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:
Oct. 02, 2018

Filed:

Oct. 06, 2017
Applicant:

Thales, Courbevoie, FR;

Inventors:

Benoît Dacre-Wright, Toulouse, FR;

Jérôme Sacle, Toulouse, FR;

Cédric D'Silva, Toulouse, FR;

Assignee:

THALES, Courbevoie, FR;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
G08G 5/02 (2006.01); G05D 1/06 (2006.01); G08G 5/00 (2006.01); G05D 1/10 (2006.01); B64C 39/02 (2006.01);
U.S. Cl.
CPC ...
G08G 5/025 (2013.01); G05D 1/0607 (2013.01); G05D 1/0676 (2013.01); G05D 1/101 (2013.01); G08G 5/0013 (2013.01); G08G 5/0021 (2013.01); G08G 5/0039 (2013.01); G08G 5/0052 (2013.01); G08G 5/0069 (2013.01); G08G 5/0091 (2013.01); B64C 39/024 (2013.01);
Abstract

A method for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft comprises a first step of computing an energy differential of the aircraft in the air ΔEbetween a first initial state of the aircraft at an initial geodesic point Qi and a second final state of the aircraft at the final arrival target point Qf. The method comprises a second step of adjusting an adjustable modelled profile of altitude h(t) and of air speed Va(t) of the aircraft with the aid of parameters so the adjusted modelled profile of altitude h(t) and of air speed Va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air ΔEin a fixed required timespan Δtand a fixed required altitude variation t−tin the required time timespan, the aircraft operating permanently in an engine regime with constant and minimum thrust. The method comprises a third step of determining a lateral geodesic trajectory of the aircraft on the basis of the adjusted altitude profile h(t), of the adjusted air speed profile Va(t) and of the knowledge of the speeds of the winds in the aircraft's scheduled geographical traversal zone.


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