Abstract: The invention concerns a system, in particular suitable for high power engines, comprising at least a rotor and means comprising active sections fit for making the rotor(s) rotate by their synchronized deformation, characterized in that the rotor material comprises an Al, Fe alloy with at least one other element, the alloy comprising at least more or less 80% in weight of Al and at least between 0.1 and 15.0% in weight in Fe.

Abstract: The invention concerns a system, in particular suitable for high power engines, comprising at least a rotor and means comprising active sections fit for making the rotor(s) rotate by their synchronised deformation, characterised in that the rotor material comprises an Al, Fe alloy with at least one other element, the alloy comprising at least more or less 80% in weight of Al and at least between 0.1 and 15.0% in weight in Fe.

Abstract: In the orientation device of a transmission assembly for orienting at least one beam in elevation and/or in bearing, said assembly pivots on a fork about an elevation axis and is driven about this axis by a motor supported by said fork, which fork can pivot on a base about a bearing axis, perpendicular to the elevation axis and driven about this axis by a second motor supported by said base, and at least one of the motors is a travelling-wave piezoelectric rotary motor.

Abstract: The invention concerns an actuator which includes a linear piston (2) in an active material, and an inner sliding cylinder (7, 7?) which includes an outer cylinder (5, 5?) in which the said sliding cylinder ((7, 7?) is pre-stressed, with one cylinder being in an anisotropic material with a negative or approximately zero expansion coefficient along at least one axis and a positive or approximately zero expansion coefficient on at least one other axis, and the other cylinder having a positive thermal or approximately zero expansion coefficient.

Abstract: The invention relates to an actuator comprising a sliding sleeve and an active piston, control means, wherein the sliding sleeve and the piston have at their interface at least one pair of friction layers, characterised in that at least one friction layer is made of a material selected from the following: an oxide of a Ti and Cr alloy; a zirconium matrix stabilised by Sc2O3 and/or Al2O3 and/or Cr2O3; a zirconium oxide in tetragonal phase stabilised by Y2O3; an alloy of Al, Fe and at least one other element.

Abstract: In the orientation device of a transmission assembly for orienting at least one beam in elevation and/or in bearing, said assembly pivots on a fork about an elevation axis and is driven about this axis by a motor supported by said fork, which fork can pivot on a base about a bearing axis, perpendicular to the elevation axis and driven about this axis by a second motor supported by said base, and at least one of the motors is a travelling-wave piezoelectric rotary motor.

Abstract: The invention concerns an actuator that includes an active piston, an inner sliding cylinder and an outer cylinder in which the said sliding cylinder is pre-stressed, where one of the cylinders is in a material with a negative thermal expansion coefficient or one that is close to zero, with the other cylinder having a positive thermal expansion coefficient, in which the material of the cylinder with negative expansion coefficient or one close to zero is one of the following materials: ?-ZrMo2O8 in cubic structure, Zr2W P2O12, a silicious faujasite, Lu2 (WO4)3, ZrW2O8 in cubic phase, with nanograins whose size is approximately between 10 nm and 75 nm, or any possible combination of these materials.

Abstract: The invention relates to an actuator comprising a sliding sleeve and an active piston, control means, wherein the sliding sleeve and the piston have at their interface at least one pair of friction layers, characterised in that at least one friction layer is made of a material selected from the following: an oxide of a Ti and Cr alloy; a zirconium matrix stabilised by Sc2O3 and/or Al2O3 and/or Cr2O3; a zirconium oxide in tetragonal phase stabilised by Y2O3; an alloy of Al, Fe and at least one other element.

Abstract: The invention concerns an actuator that includes an active piston, an inner sliding cylinder and an outer cylinder in which the said sliding cylinder is pre-stressed, where one of the cylinders is in a material with a negative thermal expansion coefficient or one that is close to zero, with the other cylinder having a positive thermal expansion coefficient, in which the material of the cylinder with negative expansion coefficient or one close to zero is one of the following materials: ?-ZrMo2O8 in cubic structure, Zr2W P2O12, a silicious faujasite, Lu2 (WO4)3, ZrW2O8 in cubic phase, with nanograins whose size is approximately between 10 nm and 75 nm, or any possible combination of these materials.

Abstract: The invention relates to a device for displacing a moving part along a longitudinal axis relative to a housing, said device being symmetrical about a plane extending longitudinally relative to the moving part, the device comprising two structures that are secured to said moving part and elements of active material comprising at least two blocks extending between inside walls of each structure, with the elongation directions of the blocks being antisymmetrical about an axis substantially perpendicular to the displacement axis of the moving part, wherein the structures are flexible and suitable for displacing the moving part by deforming as a function of the elongation of the blocks.

