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1.发明授权Method for determining a result path of an aircraft, associated device and computer program product 有权用于确定飞机，相关设备和计算机程序产品的结果路径的方法公开(公告)号：US09329045B2
公开(公告)日：2016-05-03
申请号：US14540756
申请日：2014-11-13
Applicant: THALES
Inventor： Francois Coulmeau , Arnaud Bonnafoux , Nicolas Rossi
CPC classification number: G01C21/00 , G01S13/953 , G05D1/101 , G08G5/0034 , G08G5/0052 , G08G5/04
Abstract: A method for determining a result path of an aircraft, the result path including a set of successive positions of the aircraft between an initial global point and a final global point that are predetermined for a mission of the aircraft is provided.The aircraft includes a plurality of calculating members, each able to guide the aircraft during at least part of the mission and to calculate an elementary path of the aircraft during that part, each elementary path including a set of successive positions of the aircraft between an initial elementary point and a final elementary point.The device includes calculating a portion of the result path from elementary paths coming from at least two distinct calculating members.
Abstract translation: 提供了一种用于确定飞行器的结果路径的方法，所述结果路径包括飞行器在为飞行器的任务预定的初始全局点和最终全局点之间的连续位置的集合。 飞行器包括多个计算构件，每个计算构件能够在至少部分任务期间引导飞行器，并且在该部分期间计算飞行器的基本路径，每个基本路径包括飞行器在初始位置之间的连续位置的集合 基本点和最终基本点。 该装置包括从至少两个不同的计算部件的基本路径计算结果路径的一部分。
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2.发明授权Method of correcting a lateral trajectory on approach as a function of the energy to be reabsorbed 有权在接近时校正侧向轨迹的方法作为要被再吸收的能量的函数公开(公告)号：US08924047B2
公开(公告)日：2014-12-30
申请号：US13789595
申请日：2013-03-07
Applicant: Thales
Inventor： Emmanuel Dewas , Vincent Savarit , Francois Coulmeau
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。
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3.发明授权Flight management device for an aircraft adapted to the handling of multiple time constraints and corresponding method 有权飞机管理装置适用于适用于处理多个时间限制的飞机和相应的方法公开(公告)号：US09494945B2
公开(公告)日：2016-11-15
申请号：US13900215
申请日：2013-05-22
Applicant: THALES
Inventor： Francois Coulmeau , Guy Deker , Xavier Blanchon , Patrick Mazoyer
CPC classification number: G05D1/101 , G08G5/0039
Abstract: A device and method for flight management of an aircraft along a flight plan comprises a plurality of waypoints comprising a computation of the temporal predictions determining the temporal situation of the aircraft for each waypoint of the flight plan, a temporal situation of the aircraft being defined by at least one set of information from among the group comprising the target time of transit at each waypoint the estimated minimum and maximum times of arrival at each waypoint, the estimated time of transit at the waypoint, and a formatting and display simultaneously presenting the temporal situations of the said plurality of waypoints.
Abstract translation: 一种沿着飞行计划的飞行器的飞行管理的装置和方法包括多个航路点，其包括对飞行计划的每个航路点确定飞机的时间状态的时间预测的计算，飞行器的时间情况由 包括在每个航路点的目标传输时间的组中的至少一组信息，估计在每个航路点的最小和最大到达时间，在航路点的过境估计时间以及同时呈现时间情况的格式化和显示 的所述多个航路点。
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4.发明授权Method for aiding navigation making it possible to manage a vertical constraint in an anticipated manner 有权用于辅助导航的方法使得可以以预期的方式管理垂直约束公开(公告)号：US09440731B2
公开(公告)日：2016-09-13
申请号：US13934854
申请日：2013-07-03
Applicant: THALES
Inventor： Francois Coulmeau , Xavier Blanchon , Christophe Pierre
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，以及预定义的速度，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。
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5.发明授权Method for aiding navigation for an aircraft during descent and during approach at reduced thrust 有权在下降期间和在减小推力进近期间协助航空器导航的方法公开(公告)号：US09188978B2
公开(公告)日：2015-11-17
申请号：US14522469
申请日：2014-10-23
Applicant: THALES
Inventor： Jerome Sacle , Johan Boyer , Francois Coulmeau
CPC classification number: G05D1/00 , G01C21/20 , G01C23/00 , G05D1/0005 , G05D1/042 , G05D1/0676 , G06Q10/047 , G08G5/003 , G08G5/006 , G08G5/0095 , G08G5/025 , Y02T50/84
Abstract: A method for aiding navigation for an aircraft between a descent start point and a computation end point, comprises the computation steps of: collecting a flight plan consisting of a succession of waypoints and of the associated vertical constraints; determining a corridor consisting of a floor trajectory and of a ceiling trajectory defining the minimum and maximum altitudes permitted to the aircraft; splitting the corridor into several cells defined between two waypoints furthest apart and between which the ceiling trajectory is distinct from the floor trajectory; determining for at least one cell a vertical trajectory complying with the altitude constraints and comprising the longest possible IDLE segment; and a step consisting in determining and displaying maneuvering points of the aircraft making it possible to follow the target vertical trajectory.
