公开(公告)号：US20140330458A1

公开(公告)日：2014-11-06

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。

公开(公告)号：US20180239364A1

公开(公告)日：2018-08-23

申请号：US15753537

申请日：2016-09-06

Applicant: THALES

Inventor： Guillaume MEULLE ,  Enrique LASO-LEON

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

CPC classification number: G05D1/0661 ,  G01C21/20 ,  G05D1/0005 ,  G05D1/0607 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0065

Abstract: A method for optimizing the trajectory of an aircraft comprises the steps of determining one or more reference criteria CiRef on the basis of a non-optimized initial trajectory; determining one or more initial constraints K′j on the basis of the initial trajectory; determining a criterion Ci according to an analytical function of the criteria CiRef; and, per iteration cycle, determining an optimized trajectory; determining intermediate constraints K′j on the basis of the optimized trajectory; minimizing the criterion Ci determined under the initial constraints K′j and the intermediate constraints K′j; determining q takeoff parameters Pi. Developments describe an incremental iteration of the method, an interruption by the pilot, the use of criteria comprising the fuel consumption, the acoustic noise level, the emission of chemical compounds, the level of wear of the engine, the use of a gradient descent and of diverse optimizations. System and software aspects are described.

公开(公告)号：US20180366011A1

公开(公告)日：2018-12-20

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

Abstract: A method for assisting in the flight management of an aircraft calculates a local operating cost function CF(xi, hj) at various altitudes hj along a planned 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. The method is implemented in an onboard flight management avionics system, in an onboard tablet of EFB type, in a ground tool of the operator which is interfaced with the onboard flight management system, or by distribution over the three types of systems.

公开(公告)号：US20140244077A1

公开(公告)日：2014-08-28

申请号：US14186681

申请日：2014-02-21

Applicant: THALES

Inventor： Enrique LASO-LEON ,  Amandine AUDOUY ,  Guillaume MEULLE ,  Michel ROGER

IPC: B64C19/00

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。