Abstract: The invention provides an actuator for a control surface (7), in particular for a primary flight control of an aircraft, the actuator including a main actuator (3) in a main control line (1) for actuating the control surface (7), the actuator being characterized in that the actuator of the main control line (1) comprises a motor of the vibration motor type, and in that it further comprises, in a compensation, secondary control line (2), a compensation actuator (4) and spring-forming apparatus (5) interposed between the compensation actuator (4) and the control surface (7), the compensation actuator (4) tensioning or compressing the spring-forming apparatus so as to make them suitable for delivering a mean force to the control surface (7) so as to off-load from the main actuator (3) the mean force that it needs to deliver to the flight control (7).

Abstract: The invention concerns an actuator which includes a linear piston (2) in an active material, and an inner sliding cylinder (7, 7?) which includes an outer cylinder (5, 5?) in which the said sliding cylinder ((7, 7?) is pre-stressed, with one cylinder being in an anisotropic material with a negative or approximately zero expansion coefficient along at least one axis and a positive or approximately zero expansion coefficient on at least one other axis, and the other cylinder having a positive thermal or approximately zero expansion coefficient.

Abstract: The invention relates to a device for displacing a moving part along a longitudinal axis relative to a housing, said device being symmetrical about a plane extending longitudinally relative to the moving part, the device comprising two structures that are secured to said moving part and elements of active material comprising at least two blocks extending between inside walls of each structure, with the elongation directions of the blocks being antisymmetrical about an axis substantially perpendicular to the displacement axis of the moving part, wherein the structures are flexible and suitable for displacing the moving part by deforming as a function of the elongation of the blocks.

Abstract: An electromechanical multiple-disk brake actuator is provided. The actuator includes a first reversible assembly with a central screw, a first electric motor rotating the screw, a first nut displaceable over the screw when the screw is rotated and a connection between the screw and the nut permit reversible displacement. The actuator also has a second non-reversible assembly including an annular screw on the first nut, a second electric motor for rotating the annular screw and the first nut, and a second nut fixed to a frame but axially displaceable over the annual screw when the annular screw is rotated. A piston at one of the ends of the second nut presses the disk against one another to ensure braking.

Abstract: A linear actuator comprises a piston and a rotary electric motor together with means which are interposed between the electric motor and the piston to define a mechanical system for transforming rotary movement of the motor into linear displacement of said piston, the actuator is characterized in that the electric motor is a vibration type motor comprising at least a stator and a rotor together with excitation means for deforming said stator and/or said rotor in modes of vibration combining tangential vibration and normal vibration for driving said rotor in rotation, and in that the means interposed between the electric motor and the piston include means for mechanically decoupling said piston from said electric motor in the event of the electrical power supply to the elector motor being interrupted.

Abstract: This invention relates to a system, especially adapted for high-power motors, comprising at least one rotor (1a; 1b) and means (4a, 4b; 5a, 5b) comprising active elements (7, 8) capable of rotating the rotor(s) (1a; 1b) by their synchronized deformation; said rotating means of the rotor(s) comprising at least one petal (6) comprising a hot top (11), characterized in that the material of each hot top (11) is such that it has a thermal mass capacity (Cp22C) of greater than 0.35 [J/g/K], and/or the material of each rotor (1a; 1b) is such that it has a thermal capacity of greater than 2 [J/cm3/K].

Abstract: The invention provides an actuator for a control surface (7), in particular for a primary flight control of an aircraft, the actuator including a main actuator (3) in a main control line (1) for actuating the control surface (7), the actuator being characterized in that the actuator of the main control line (1) comprises a motor of the vibration motor type, and in that it further comprises, in a compensation, secondary control line (2), a compensation actuator (4) and spring-forming means (5) interposed between the compensation actuator (4) and the control surface (7), said compensation actuator (4) tensioning or compressing the spring-forming means so as to make them suitable for delivering a mean force to the control surface (7) so as to off-load from the main actuator (3) the mean force that it needs to deliver to the flight control (7).

Abstract: A linear actuator comprises a piston and a rotary electric motor together with means which are interposed between the electric motor and the piston to define a mechanical system for transforming rotary movement of the motor into linear displacement of said piston, the actuator is characterized in that the electric motor is a vibration type motor comprising at least a stator and a rotor together with excitation means for deforming said stator and/or said rotor in modes of vibration combining tangential vibration and normal vibration for driving said rotor in rotation, and in that the means interposed between the electric motor and the piston include means for mechanically decoupling said piston from said electric motor in the event of the electrical power supply to the elector motor being interrupted.

Abstract: This invention relates to a system, especially adapted for high-power motors, comprising at least one rotor (1a; 1b) and means (4a, 4b; 5a, 5b) comprising active elements (7, 8) capable of rotating the rotor(s) (1a; 1b) by their synchronized deformation; said rotating means of the rotor(s) comprising at least one petal (6) comprising a hot top (11), characterized in that the material of each hot top (11) is such that it has a thermal mass capacity (Cp22C) of greater than 0.35 [J/g/K], and/or the material of each rotor (1a; 1b) is such that it has a thermal capacity of greater than 2 [J/cm3/K].

Abstract: The present invention relates to an electromechanical multiple-disk brake actuator for a means of transport, in particular for an aircraft.