An aeroplane attitude indicator device includes a mobile rod which includes a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body, at least one actuator for controlling the motions of the rod, and a system for piloting the at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction. The assembly of rod and moving body correspond to a pendulum-like artifact. Also described is an aeroplane cockpit equipped with an attitude indicator device.

One embodiment is directed towards an inertial measurement unit (IMU) for measuring an input rate of rotation about an input axis. The IMU includes a first three dimensional gyroscope disposed such that a first axis of its three axes is oriented at a skew angle in degrees away from a reference plane, wherein the reference plane is normal to the input axis. The IMU also includes one or more processing devices coupled to the first gyroscope. The IMU also includes one or more data storage devices coupled to the one or more processing devices, the one or more data storage devices including instructions which, when executed by the one or more processing devices, cause the one or more processing devices to calculate the input rate of rotation based on dividing a sensed rate of rotation about the first axis by the sine of the skew angle.

One embodiment is directed towards an inertial measurement unit (IMU) for measuring an input rate of rotation about an input axis. The IMU includes a first three dimensional gyroscope disposed such that a first axis of its three axes is oriented at a skew angle in degrees away from a reference plane, wherein the reference plane is normal to the input axis. The IMU also includes one or more processing devices coupled to the first gyroscope. The IMU also includes one or more data storage devices coupled to the one or more processing devices, the one or more data storage devices including instructions which, when executed by the one or more processing devices, cause the one or more processing devices to calculate the input rate of rotation based on dividing a sensed rate of rotation about the first axis by the sine of the skew angle.

An aeroplane attitude indicator device includes a mobile rod which includes a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body, at least one actuator for controlling the motions of the rod, and a system for piloting the at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction. The assembly of rod and moving body correspond to a pendulum-like artefact. Also described is an aeroplane cockpit equipped with an attitude indicator device.

The invention relates to a device (100) for measuring the angular errors in the inclination of a real axis of rotation (204) of a rotary element (101), the device comprising control electronics (111) controlling the rotation of the rotary element (101) about its real axis of rotation (204), a first and a second rotation sensor (112a, 112b) for obtaining angular velocities about two measurement axes (302, 304) which are orthogonal to one another and both orthogonal to the real axis of rotation (204), a third rotation sensor (112c) making it possible to obtain the angular position and angular velocity of the rotation element (101) about its real axis of rotation (204), at least two of the aforementioned sensors being inertial sensors making it possible to obtain projections of the vector of the speed of rotation of the Earth onto at least two axes of projection, an acquisition unit (113), a measurements-storage memory (114), a computation unit (115) configured to compute, from the angular positions and velocities obtained from the aforesaid sensors, the angular errors in the inclination of the real axis of rotation (204) of the rotary element (101).

The invention relates to a device (100) for measuring the angular errors in the inclination of a real axis of rotation (204) of a rotary element (101), the device comprising control electronics (111) controlling the rotation of the rotary element (101) about its real axis of rotation (204), a first and a second rotation sensor (112a, 112b) for obtaining angular velocities about two measurement axes (302, 304) which are orthogonal to one another and both orthogonal to the real axis of rotation (204), a third rotation sensor (112c) making it possible to obtain the angular position and angular velocity of the rotation element (101) about its real axis of rotation (204), at least two of the aforementioned sensors being inertial sensors making it possible to obtain projections of the vector of the speed of rotation of the Earth onto at least two axes of projection, an acquisition unit (113), a measurements-storage memory (114), a computation unit (115) configured to compute, from the angular positions and velocities obtained from the aforesaid sensors, the angular errors in the inclination of the real axis of rotation (204) of the rotary element (101).

An instrument for determining the spreading capacity of a coating or a surface, including a plate on which a gripping system is secured, the tool including a measuring system configured to measure the coating to be spread, wherein the measuring system includes at least one force sensor for generating data relating to the average force applied on the instrument, the maximum force applied on the instrument and the duration, in order to provide a signal representative of the capacity of the coating to be spread or the surface to be spread.

An instrument for determining the spreading capacity of a coating or a surface, including a plate on which a gripping system is secured, the tool including a measuring system configured to measure the coating to be spread, wherein the measuring system includes at least one force sensor for generating data relating to the average force applied on the instrument, the maximum force applied on the instrument and the duration, in order to provide a signal representative of the capacity of the coating to be spread or the surface to be spread.