公开(公告)号：US20180370645A1

公开(公告)日：2018-12-27

申请号：US16007981

申请日：2018-06-13

Applicant: THALES

Inventor： Geoffrey DURAND ,  Johan BOYER

IPC: B64D31/04 ,  B64D43/00

Abstract: This aid method for controlling the energy situation of an aircraft includes steps for determining (120) an energy meeting point corresponding to a constraint point, determining (130) a meeting type based on the constraint at the constraint point, determining (140) an energy state of the aircraft relative to a reference altitude profile determined by a flight management system, determining (150) a high-energy joining profile representative of a future path of the aircraft with an energy dissipation strategy, the determination being carried out backwards depending on the type of meeting and the energy state of the aircraft, determining (160) energy deviations relative to the high-energy joining profile, and displaying (170) energy deviations.

公开(公告)号：US20150323933A1

公开(公告)日：2015-11-12

申请号：US14707946

申请日：2015-05-08

Applicant: THALES

Inventor： Alexandre DARBOIS ,  Mathieu LE MERRER ,  Johan BOYER

IPC: G05D1/02

CPC classification number: G05D1/0005

Abstract: A method implemented by computer for optimizing the cruising trajectory of an aircraft comprises the steps consisting in receiving the parameters of a reference trajectory, the trajectory comprising one or more plateaus and the transitions between these plateaus, the transitions being ascending or descending; and determining, in response to a request received in the course of the flight, at least one candidate alternative trajectory; and determining one or more indicators associated with the candidate alternative trajectory such as determined. Developments comprise the optional display of at least one indicator, indicators associated with the fuel consumption, with a difference in flight time or with the operational cost of the flight of the aircraft, the use of ratios of indicators, the inhibition of descending transitions, particular plateau length transitions as well as economical modes of transition. System aspects are described, comprising avionic or non-avionic means.

Abstract translation: 用于优化飞行器巡航轨迹的计算机实现的方法包括以下步骤：接收参考轨迹的参数，所述轨迹包括一个或多个平台，以及这些平台之间的转换，所述转换是上升或下降; 以及响应于在飞行过程中接收的请求确定至少一个候选替代轨迹; 以及确定与候选替代轨迹相关联的一个或多个指示符，例如确定的。 发展包括可选地显示至少一个指标，与燃料消耗相关联的指标，飞行时间的差异或飞行器的飞行的运行成本，指示器的使用比例，下降转换的抑制，特别是 平台长度转换以及经济的转型模式。 描述了系统方面，包括航空电子或非航空手段。

公开(公告)号：US20220282975A1

公开(公告)日：2022-09-08

申请号：US17637299

申请日：2020-08-20

Applicant: THALES

Inventor： Johan BOYER ,  Emmanuel DEWAS ,  Geoffrey DURAND

IPC: G01C21/20 ,  G01C21/00

Abstract: This method comprises a step of determining a reference profile along a lateral trajectory precalculated comprising searching, in the precalculated lateral trajectory, at least one segment of discontinuity comprising a lateral discontinuity, determining a required distance corresponding to a minimum flight distance between the two segments bordering the discontinuity segment and integrating each required distance into the reference profile.
This method further comprises a step of determining, on the basis of the reference profile, vertical predictions relating to a vertical trajectory of the aircraft and a step of determining, on the basis of the vertical predictions, a resulting lateral trajectory comprising, for each discontinuity segment, determining a substitution segment connecting the two corresponding bordering segments in a continuous manner.

公开(公告)号：US20150120095A1

公开(公告)日：2015-04-30

申请号：US14521239

申请日：2014-10-22

Applicant: THALES

Inventor： Francois COULMEAU ,  Jerome SACLE ,  Johan BOYER

IPC: G05D1/00 ,  G08G5/00

CPC classification number: G05D1/00 ,  G01C23/00 ,  G05D1/042 ,  G05D1/0676 ,  G05D1/101 ,  G08G5/0021 ,  G08G5/003 ,  G08G5/0052 ,  G08G5/025 ,  Y02T50/84

Abstract: A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft.

