Abstract: An aerodynamic measurement probe intended to measure a local angle of attack of an airflow circulating along the fuselage of an aircraft, the support comprising a circular cover with a central opening which is passed through by the mobile shaft, the outer surface of the cover comprising a frustoconical face exhibiting symmetry of revolution about the longitudinal axis, the cover comprising polyether ether ketone reinforced with glass or carbon fibers, with a thermal conductivity of less than 3 W.m?1·K?1 and being provided with metallic inserts at its fastenings, at least one metallic electrical continuity insert being configured to establish an electrical connection between the inner part of the probe and an interface of the metallic insert disposed under the lower periphery of that part of the metallic insert which is furthest away from the shaft.

Abstract: An aerodynamic measurement probe intended to measure a local angle of attack of an air stream flowing along the fuselage of an aircraft, includes a support and a shaft that is able to rotate about a longitudinal axis with respect to the support, the support and the shaft being configured to form between them a gap, passing around an annular tab at the end of the shaft in the support, making it possible to maintain a functional clearance to allow one end of the shaft to pivot freely in the support, and communicating with an impurity discharge circuit, the gap comprising an inner annular groove about the axis of rotation, made in the support, and opening out away from the axis directly onto the end part of the annular tab, the profile of the inner groove being rounded.

Abstract: A laser gyro includes a cylindrical solid amplifier bar having an axis of revolution. The laser gyro also includes: an annular piezoelectric element for exciting said solid amplifier element at a predetermined frequency f, along said axis of revolution, said annular piezoelectric element being mounted fixed on one of the two end cross sections of the cylindrical solid amplifier bar so that its axis of revolution coincides with said axis of revolution of said cylindrical solid amplifier bar; and an annular dynamic counterweight mounted fixed on the free end cross section of said annular piezoelectric element so that its axis of revolution coincides with said axis of revolution of said cylindrical solid amplifier bar; said cylindrical solid amplifier bar being dimensioned so as to be considered nondeformable at said excitation frequency f.

Abstract: A laser gyro includes a cylindrical solid amplifier bar having an axis of revolution. The laser gyro also includes: an annular piezoelectric element for exciting said solid amplifier element at a predetermined frequency f, along said axis of revolution, said annular piezoelectric element being mounted fixed on one of the two end cross sections of the cylindrical solid amplifier bar so that its axis of revolution coincides with said axis of revolution of said cylindrical solid amplifier bar; and an annular dynamic counterweight mounted fixed on the free end cross section of said annular piezoelectric element so that its axis of revolution coincides with said axis of revolution of said cylindrical solid amplifier bar; said cylindrical solid amplifier bar being dimensioned so as to be considered nondeformable at said excitation frequency f.

Abstract: The invention relates to a gyrometer based on a vibrating structure, produced by micromachining in a thin planar wafer, including two symmetrical moving assemblies coupled by a coupling structure connecting these two assemblies in order to allow transfer of mechanical vibration energy between them, each moving assembly comprising three moving elements, a first inertial moving element intended to vibrate in two orthogonal directions Ox and Oy in the plane of the wafer, a second moving element intended to vibrate along Oy and connected to the first moving element and to fixed anchoring zones, by first linking means which allow the vibration movement of the first moving element along Oy to be transmitted to the second moving element without permitting movement of the second element along the Ox direction and a third moving element intended to vibrate along Oy and connected to the second moving element and to fixed anchoring zones by second linking means which allow the vibration movement of the second moving ele

Abstract: The invention relates to a gyrometer based on a vibrating structure, produced by micromachining in a thin planar wafer, including two symmetrical moving assemblies coupled by a coupling structure connecting these two assemblies in order to allow transfer of mechanical vibration energy between them, each moving assembly comprising three moving elements, a first inertial moving element intended to vibrate in two orthogonal directions Ox and Oy in the plane of the wafer, a second moving element intended to vibrate along Oy and connected to the first moving element and to fixed anchoring zones, by first linking means which allow the vibration movement of the first moving element along Oy to be transmitted to the second moving element without permitting movement of the second element along the Ox direction and a third moving element intended to vibrate along Oy and connected to the second moving element and to fixed anchoring zones by second linking means which allow the vibration movement of the second moving ele

Abstract: An actuating motion detection device for a mechanically actuated gyrolaser including at least one fastening ring coaxial with an actuation axis of the gyrolaser. The fastening ring includes a hub held at a center of a rim by radial flexible strips distributed about the hub, and the radial flexible strips are configured to act as springs and to vibrate under an actuating motion. The motion detecting device includes torsion detectors having a pair of piezoelectric plates disposed at a radial position along one radial flexible strip. The piezoelectric plates have respective remanent magnetic fields aligned in opposite directions, and each piezoelectric plate has two electrodes positioned on opposite sides of the piezoelectric plate with one of the two electrodes contacting the radial flexible strip. The electrodes are connected to a common output.

Abstract: A device for fastening an optical unit to an actuating ring of an actuating device including a fastening ring joined to the actuating ring and having a plurality of securing shims bonded to the optical unit and connected to the fastening ring by flexible axial tongues. The device can be applied to a triaxial laser gyrometer.

Abstract: In the disclosed laser gyrometer, the three resonant optical cavities of the block are connected to a cathode chamber by means of the three cathode capillary tubes and to a balancing chamber by means of three balancing capillary tubes. The axis of the cathode is identified with the axis of actuation. The block is actuated by means of an actuating ring in thermal contact with the cathode so as to provide for dissipation of the heat generated at the cathode. The invention makes it possible to solve the problems relating to wobble (or lack of dynamic balance) as well as thermal gradients.