Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Maxime Semat

Thierry Bourret

Florent Lanterna

Martin Delporte

David Andissac

Matthieu Barba

Didier Sauve

A piloting assistance system for an aircraft includes a measuring module for measuring a vertical manoeuvre of the aircraft, a computational module for computing a first load factor from the measured vertical manoeuvre and from a setpoint vertical manoeuvre, a measuring module for measuring an inclination angle, a pitch rate and a pitch acceleration, a protection module including a computational submodule configured to compute a second load factor and a comparison submodule in order to compare the first and the second load factor in order to determine an applicable load factor equal to the minimum between the first and the second load factor, a computational module configured to compute elevator control from the applicable load factor and a sending module configured to send the elevator control to the automatic pilot.

Piloting assistance method for an aircraft, making it possible to ensure the availability of an automatic pilot

An estimation system includes a module for measuring a current angle of attack and current flight parameters of the aircraft, a module for estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft, a module for estimating an angle of attack for a zero lift from the current angle of attack, from the current lift coefficient and from a slope of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack, a module for estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift and a module for sending the current position of the flaps to a user device.

Method and system for estimating the flaps position of an aircraft

A measurement unit for measuring a first static pressure of the ambient air in a first measurement zone of the aircraft, a measurement unit for measuring a second pressure of the ambient air, at least one static pressure probe, in a second measurement zone of the aircraft, the second pressure having a value lower than the first static pressure, a computation unit for estimating a Mach number using these two measured pressures and a data transmission unit configured to transmit the estimated Mach number to a user system.

Method and device for estimating the mach number of an aircraft

Growing community of inventors

Toulouse, France

Maxime Semat