公开(公告)号：US08948939B2

公开(公告)日：2015-02-03

申请号：US13797485

申请日：2013-03-12

Applicant: Thales

Inventor： Guilhem Putz ,  Christophe Caillaud ,  Francois Coulmeau

IPC: G06F19/00 ,  G08G5/00 ,  G01C23/00 ,  G05D1/06 ,  G05D1/10 ,  G08G5/02 ,  G05D1/02

CPC classification number: G01C23/00 ,  G05D1/0202 ,  G05D1/0676 ,  G05D1/101 ,  G08G5/0021 ,  G08G5/025

Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a calculation step for converting an angular deviation into an equivalent linear deviation, and, conversely, converting a linear deviation into an equivalent angular deviation. The method comprises a step of graphic representation, called unified monitoring, intended for the crew, of a deviation of the aircraft, on a lateral deviation axis and a vertical deviation axis; each of the deviations, lateral and vertical, being able to be represented on a linear scale, an angular scale or a mixed scale.

Abstract translation: 一种辅助飞行器导航的方法包括以下步骤：计算和显示第一线性部分上的线性偏差和在第二角度部分上的角度偏差。 该方法包括用于将角度偏差转换为等效线性偏差的计算步骤，相反地，将线性偏差转换为等效的角度偏差。 该方法包括一个图形表示，称为统一监视，用于机组人员，在横向偏离轴线和垂直偏离轴线上有飞行器偏离; 横向和垂直的每个偏差能够以线性刻度，角度刻度或混合刻度表示。

公开(公告)号：US09766091B2

公开(公告)日：2017-09-19

申请号：US14622683

申请日：2015-02-13

Applicant: THALES

Inventor： Christophe Caillaud ,  Jérôme Sacle

IPC: G01C23/00 ,  G08G5/02 ,  G05D1/06 ,  G08G5/00

CPC classification number: G01C23/005 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/02 ,  G08G5/025

Abstract: A method and system is provided for determining the compatibility of an approach, to a landing runway, with an angular guidance mode, the approach being compatible with a linear guidance mode, the angular guidance being characterized by a lateral angle of precision, the linear guidance being characterized by a lateral divergence of precision. The method is implemented on a flight management system deployed aboard an aircraft and comprising a first step of determining a first distance representative of a maximum distance of use of the angular guidance, on the basis of the lateral angle of precision and of the lateral divergence of precision.

公开(公告)号：US08983689B2

公开(公告)日：2015-03-17

申请号：US13797617

申请日：2013-03-12

Applicant: Thales

Inventor： Guilhem Putz ,  Christophe Caillaud ,  Francois Coulmeau

IPC: G01C23/00 ,  G05D1/06 ,  G08G5/00 ,  G08G5/02

CPC classification number: G01C23/00 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/025

Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a step of calculation of an anticipated deviation of the aircraft, expressed linearly or angularly, projected to a time DT, characteristic of a reaction time of the aircraft, and of a statistical error distribution associated with this anticipated deviation; and a step of calculation of a probability of exceeding a predetermined target deviation, by means of the anticipated deviation and of the statistical error distribution. The method also comprises a crew alert when the probability is above a predetermined threshold.

Abstract translation: 一种辅助飞行器导航的方法包括以下步骤：计算和显示第一线性部分上的线性偏差和在第二角度部分上的角度偏差。 该方法包括计算飞行器的预期偏差的步骤，线性或角度地表示，投影到时间DT，飞机的反应时间的特征，以及与该预期偏差相关联的统计误差分布; 以及通过预期偏差和统计误差分布计算超过预定目标偏差的概率的步骤。 当概率高于预定阈值时，该方法还包括机组警报。