The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Nov. 03, 2015

Filed:

Oct. 22, 2014
Applicant:

Thales, Neuilly-sur-Seine, FR;

Inventors:

Francois Coulmeau, Seilh, FR;

Jerome Sacle, Tournefeuille, FR;

Johan Boyer, Toulouse, FR;

Assignee:

Thales, Courbevoie, FR;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
G05D 1/00 (2006.01); G08G 5/00 (2006.01); G01C 23/00 (2006.01); G05D 1/04 (2006.01); G05D 1/06 (2006.01); G08G 5/02 (2006.01);
U.S. Cl.
CPC ...
G05D 1/00 (2013.01); G01C 23/00 (2013.01); G05D 1/042 (2013.01); G05D 1/0676 (2013.01); G08G 5/003 (2013.01); G08G 5/0021 (2013.01); G08G 5/025 (2013.01);
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.


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