Abstract: A device for assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35. An additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35. The additional force is a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).

Abstract: An energy absorber element comprises an absorber portion having first and second distal ends and having a first elongate element and a second elongate element facing the first elongate element and connected to the second element solely at the first and second distal ends, a first anchor point secured to the first distal end of the absorber portion, and a second anchor point secured to the second distal end of the absorber portion, wherein each of the first and second elongate elements includes a succession of straight-line segments parallel to one another and at least one circularly-arcuate segment such that at least two successive straight-line segments are connected together by one of the at least one circularly-arcuate segment.

Abstract: A seat for a powered aircraft, the seat comprising a bucket (2) that is supported in hyperstatic manner on a stand. Leg members (7, 8) carry the bucket (2) via bolts (10). A first hinged mechanism for geometrically compensating deformation of the floor associates a ball-joint mounting of the bolts (10) on the leg members (7, 8) with an axial deformation arrangement of the bolts (10) between opposing axial bearing surfaces where they press against a strength member (9) of the bucket (2) and against the leg members (7, 8). A second energy-absorber mechanism associates fuses (22) with deformable support members (23) for the bucket (2), which members engage the bolts (10) and the leg members (7, 8) via slides (25) arranged to adjust the initial height position of the bucket (2).

Abstract: The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35), during which method an additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35), the additional force being a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).

Abstract: A crashworthy seat for a vehicle comprises a stand including a first and a second foot connected mechanically to a first and a second vertical support leg; a pan connected by the stand to a floor wherein the first and the second feet are disposed on each side of the pan, the pan including a seat proper and a seat back, wherein the seat back has a support element secured to the first and the second vertical support legs configured to support the seat back; a guide element configured to guide the pan in translation; an energy absorber device; a first anchor point secured to the first distal end of the absorber portion; and a second anchor point secured to the second distal end of the absorber portion.

Abstract: A seat for a powered aircraft, the seat comprising a bucket (2) that is supported in hyperstatic manner on a stand. Leg members (7, 8) carry the bucket (2) via bolts (10). A first hinged mechanism for geometrically compensating deformation of the floor associates a ball-joint mounting of the bolts (10) on the leg members (7, 8) with an axial deformation arrangement of the bolts (10) between opposing axial bearing surfaces where they press against a strength member (9) of the bucket (2) and against the leg members (7, 8). A second energy-absorber mechanism associates fuses (22) with deformable support members (23) for the bucket (2), which members engage the bolts (10) and the leg members (7, 8) via slides (25) arranged to adjust the initial height position of the bucket (2).

Abstract: The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35), during which method an additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35), the additional force being a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).

Abstract: The invention relates to an actuator (9) comprising a rotary electric motor (12) a screw Old) driven in rotation by the motor, a mechanical member (15) driven in translation by the screw, a first position sensor (40) sensitive to a position of the electric motor and/or of the screw, a second position sensor (41) sensitive to a position of the mechanical member, and a servo-control circuit (11) connected to both of the position sensors and to the motor, this circuit delivering a power supply signal to the motor that varies as a function of a position setpoint signal (23) and as a function of signals delivered by the two position sensors; the second position sensor presents a resolution that is at least equivalent to the resolution of the first position sensor, and the servo-control circuit includes redundant modules (19, 22) for calculating the position of the mechanical member as a function of the signals/data delivered by the two sensors, together with at least two modules (17, 18) for mutual surveillance of

Abstract: An energy absorber element comprises an absorber portion having first and second distal ends and having a first elongate element and a second elongate element facing the first elongate element and connected to the second element solely at the first and second distal ends, a first anchor point secured to the first distal end of the absorber portion, and a second anchor point secured to the second distal end of the absorber portion, wherein each of the first and second elongate elements includes a succession of straight-line segments parallel to one another and at least one circularly-arcuate segment such that at least two successive straight-line segments are connected together by one of the at least one circularly-arcuate segment.

Abstract: A crashworthy seat for a vehicle comprises a stand including a first and a second foot connected mechanically to a first and a second vertical support leg; a pan connected by the stand to a floor wherein the first and the second feet are disposed on each side of the pan, the pan including a seat proper and a seat back, wherein the seat back has a support element secured to the first and the second vertical support legs configured to support the seat back a guide element configured to guide the pan in translation; an energy absorber device; a first anchor point secured to the first distal end of the absorber portion; and a second anchor point secured to the second distal end of the absorber portion.

Abstract: The invention relates to an actuator (9) comprising a rotary electric motor (12) a screw Old) driven n rotation by the motor, a mechanical member (15) driven in translation by the screw, a first position sensor (40) sensitive to a position of the electric motor and/or of the screw, a second position sensor (41) sensitive to a position of the mechanical member, and a servo-control circuit (11) connected to both of the position sensors and to the motor, this circuit delivering a power supply signal to the motor that varies as a function of a position setpoint signal (23) and as a function of signals delivered by the two position sensors; the second position sensor presents a resolution that is at least equivalent to the resolution of the first position sensor, and the servo-control circuit includes redundant modules (19, 22) for calculating the position of the mechanical member as a function of the signals/data delivered by the two sensors, together with at least two modules (17, 18) for mutual surveillance of