公开(公告)号：US12084192B2

公开(公告)日：2024-09-10

申请号：US17872628

申请日：2022-07-25

Applicant: DASSAULT AVIATION

Inventor： Angélique Beaucamp ,  Laurent Fillet ,  Nicolas Le Corre

IPC: B64D31/04 ,  G05D1/00

CPC classification number: B64D31/04 ,  G05D1/0083

Abstract: A device is for assisting the piloting in acceleration of an aircraft in taking in order to control its speed. The comprises a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command for controlling the speed of the aircraft and a central controller, adapted to operate pilot at least one engine of the aircraft to apply the taxiing command defined by the pilot. The taxiing piloting command is an acceleration or deceleration command of the aircraft during taxiing.

公开(公告)号：US12227288B2

公开(公告)日：2025-02-18

申请号：US17872676

申请日：2022-07-25

Applicant: DASSAULT AVIATION

Inventor： Angélique Beaucamp ,  Nicolas Le Corre ,  François Pineau

IPC: B64C25/42 ,  B64C25/32 ,  B64C25/48

Abstract: A device is for assisting the taxiing of an aircraft, using at least one engine and at least one braking member. The device includes a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command and a central controller, adapted to operate pilot at least one engine of the aircraft to apply the taxiing command defined by the pilot. The central controller is also configured to pilot at least one braking member of the aircraft to apply the taxiing piloting command defined by the pilot.

公开(公告)号：US10099775B2

公开(公告)日：2018-10-16

申请号：US15203605

申请日：2016-07-06

Applicant: DASSAULT AVIATION

Inventor： Arnaud Turpin ,  Nicolas Le Corre

IPC: B64C13/18 ,  G05D1/00 ,  G05D1/08 ,  G05D1/04

Abstract: An autopilot system for an aircraft and related process are provided. The system includes a first load factor command definition and application module; a second roll command definition and application module; a control module of the first definition and application module and the second definition and application module, able to define parameters of a recovery maneuver seeking to return the aircraft to setpoint attitudes at the end of a maneuver from initial attitudes. The control module includes a submodule for computing at least one pair of authorities respectively applied by the first module and by the second module during the recovery maneuver. The authorities are computed as a function of at least a current movement parameter of the aircraft and a safety parameter.

公开(公告)号：US09159239B2

公开(公告)日：2015-10-13

申请号：US14089535

申请日：2013-11-25

Applicant: DASSAULT AVIATION

Inventor： Nicolas Le Corre ,  Sébastien Lepage ,  Alain Boucher

IPC: G06F19/00 ,  G06G7/70 ,  G08G5/00 ,  G05D1/00 ,  G05D1/06 ,  G08G5/02

CPC classification number: G08G5/00 ,  G05D1/0083 ,  G05D1/0676 ,  G08G5/025

Abstract: The method according to the invention comprise the following steps, dynamic measurement of the current geographical position of the aircraft, and its current ground speed, calculation of a first length representative of a flight phase of the aircraft, and calculation of a second length representative of a ground phase of the aircraft, calculation of the position of the stop point based on the first length, the second length and the current geographical position. The calculation of the first length comprises a phase for dynamically estimating a distance traveled by the aircraft during at least part of a flare phase of the aircraft.

Abstract translation: 根据本发明的方法包括以下步骤：飞行器当前地理位置的动态测量及其当前地面速度，代表飞行器飞行阶段的第一长度的计算，以及代表飞行器的第二长度的计算 飞机的地面相位，基于第一长度，第二长度和当前地理位置计算停止点的位置。 第一长度的计算包括一个阶段，用于动态地估计飞机在至少部分飞机的火炬阶段期间行驶的距离。