07-22

Applicant: THALES

Inventor： Michel ROGER ,  Pascal RIVES ,  Jérôme SACLE ,  Guy DEKER

IPC: G08G5/00

CPC classification number: G08G5/0039 ,  G08G5/0017

Abstract: A method for managing speed constraints of a flight plan of an aircraft, the method includes the following steps: identifying a current flight phase, determining CAS speed profile, the speed profile establishing a behavior of the aircraft with respect to a speed setpoint, determining a Mach speed profile, the Mach speed profile establishing a behavior of the aircraft with respect to a Mach setpoint, the Mach setpoint being a speed setpoint transcribed into an equivalent Mach number, determining a Cross-Over altitude, the Cross-Over altitude being an altitude of transition from an automatic control of the aircraft according to the CAS speed profile to an automatic control according to the Mach speed profile, determining an end-of-applicability criterion of the speed profile and of the Mach speed profile.

公开(公告)号：US20180300895A1

公开(公告)日：2018-10-18

申请号：US15952312

申请日：2018-04-13

Applicant: THALES

Inventor： Clément Victor HUBER ,  Michel ROGER

IPC: G06T7/70 ,  G06T7/20 ,  G05D1/00 ,  B64C39/02

Abstract: The invention relates to a method (34) for tracking a target (10), using an electronic target tracking system (14) on board a drone (12), the method (34) comprising at least determining (40) a movement trajectory of the drone (12), the trajectory comprising a plurality of successive orbits respectively centered on a plurality of successive positions (C) of the target (10), the orbit radius being able to vary, from one successive orbit to another, based on at least one element belonging to the group comprising: at least one datum (50) associated with the movement performance of the drone (12), the current position of the target (10), a predetermined elevation angle (ζ) of the drone relative to the target (10), the current altitude of the drone (12) relative to the target (10).

公开(公告)号：US20160180716A1

公开(公告)日：2016-06-23

申请号：US14978812

申请日：2015-12-22

Applicant: THALES

Inventor： Michel ROGER ,  Mathieu ORVAIN

IPC: G08G5/00 ,  G05D1/00

CPC classification number: G08G5/0034 ,  G05D1/0088 ,  G08G5/0021 ,  G08G5/0047 ,  G08G5/0052

Abstract: A method of flight management and guidance of an aircraft executed by a flight management system FMS comprises the steps of: generating a reference trajectory, generating a short-term trajectory, periodically transmitting the short-term trajectory, generating a long-term trajectory, formatting the segments of the long-term trajectory, periodically transmitting the long-term trajectory, storing the long-term trajectory transmitted, testing the validity of the FMS sub-assembly, when the FMS sub-assembly is valid: identifying, by the autonomous guidance module, the active segment of the short-term trajectory, generating, by the autonomous guidance module, a first flight guidance order on the basis of the active segment of the short-term trajectory; when the FMS sub-assembly is not valid: identifying, by the autonomous guidance module, the active segment of the stored trajectory, generating, by the autonomous guidance module, a second flight guidance order on the basis of the active segment of the stored trajectory.

Abstract translation: 由飞行管理系统FMS执行的飞行管理和指导飞行管理方法包括以下步骤：产生参考轨迹，产生短期轨迹，周期性地发送短期轨迹，产生长期轨迹，格式化 长期轨迹的段，周期性地发送长期轨迹，存储发送的长期轨迹，测试FMS子组件的有效性，当FMS子组件有效时：通过自主指导识别 模块，短期轨迹的活动段，由自主引导模块根据短期轨迹的活动段生成第一个飞行指导指令; 当FMS子组件无效时，由自主引导模块识别存储的轨迹的活动段，由自主引导模块根据所存储的轨迹的活动段产生第二飞行引导顺序 。