Abstract translation: 提供了一种用于管理飞行由飞行管理系统计算的轨迹的飞行器的飞行的方法。 轨迹必须在飞行器的两种不同的空气动力学构型之间进行至少一个过渡。 该方法包括：从数据库中提取飞行器的性能数据，作为空气动力学配置的函数的至少一个性能数据项，第一确定步骤和第二确定步骤之间的选择，确定起始点的步骤 以及在飞行期间飞行器的两种空气动力学构型和发动机速度之间的转变的终点，所述确定步骤由飞行管理系统实施并且从第一和第二确定步骤中选择，所述确定步骤通过以下步骤计算轨迹： 代表使用飞机性能数据的飞机动力学的方程的数值积分。

公开(公告)号：US20250002172A1

公开(公告)日：2025-01-02

申请号：US18751271

申请日：2024-06-23

Applicant: THALES

Inventor： Denis RICAUD ,  Johan BOYER ,  Laurent FREDE

IPC: B64D45/04 ,  G01C21/20

Abstract: A method for determining a runway to be used for making an emergency landing, implemented in flight by an electronic device on-board an aircraft. The method includes at least one iteration of (i) obtaining, from on-board equipment of the aircraft, data representative of current wind characteristics, at a current altitude of the aircraft, and (ii) determining a runway to be used for the emergency landing, based on data representative of current wind characteristics at current altitude, based on a set of preselected runways, and based on a structure of correlation data between the data representative of wind characteristics at the current altitude and data representative of runways in service on the ground.

公开(公告)号：US20240185727A1

公开(公告)日：2024-06-06

申请号：US18527324

申请日：2023-12-03

Applicant: THALES

Inventor： Denis RICAUD ,  Johan BOYER ,  Laurent FREDE

IPC: G08G5/00

CPC classification number: G08G5/0039 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0056

Abstract: A method for remotely controlling the flight of an aircraft following a first flight plan, the aircraft includes a communication module connected to a flight management centre of the aircraft, the communication module being suitable for allowing a communication between a terrestrial communication station and the aircraft, the method comprising the following steps:



determining, in the terrestrial communication station, an incapacity of the pilot or pilots of the aircraft,
using the communication module, receiving a first signal that has been coded using a predetermined code and transmitted by the terrestrial communication station, and then decoding the first signal using the predetermined code, which has previously been stored in the communication module,
after the first signal has been decoded, sending, using the communication module, a command to the flight management centre prompting a second flight plan to be followed by the aircraft.

公开(公告)号：US20230206774A1

公开(公告)日：2023-06-29

申请号：US17927683

申请日：2021-05-25

Applicant: THALES

Inventor： Johan BOYER ,  Sabine TAINTURIER ,  Geoffrey DURAND

IPC: G08G5/02 ,  G08G5/00

CPC classification number: G08G5/025 ,  G08G5/0047 ,  G08G5/0039

Abstract: An approach assistance method includes: an initial calculation step for calculating a reference path and the application of a stabilization test for determining whether the reference path makes the landing possible; modification steps implemented in a sequence and applying predefined modification rules and applying the stabilization test after each modification; and a transmitting step including transmitting the reference path to the human pilot, to an autopilot and/or to a traffic management system as soon as the reference path passes the stabilization test.

公开(公告)号：US20180284812A1

公开(公告)日：2018-10-04

申请号：US15940753

申请日：2018-03-29

Applicant: THALES

Inventor： Geoffrey DURAND ,  Bertrand CAUDRON DE COQUEREAUMONT ,  Johan BOYER

IPC: G05D1/06 ,  B64D45/04

Abstract: A method implemented by computer for the management of the descent of an aircraft, comprises the steps of: receiving a descent profile; determining a search band comprising a plurality of flight segments of the profile; and selecting a flight segment in the search band. Various selection criteria are described, in particular the consideration of the commands of pitch-up and/or separation with respect to the active segment (anticipation distance). Other developments comprise the fact that the search band is configurable, the consideration of the load factor, modalities of tangent capture (trajectory with no segment crossing), compliance with altitude constraints, the determination of capture parabola modeling the trajectory, as well as the activation of the segment selected as control reference. System aspects and software aspects are described.

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。

公开(公告)号：US20220390959A1

公开(公告)日：2022-12-08

申请号：US17775865

申请日：2020-11-13

Applicant: THALES

Inventor： Johan BOYER ,  Geoffrey DURAND ,  Jérôme SACLE

IPC: G05D1/06 ,  B64C39/02

Abstract: Methods and devices for optimizing the climb of an aircraft or drone are provided. After an optimal continuous climb strategy has been determined, a lateral path is determined, in particular in terms of speeds and turn radii, based on vertical predictions computed in the previous step. Subsequently, computation results are displayed on one or more human-machine interfaces and the climb strategy is actually flown. Embodiments describe the use of altitude and speed constraints and/or settings in respect of speed and/or thrust and/or level-flight avoidance and/or gradient-variation minimization, and iteratively fitting parameters in order to make the profile of the current path coincide with the constrained profile in real time depending on the selected flight dynamics (e.g. energy sharing, constraint on climb gradient, constraint on the vertical climb rate). System (e.g. FMS) and software aspects are described.