公开(公告)号：US11436928B2

公开(公告)日：2022-09-06

申请号：US16821779

申请日：2020-03-17

Applicant: DASSAULT AVIATION

Inventor： Cyrille Grimald ,  Benoit Urien

IPC: G08G5/00 ,  G06F16/29 ,  B64D45/00 ,  G05D1/04

Abstract: Aircraft mission calculation system includes a first calculator configured to calculate a plurality of iso-displacement curves from a selected point, at a displacement range corresponding to several successive displacement increments of the aircraft from the selected point, the iso-displacement curves being obtained at the displacement range for a displacement of the aircraft to a given flight level from displacements of the aircraft at distinct flight altitude levels. The first calculator is configured to determine, based on iso-displacement curves up to the given flight level, obtained at distinct flight altitude levels, taken at the same displacement range of the aircraft, an extended iso-displacement curve at the given flight level maximizing the displacement of the aircraft from the geographical point of origin or minimizing the displacement of the aircraft toward the geographical destination point.

公开(公告)号：US12230147B2

公开(公告)日：2025-02-18

申请号：US16357639

申请日：2019-03-19

Applicant: DASSAULT AVIATION

Inventor： Cyrille Grimald ,  Benjamin Briand

IPC: G08G5/00

Abstract: A system for establishing an operational flight plan includes a basic flight data acquisition unit for acquiring basic flight data from an external flight plan development system, the basic flight data comprising at least one theoretical fuel weight to be loaded into the aircraft. The system also includes an aircraft actual operational specifications acquisition unit for acquiring actual operational specifications of the aircraft, the actual operational specifications including an airplane context; a proposed flight data calculating unit for calculating proposed flight data including at least one proposed weight of fuel corresponding to the theoretical weight, calculated based on actual operational specifications of the aircraft and a specified trajectory of the aircraft; and a viewer, and a display manager capable of displaying a proposed flight data display window including the proposed fuel weight.

公开(公告)号：US12170027B2

公开(公告)日：2024-12-17

申请号：US17967587

申请日：2022-10-17

Applicant: DASSAULT AVIATION

Inventor： Cyrille Grimald ,  Benoît Urien

IPC: G01C21/20 ,  G08G5/00

Abstract: An aircraft mission calculation system is configured to calculate an environmental benefit index. The system includes an aircraft trajectory calculation engine, able to calculate at least one potential mission trajectory between a geographic point of origin and a geographic point of destination. The aircraft trajectory calculation engine comprises an environmental benefit index calculation module, able to activate the calculation engine. The environmental benefit index calculation module is able to determine an environmental benefit index (GI) of the potential trajectory from the first amount of carbon dioxide (Q1(TR1)) produced on a first reference trajectory defining a fastest mission, the second amount of carbon dioxide produced on a second reference trajectory (Q2(TR2)), defining a mission minimizing the amount of carbon dioxide produced, and the potential amount of carbon dioxide produced on the potential trajectory.

公开(公告)号：US11430343B2

公开(公告)日：2022-08-30

申请号：US16199045

申请日：2018-11-23

Applicant: DASSAULT AVIATION

Inventor： Benjamin Briand ,  Cédric Carle ,  Stéphane Drinal ,  Cyrille Grimald ,  Jean-François Saez ,  Cyril Saint Requier ,  Jean-Baptiste Vallart

IPC: G08G5/00 ,  G01C23/00 ,  G06F3/0488 ,  G06F3/04847

Abstract: An aircraft mission computing system includes an aircraft mission path computing engine, and a mission deck comprising a display and a display management assembly configured for displaying, on the display, at least one button for defining an operational specification of the mission. The computing engine is configured to be activated after defining the choice of operational specification using the definition button to determine at least one possible path of the aircraft based on the or each choice of defined operational specification using the or each definition button. The display management assembly is configured to display, on the display, after the activation of the computing engine, at least one outcome indicator providing mission feasibility information while respecting the or each operational specification choice.