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：US20180284813A1

公开(公告)日：2018-10-04

申请号：US15940777

申请日：2018-03-29

Applicant: THALES

Inventor： Johan BOYER ,  Lucia GUERRA MARTIN

IPC: G05D1/06 ,  G08G5/00 ,  G01C23/00 ,  G01C5/00 ,  G05D1/04

Abstract: A method is described that is implemented by computer for optimizing the vertical descent profile of an aircraft, the vertical profile being broken down into an altitude profile and a speed profile. One or more altitudes of passage can be determined by minimizing the overall deviation between the speed profile and one or more speed constraints previously received. The optimized descent profile can comprise one or more of these altitudes of passage. Different developments are described, in particular embodiments in which an optimized altitude of passage minimizes the engine thrust, the descent profile is of OPEN IDLE, FPA or VS type, the optimized descent profile is determined backward, a speed constraint is of AT or AT OR ABOVE type, and the use of the airbrakes. Display modalities are described, as are system and software aspects.

公开(公告)号：US20160085239A1

公开(公告)日：2016-03-24

申请号：US14861610

申请日：2015-09-22

Applicant: THALES

Inventor： Johan BOYER ,  Rémy AULETTO ,  Norbert BALOCHE

IPC: G05D1/04 ,  G05D1/06 ,  G01C21/00

CPC classification number: G05D1/042 ,  G01C21/00 ,  G01C23/00 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/025 ,  Y02T50/84

Abstract: A method for adapting an aircraft constant-gradient descent segment comprises: an acquisition step in which state variables characterizing the aircraft, environment variables characterizing the environment thereof and path variables characterizing the predicted path thereof at one of the initial and final points of the segment are acquired; a calculation step whereby a limit ground gradient for at least one performance criterion is calculated from the state variables, environment variables and path variables; a validity verification step checking the validity of the path initially predicted against the most restrictive limit ground gradient; and when the path initially predicted is not valid: a feasibility verification step checking the feasibility of a command to modify at least one state variable; if feasibility is verified, a prediction of executing the command; otherwise, a prediction of modifying one of the initial and final points of the segment with respect to constraints of the flight plan.

Abstract translation: 一种用于调整飞行器恒定梯度下降段的方法，包括：获取步骤，其中表征飞行器的状态变量，表征其环境的环境变量和表征其在该段的初始和最终点之一的预测路径的路径变量是 获得 计算步骤，其中根据状态变量，环境变量和路径变量计算至少一个性能标准的极限地面梯度; 有效性验证步骤，根据最严格限制的地面坡度检查最初预测的路径的有效性; 并且当最初预测的路径无效时：可行性验证步骤检查命令修改至少一个状态变量的可行性; 如果验证可行性，则执行命令的预测; 否则，预测相对于飞行计划的约束修改段的初始和最终点之一。

公开(公告)号：US20150120100A1

公开(公告)日：2015-04-30

申请号：US14522469

申请日：2014-10-23

Applicant: THALES

Inventor： Jerome SACLE ,  Johan BOYER ,  Francois COULMEAU

IPC: G05D1/00 ,  G08G5/00 ,  G05D1/04

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。