公开(公告)号：US20190384326A1

公开(公告)日：2019-12-19

申请号：US16435239

申请日：2019-06-07

Applicant: THALES

Inventor： Romain LAMOUR ,  Frédéric BERGER ,  François COLONNA ,  Marianne CAZES

IPC: G05D1/10 ,  B64C13/18

Abstract: A conversion device for converting a guidance setpoint signal from an aircraft guidance system for at least one control axis, into a control signal for an avionics system such as an aircraft stabilization system, comprising an acquisition module designed to acquire the guidance setpoint signal, and a generation module designed to generate the control signal from the acquired guidance setpoint signal, the control signal comprising at least two command pulses, the generation module being designed to calculate the duration between two consecutive command pulses depending on a corresponding value of the acquired guidance setpoint signal.

公开(公告)号：US20230192312A1

公开(公告)日：2023-06-22

申请号：US17924969

申请日：2021-05-12

Applicant: THALES

Inventor： Frédéric BERGER ,  Thierry GANILLE ,  Didier POISSON ,  Pierre-Yves DUMAS

IPC: B64D43/02 ,  B64D45/08 ,  G01C23/00

CPC classification number: B64D43/02 ,  B64D45/08 ,  G01C23/005

Abstract: Disclosed is a method of guiding the pilot of an aircraft for the alignment maneuver, including: determining at a first instant an occurrence close to the alignment maneuver and triggering the display of a first symbol on the screen; updating the position of the first symbol on the horizon according to the updated value of the aircraft heading; when the alignment maneuver is to begin, moving a second symbol on the screen from the position of the first symbol, the direction of the displacement with respect to the horizon being determined depending on the direction of the crosswind with respect to the runway and the value of the displacement being determined depending on the difference between the current dynamic sideslip of the aircraft and a current dynamic sideslip setpoint value calculated for the aircraft.