Abstract translation: 一种用于帮助航空器在下降起点和计算终点之间的导航的方法包括以下计算步骤：收集由一系列航路点和相关垂直约束组成的飞行计划; 确定由地板轨迹和限定飞机允许的最小和最大高度的天花板轨迹组成的走廊; 将走廊拆分成两个距离最远的两个航点之间定义的几个单元，天花板轨迹与地板轨迹不同; 为至少一个小区确定符合所述高度约束的垂直轨迹并且包括所述最长可能的空闲段; 并且包括确定和显示飞行器的机动点的步骤，使得可以跟随目标垂直轨迹。
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Patent Agency Ranking
6.发明授权Navigation assistance method based on anticipation of linear or angular deviations 有权基于预测线性或角度偏差的导航辅助方法公开(公告)号：US08983689B2
公开(公告)日：2015-03-17
申请号：US13797617
申请日：2013-03-12
Applicant: Thales
Inventor： Guilhem Putz , Christophe Caillaud , Francois Coulmeau
CPC classification number: G01C23/00 , G05D1/0676 , G08G5/0021 , G08G5/025
Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a step of calculation of an anticipated deviation of the aircraft, expressed linearly or angularly, projected to a time DT, characteristic of a reaction time of the aircraft, and of a statistical error distribution associated with this anticipated deviation; and a step of calculation of a probability of exceeding a predetermined target deviation, by means of the anticipated deviation and of the statistical error distribution. The method also comprises a crew alert when the probability is above a predetermined threshold.
Abstract translation: 一种辅助飞行器导航的方法包括以下步骤：计算和显示第一线性部分上的线性偏差和在第二角度部分上的角度偏差。 该方法包括计算飞行器的预期偏差的步骤，线性或角度地表示，投影到时间DT，飞机的反应时间的特征，以及与该预期偏差相关联的统计误差分布; 以及通过预期偏差和统计误差分布计算超过预定目标偏差的概率的步骤。 当概率高于预定阈值时，该方法还包括机组警报。
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公开(公告)号：US09709420B2
公开(公告)日：2017-07-18
申请号：US14717993
申请日：2015-05-20
Applicant: THALES
Inventor： Frederic Bonamy , Francois Coulmeau , Celia Ebrard
CPC classification number: G01C23/005 , G08G5/0021
Abstract: A method implemented by computer for the display of information relating to the flight of an aircraft comprises receiving indication of a selection of an arbitrary display zone on a screen of an onboard computer of the aircraft; and reconfiguring the display, in response to the indication. Developments describe several geometric transformations, various display reconfigurations (e.g. centering of the display), the use of systems third party to the aircraft (e.g. taxiing computer, ground client, maintenance, terrain monitoring, traffic, weather), associated operations of revisions of the flight plan, the use of display rules (notably associated with the flight situation), and the emergency deactivation of the display reconfigurations. Computer programs and associated systems are also described (notably Man-System Interface, virtual and/or augmented reality).
