公开(公告)号：US11195420B2

公开(公告)日：2021-12-07

申请号：US16003649

申请日：2018-06-08

Applicant: THALES

Inventor： Xavier Blanchon ,  Guillaume Boyer ,  Guillaume Meulle ,  Sonia Vautier

IPC: G08G5/00 ,  G01C21/20 ,  G05D1/06 ,  G05D1/00 ,  G01C23/00 ,  G05D1/10

Abstract: A method for assisting in a flight management of an aircraft calculates a local cost function CF(xi, hj) at various altitudes hj along a planned vertical reference flight trajectory over a discrete set of points P(xi, hj) which forms a two-dimensional grid in which the planned vertical reference flight trajectory varies, the local cost function CF(xi, hj) being calculated locally at each point P(xi, hj) according to aircraft data and environmental data predicted at said local point P(xi, hj). Then, for each point P(xi, hj) of the grid, the method determines a neighbourhood including the point P(xi, hj), and associates a colour K(xi, hj) therewith that is dependent on the value of the local cost function CF(xi, hj) using a predetermined bijective lookup transformation. Next, the method displays the coloured grid formed by the coloured neighbourhoods.

公开(公告)号：US11823582B2

公开(公告)日：2023-11-21

申请号：US16716198

申请日：2019-12-16

Applicant: THALES

Inventor： Guillaume Meulle ,  Christophe Pierre ,  Dorian Martinez

IPC: G08G5/00 ,  B64D45/00 ,  G05D1/10 ,  G06F17/17 ,  G01C21/20

CPC classification number: G08G5/0047 ,  B64D45/00 ,  G01C21/20 ,  G05D1/101 ,  G06F17/17 ,  G08G5/0052 ,  B64D2045/0075

Abstract: Methods and systems for optimizing the flight of an aircraft are disclosed. The trajectory is divided into segments, each of the segments being governed by distinct sets of equations, depending on engine thrust mode and on vertical guidance (climb, cruise or descent). By assuming two, aerodynamic and engine-speed, models, data from flight recordings are received and a number of parameters from a parameter-optimization engine is iteratively determined by applying a least-squares calculation until a predefined minimality criterion is satisfied. The parameter optimization engine is next used to predict the trajectory point following a given point. Software aspects and system (e.g. FMS and/or EFB) aspects are described.

公开(公告)号：US09290262B2

公开(公告)日：2016-03-22

申请号：US14186681

申请日：2014-02-21

Applicant: THALES

Inventor： Enrique Laso-Leon ,  Amandine Audouy ,  Guillaume Meulle ,  Michel Roger

IPC: G08G5/02 ,  G05D1/04 ,  B64C19/00 ,  G05D1/00 ,  G05D1/06 ,  G01C21/20 ,  G08G5/00

CPC classification number: B64C19/00 ,  G01C21/20 ,  G05D1/0005 ,  G05D1/0607 ,  G08G5/0021 ,  G08G5/0034

Abstract: A method for creating a vertical trajectory profile of an aircraft by optimization of a criterion representative of a flight cost, comprises: performing a first iterative computation of a profile free of altitude constraints as long as a condition dependent on the criterion is not reached, replacing each free level of the constraint-free profile with a permitted level so as to generate an initial constrained profile comprising a plurality of permitted levels, and, for each level, an altitude change point and a plurality of speeds, and performing a second iterative computation of a profile in which the altitude levels to be reached remain constant, equal to the initial permitted levels of the initial constrained profile, as long as a condition dependent on the criterion is not reached.

Abstract translation: 一种用于通过优化表示飞行成本的标准来创建飞行器的垂直轨迹曲线的方法包括：只要没有达到取决于标准的条件，就执行没有高度约束的轮廓的第一迭代计算，替换 每个具有允许级别的无约束简档的空闲级别，以便产生包括多个允许级别的初始约束简档，并且对于每个级别，对于每个级别，高度变化点和多个速度，以及执行第二迭代计算 其中要达到的高度水平保持恒定，等于初始约束曲线的初始允许水平，只要不达到取决于准则的条件即可。

公开(公告)号：US09234909B2

公开(公告)日：2016-01-12

申请号：US14268816

申请日：2014-05-02

Applicant: THALES

Inventor： Guillaume Meulle ,  Thomas Caussat ,  Arnaud Beaufils ,  Christophe Pierre

IPC: G01P5/00 ,  B64C19/00

CPC classification number: G01P5/00 ,  B64C19/00

Abstract: A method and system for determining an airspeed of an aircraft, known as assisted aircraft, comprises: a) determining a position; b) measuring a ground speed; c) receiving a plurality of messages from a plurality of other assisting, aircraft, each message containing a first item of information, indicating a position of an assisting aircraft, and a second item of information, indicating a wind speed at the position; d) estimating a wind speed at the position of the assisted aircraft by interpolating the wind speed values at the positions of the assisting aircraft obtained in step c); and e) computing a true speed of the assisted aircraft by using the vector difference between its ground speed, measured in step b), and the wind speed estimated in step d). The method can check operation of an anemometric subsystem aboard an aircraft, to compensate for any malfunction and/or to enable automatic piloting.

Abstract translation: 一种称为辅助飞行器的用于确定飞机空速的方法和系统，包括：a）确定位置; b）测量地面速度; c）从多个其他辅助飞机接收多个消息，每个消息包含指示协助飞机的位置的第一信息项和指示该位置的风速的第二信息项; d）通过在步骤c）中获得的辅助飞行器的位置处插入风速值来估计辅助飞机位置处的风速; 以及e）通过使用在步骤b）中测量的地面速度与步骤d）中估计的风速之间的矢量差来计算辅助飞行器的真实速度。 该方法可以检查飞机上的气象学子系统的操作，以补偿任何故障和/或实现自动驾驶。