公开(公告)号：US11138891B2

公开(公告)日：2021-10-05

申请号：US16921242

申请日：2020-07-06

Applicant: THALES

Inventor： Michel Roger ,  Valérie Bataillon

IPC: G01C21/00 ,  G08G5/02

Abstract: This method for managing the flight of an aircraft in a visual approach phase to a runway is implemented by an electronic flight management system and comprises: acquiring at least one set among a set of values of lateral visual approach trajectory parameters and a set of values of vertical visual approach trajectory parameters, at least one of said values of visual approach trajectory parameters being able to be designated by a user, computing at least one trajectory among a lateral visual approach trajectory from the values of said lateral visual approach trajectory parameters and a vertical visual approach trajectory from the values of said vertical visual approach trajectory parameters, and generating a visual approach trajectory to the runway from the lateral visual approach trajectory and/or the vertical visual approach trajectory.

公开(公告)号：US09530321B2

公开(公告)日：2016-12-27

申请号：US14627645

申请日：2015-02-20

Applicant: THALES

Inventor： Guy Deker ,  Michel Roger ,  Bruno Aymeric

IPC: G01C23/00 ,  G08G5/00 ,  G05D1/10

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.

公开(公告)号：US11435763B2

公开(公告)日：2022-09-06

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, said device being adapted for collecting the location data of the leader mobile machine from among the actual location data derived from measurements relating to the current location of the leader mobile machine and the current trajectory data of the accompanying mobile machine, and of determining, on the basis of 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, 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：US09575489B2

公开(公告)日：2017-02-21

申请号：US14951420

申请日：2015-11-24

Applicant: THALES

Inventor： Michel Roger ,  Alexandre Darbois

IPC: G05D1/00 ,  G08G5/00

CPC classification number: G05D1/0077 ,  G08G5/003 ,  G08G5/0047

Abstract: A method of error detection of a flight management system coupled with a guidance of an aircraft according to a flight plan, comprises the steps of: generating a first reference guidance order, monitoring the integrity of the first reference position, when the first reference position is not monitored as being dependable: invalidating the first FMS assembly and the associated guidance system, when the first reference position and the first reference trajectory are monitored as being dependable: generating a first monitoring guidance order, generating a first reference flight control, generating a first monitoring flight control, in monitoring the integrity of the first reference guidance order when the first reference guidance order is not monitored as being dependable: invalidating the first FMS assembly and the associated guidance.

Abstract translation: 根据飞行计划与飞行器的引导相结合的飞行管理系统的错误检测方法包括以下步骤：产生第一参考指导指令，监视第一参考位置的完整性，当第一参考位置是 不被监视为可靠的：当第一参考位置和第一参考轨迹被监视为可靠时，使第一FMS组件和相关联的引导系统无效：产生第一监视引导顺序，产生第一参考飞行控制，产生第一参考飞行控制 监控飞行控制，在第一个参考指导指令不被监视为可靠时监视第一参考指南顺序的完整性：使第一个FMS组件和相关指导无效。

公开(公告)号：US09290262B2

公开(公告)日：2016-03-22

申请号：US14186681

申请日：2014-02-21

Applicant: THALES

Inventor： Enrique Laso-Leon ,  Amandine Audouy ,  Guillaume Meulle ,  Michel Roger

IPC: G08G5/02 ,  G05D1/04 ,  B64C19/00 ,  G05D1/00 ,  G05D1/06 ,  G01C21/20 ,  G08G5/00

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：US09272771B2

公开(公告)日：2016-03-01

申请号：US14075707

申请日：2013-11-08

Applicant: THALES

Inventor： Norbert Baloche ,  Bertrand Barnetche ,  Michel Roger

IPC: G01C21/00 ,  B64C19/00 ,  G05D1/10

CPC classification number: B64C19/00 ,  G01C21/00 ,  G05D1/101

Abstract: An onboard flight management system in an aircraft comprises means for continuously calculating first geolocation data, from data received from at least one external geolocation device, comprising a current position and future positions of an aircraft along a trajectory sequenced in several portions and comprising second data comprising demands required by an international navigation procedure called “Required Navigation Performance”, or RNP, for all the portions of the trajectory. The management system additionally comprises a means for displaying first and second data all the way along the trajectory, the first and second data being represented graphically and simultaneously on the said display means in order to enable the pilot to anticipate the flight characteristics for the aircraft and make them converge toward the required demands of the next trajectory portion.

Abstract translation: 飞行器中的机载飞行管理系统包括用于从从至少一个外部地理定位装置接收的数据连续地计算第一地理位置数据的装置，其包括沿着以若干部分排序的轨迹的飞行器的当前位置和未来位置，并且包括第二数据， 对于轨迹的所有部分，国际导航程序所要求的要求，称为“所需导航性能”（RNP）。 管理系统还包括用于沿着轨迹一直显示第一和第二数据的装置，第一和第二数据在所述显示装置上以图形和同时的方式表示，以使驾驶员能够预测飞机的飞行特性， 使它们朝着下一个轨迹部分的要求收敛。

公开(公告)号：US09983009B2

公开(公告)日：2018-05-29

申请号：US15642238

申请日：2017-07-05

Applicant: THALES

Inventor： Michel Roger ,  Christophe Pierre ,  Hervé Goutelard

IPC: G01C21/20 ,  G01S19/49 ,  G01C21/16 ,  G01C23/00 ,  G08G5/00 ,  G01S19/48 ,  G05D1/02

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：US09666082B2

公开(公告)日：2017-05-30

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.

公开(公告)号：US12198557B2

公开(公告)日：2025-01-14

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：US10380901B2

公开(公告)日：2019-08-13

申请号：US15492693

申请日：2017-04-20

Applicant: THALES

Inventor： Guy Deker ,  Michel Roger

IPC: G08G5/00 ,  G01C21/20 ,  G05D1/06 ,  B64D31/02 ,  G01C21/00

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.