公开(公告)号：US10424208B2

公开(公告)日：2019-09-24

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 ,  G01C21/20 ,  G01C23/00 ,  G01W1/00

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.

公开(公告)号：US11536570B2

公开(公告)日：2022-12-27

申请号：US16719409

申请日：2019-12-18

Applicant: THALES

Inventor： Nicolas Rossi ,  Benoît Dacre-Wright ,  Cédric D'Silva

IPC: G01C21/20 ,  G08G5/00 ,  G08G5/02

Abstract: A method for determining an optimized trajectory to be followed by an aircraft, the method being implemented by a determining system of the aircraft and comprising: a first step for acquiring at least one constraint relative to at least one parameter of the trajectory to be followed, the constraint being determined by a control system of a remote station as a function of the air traffic and/or the aircraft mission; a step for calculating a desired trajectory as a function of the constraint; a step for transmitting the desired trajectory to the remote station; a second step for acquiring an instruction comprising an authorization to follow the desired trajectory or a refusal of the desired trajectory.

公开(公告)号：US10699582B2

公开(公告)日：2020-06-30

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 ,  G01C21/20 ,  G01C23/00

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：US10089893B2

公开(公告)日：2018-10-02

申请号：US15727468

申请日：2017-10-06

Applicant: THALES

Inventor： Benoît Dacre-Wright ,  Jérôme Sacle ,  Cédric D'Silva

IPC: G08G5/02 ,  G05D1/06 ,  G08G5/00 ,  G05D1/10 ,  B64C39/02

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：US09963247B2

公开(公告)日：2018-05-08

申请号：US15176003

申请日：2016-06-07

Applicant: THALES

Inventor： Johan Boyer ,  Benoît Dacre-Wright

IPC: B64F1/18 ,  B64C19/00 ,  G05D1/00 ,  G05D1/06 ,  G08G5/00 ,  G08G5/02

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.