FLIGHT COMMAND AND DIRECTION ON GROUND COMMAND SYSTEM FOR AN AIRCRAFT
Aircraft flight control and ground steering control system This electrical flight control system is intended for an aircraft that has a main landing gear with a front landing gear. It is provided with a handle ( 2 ) that can move around two maneuvering axes ( 4, 6 ) by means of a linkage system ( 8 ), and is movable in rotation around a longitudinal axis substantially perpendicular to the maneuvering axes, means on each of the maneuvering axes for generating a pilot-operated instruction from a movement of the movable handle around one maneuvering axis, and means for generating an instruction in order to act on the orientation of the front landing gear of the aircraft as a function of the angular position of the movable handle ( 2 ) relative to the longitudinal axis.
1 . An electrical aircraft flight control system that has a main landing gear with a front landing gear, comprising a handle ( 2 ) that can move around two maneuvering axes ( 4 , 6 ) by means of a linkage system ( 8 ), and means on each of the maneuvering axes for generating a pilot-operated instruction from a movement of the movable handle around one maneuvering axis,
characterized in that the movable handle is also movable in rotation around a longitudinal axis substantially perpendicular to the maneuvering axes, and in that means are provided to generate an instruction in order to act on the orientation of the front landing gear of the aircraft as a function of the angular position of the movable handle ( 2 ) relative to the longitudinal axis.
2 . An electrical flight control system according to claim 1 , characterized in that the means for generating an instruction comprise at least one device ( 20 ) for sensing the position of the movable handle ( 2 ) relative to a reference position.
3 . An electrical flight control system according to claim 2 , characterized in that the position sensor ( 20 ) is a rotary potentiometer.
4 . An electrical flight control system according to one of claims 2 or 3 , characterized in that the position sensor ( 20 ) is placed between the movable handle ( 2 ) and the linkage system ( 8 ).
5 . An electrical flight control system according to one of claims 1 to 4 , characterized in that a double-spring system tends to return the movable handle ( 2 ) to a reference angular position relative to its longitudinal axis.
6 . An aircraft flight deck, characterized in that it is equipped with a flight control system according to one of claims 1 to 5 .
7 . An aircraft, characterized in that it is equipped with a flight control system according to one of claims 1 to 5 .