公开(公告)号：US20160210867A1

公开(公告)日：2016-07-21

申请号：US14992929

申请日：2016-01-11

Applicant: THALES

Inventor： Christophe PIERRE ,  Rémy AULETTO ,  Benoît DACRE-WRIGHT

IPC: G08G5/00 ,  G01W1/02 ,  G06F7/72 ,  G01C21/20

CPC classification number: G08G5/0039 ,  G01C21/20 ,  G01W1/02 ,  G06F7/724 ,  G08G5/0034 ,  G08G5/0052 ,  G08G5/0091

Abstract: A navigation aid method for an aircraft flying a reference trajectory between a point of departure and a point of arrival subject to a field of wind vectors comprises: decomposing the reference trajectory into a plurality of discrete waypoints Pi, loading meteorological data comprising the field of wind vectors, iterating the following steps N times, to generate an improved trajectory: for each waypoint Pi named current point, determining a reference plane, determining an orthonormal reference frame, determining a wind curl ((∇W)Pi), determining a sign of the projection of the wind curl on axis zi ((∇W)zi Pi), determining a direction of displacement from the current point Pi to a new current waypoint Pi′, determining a line of displacement, determining a displacement distance, determining the new current waypoint, determining a new trajectory, assigning the new waypoints Pi′ determined in the preceding iteration to the waypoints Pi for the next iteration.

Abstract translation: 一种用于飞行在出发点与受到风向量场的到达点之间的参考轨迹的飞行器的导航辅助方法包括：将参考轨迹分解为多个离散航路点Pi，加载包括风场的气象数据 向量，迭代以下步骤N次，以产生改进的轨迹：对于每个路点Pi命名当前点，确定参考平面，确定正交参考帧，确定风卷曲（（∇W）Pi），确定 确定从当前点Pi到新的当前路点Pi'的位移方向，确定位移线，确定位移距离，确定新的当前点Pi 确定一个新的轨迹，将上一次迭代中确定的新路点Pi'分配给下一次迭代的路点Pi。

公开(公告)号：US20160210866A1

公开(公告)日：2016-07-21

申请号：US14991704

申请日：2016-01-08

Applicant: THALES

Inventor： Christophe PIERRE ,  Rémy AULETTO ,  Benoît DACRE-WRIGHT

IPC: G08G5/00 ,  G01C21/00

Abstract: A navigational aid method of an aircraft, carried out by a flight management system, for comparing a reference trajectory of the aircraft subjected to a wind vector field with a new trajectory between the same starting and end points, respectively, the method comprises: determining the reference trajectory, determining the new trajectory, loading meteorological data, determining a directional surface, delimited by a directional closed curve, consisting of the new trajectory, from the starting point to the end point, closed by the opposite of the reference trajectory from the end point to the starting point, determining a wind curl on the basis of the wind vector field, determining a flow of the wind curl through the surface, a positive value of flow indicating that the new trajectory makes better use of the wind load, a negative value of flow indicating that the new trajectory makes less effective use of the wind load.

Abstract translation: 一种由飞行管理系统执行的用于将经过风矢量场的飞行器的参考轨迹与相同起点和终点之间的新轨迹进行比较的飞行器的导航辅助方法，包括：确定 参考轨迹，确定新的轨迹，加载气象数据，确定由方向性闭合曲线限定的方向表面，由新的轨迹组成，从起始点到终点，与从末端到参考轨迹的相反闭合 指出起点，根据风矢量场确定风卷曲，确定通过表面的卷曲流动，表示新轨迹更好地利用风荷载的流量正值，负值 流量值指示新的轨迹使得风力负荷的使用效果较差。

公开(公告)号：US20180366008A1

公开(公告)日：2018-12-20

申请号：US16009017

申请日：2018-06-14

Applicant: THALES

Inventor： Benoît DACRE-WRIGHT ,  Olivier PINEAU ,  François NEFFLIER

IPC: G08G5/00 ,  G02B27/01

Abstract: Various methods for regulating and/or for integrating avionic systems with non-avionic systems are described. An avionic system is generally associated with a physical fault rate that is lower and a logic verification that is higher than those of a non-avionic system. Developments describe notably the use: of remote computing resources; of comparison, test, verification and authorization steps before injection of data of non-avionic origin into the avionics; of human-machine interaction methods; of various parameters (weather, air traffic, etc.) for the purpose of combinatorial optimization; and of electronic flight bags EFB and of flight management systems FMS.

公开(公告)号：US20180114452A1

公开(公告)日：2018-04-26

申请号：US15727468

申请日：2017-10-06

Applicant: THALES

Inventor： Benoît DACRE-WRIGHT ,  Jérôme SACLE ,  Cédric D'SILVA

IPC: G08G5/02 ,  G08G5/00

CPC classification number: G08G5/025 ,  B64C39/024 ,  G05D1/0607 ,  G05D1/0676 ,  G05D1/101 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0039 ,  G08G5/0052 ,  G08G5/0069 ,  G08G5/0091

Abstract: A method for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft comprises a first step of computing an energy differential of the aircraft in the air ΔEa between a first initial state of the aircraft at an initial geodesic point Qi and a second final state of the aircraft at the final arrival target point Qf. The method comprises a second step of adjusting an adjustable modelled profile of altitude hm(t) and of air speed Vam(t) of the aircraft with the aid of parameters so the adjusted modelled profile of altitude h(t) and of air speed Va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air ΔEa in a fixed required timespan Δtrequired and a fixed required altitude variation tf−ti in the required time timespan, the aircraft operating permanently in an engine regime with constant and minimum thrust. The method comprises a third step of determining a lateral geodesic trajectory of the aircraft on the basis of the adjusted altitude profile h(t), of the adjusted air speed profile Va(t) and of the knowledge of the speeds of the winds in the aircraft's scheduled geographical traversal zone.

公开(公告)号：US20160362194A1

公开(公告)日：2016-12-15

申请号：US15176003

申请日：2016-06-07

Applicant: THALES

Inventor： Johan BOYER ,  Benoît DACRE-WRIGHT

IPC: B64F1/18 ,  G08G5/00 ,  B64C19/00

CPC classification number: B64F1/18 ,  B64C19/00 ,  G05D1/0005 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/0034 ,  G08G5/025 ,  Y02T50/84

Abstract: A method of automatic determination of a descent and approach profile for an aircraft is based on a backward computation of propagation of a state of the aircraft along segments S(i) from a backward computation start point to the start point DECEL of onset of the deceleration of the aircraft. The method of automatic determination comprises for each segment S(i) a step of determining an optimal speed VOPT(i) of the aircraft over the range of speeds of the next aerodynamic configuration C(j+1) to be implemented as a function of a predetermined deceleration strategy and/or of predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan.

Abstract translation: 自动确定飞行器的下降和接近轮廓的方法是基于飞行器状态从后向计算开始点到起始点DECEL的沿着S（i）的状态的传播的反向计算 的飞机。 自动确定的方法包括对于每个段S（i）在下一个空气动力学配置C（j + 1）的速度范围内确定飞机的最佳速度VOPT（i）的步骤，以便作为 预定的减速策略和/或飞行程序固有的预定的限制，或飞行员在其飞行计划中引入。