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8.发明申请METHOD FOR DETERMINING A RESULT PATH OF AN AIRCRAFT, ASSOCIATED DEVICE AND COMPUTER PROGRAM PRODUCT 有权用于确定飞机，相关设备和计算机程序产品的结果路径的方法公开(公告)号：US20150142221A1
公开(公告)日：2015-05-21
申请号：US14540756
申请日：2014-11-13
Applicant: THALES
Inventor： Francois Coulmeau , Arnaud Bonnafoux , Nicolas Rossi
CPC classification number: G01C21/00 , G01S13/953 , G05D1/101 , G08G5/0034 , G08G5/0052 , G08G5/04
Abstract: A method for determining a result path of an aircraft, the result path including a set of successive positions of the aircraft between an initial global point and a final global point that are predetermined for a mission of the aircraft is provided.The aircraft includes a plurality of calculating members, each able to guide the aircraft during at least part of the mission and to calculate an elementary path of the aircraft during that part, each elementary path including a set of successive positions of the aircraft between an initial elementary point and a final elementary point.The device includes calculating a portion of the result path from elementary paths coming from at least two distinct calculating members.
Abstract translation: 提供了一种用于确定飞行器的结果路径的方法，所述结果路径包括飞行器在为飞行器的任务预定的初始全局点和最终全局点之间的连续位置的集合。 飞行器包括多个计算构件，每个计算构件能够在至少部分任务期间引导飞行器，并且在该部分期间计算飞行器的基本路径，每个基本路径包括飞行器在初始位置之间的连续位置的集合 基本点和最终基本点。 该装置包括从至少两个不同的计算部件的基本路径计算结果路径的一部分。
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公开(公告)号：US08958987B2
公开(公告)日：2015-02-17
申请号：US13767471
申请日：2013-02-14
Applicant: THALES
Inventor： Emmanuel Dewas , Vincent Savarit , Francois Coulmeau
CPC classification number: G01C21/00 , G08G5/003 , G08G5/0034 , G08G5/0039 , G08G5/006
Abstract: A method and device for determining a shifted circular segment on the basis of an initial circular segment, the shifted circular segment being shifted by a shift distance, the method being implemented by a computer dedicated to flight management, comprises: determining a shifted final point terminating a shifted circular segment, on the basis of the final point terminating the initial circular segment, through a shift of the final point determined on the basis of the shift distance and in the direction of shift, through the use of a straight line passing through the center of the initial circular segment and the final point of the initial circular segment, and determining a shifted circular segment on the basis of the initial circular segment by construction of a circular segment between the shifted final point associated with the preceding shifted segment and the shifted final point associated with the shifted segment.
Abstract translation: 一种用于基于初始圆形段确定偏移的圆形段的方法和装置，所述偏移的环形段被偏移了移动距离，该方法由专用于飞行管理的计算机实现，包括：确定移位的终点终止 基于最终点终止初始圆形段的移动圆形段，通过使用通过所述移动距离的直线，基于移动距离和移动方向确定的最终点的移动 初始圆形段的中心和初始圆形段的最终点，并且基于初始圆形段通过在与前一移位段相关联的移位的最终点之间构造一个圆形段来确定移位的圆形段，并且移位 与转移段相关联的最终点。
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10.发明授权Navigation assistance method for monitoring navigation performance in linear or angular mode 有权用于监视线性或角度模式导航性能的导航辅助方法公开(公告)号：US08948939B2
公开(公告)日：2015-02-03
申请号：US13797485
申请日：2013-03-12
Applicant: Thales
Inventor： Guilhem Putz , Christophe Caillaud , Francois Coulmeau
CPC classification number: G01C23/00 , G05D1/0202 , G05D1/0676 , G05D1/101 , G08G5/0021 , G08G5/025
Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a calculation step for converting an angular deviation into an equivalent linear deviation, and, conversely, converting a linear deviation into an equivalent angular deviation. The method comprises a step of graphic representation, called unified monitoring, intended for the crew, of a deviation of the aircraft, on a lateral deviation axis and a vertical deviation axis; each of the deviations, lateral and vertical, being able to be represented on a linear scale, an angular scale or a mixed scale.
Abstract translation: 一种辅助飞行器导航的方法包括以下步骤：计算和显示第一线性部分上的线性偏差和在第二角度部分上的角度偏差。 该方法包括用于将角度偏差转换为等效线性偏差的计算步骤，相反地，将线性偏差转换为等效的角度偏差。 该方法包括一个图形表示，称为统一监视，用于机组人员，在横向偏离轴线和垂直偏离轴线上有飞行器偏离; 横向和垂直的每个偏差能够以线性刻度，角度刻度或混合刻度表示。
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