A method and device are provided for determining a mode of detection of an element that reflects ultrasonic waves, wherein it comprises at least the following steps: For each point P of a given volume Zr, determining an ultrasonic field value A.sub.ij.sup.m (P) for N emitter-receiver pairs (i, j) and for one detection mode m, computing a number $C^m\left(P,\stackrel{.fwdarw.}{n}\right)=\underset{i,j=1}{\overset{N}{.Math.}}{c}_{\mathrm{ij}}^m\left(P,\stackrel{.fwdarw.}{n}\right)$
of reflections of the wave where

The present application describes a magneto-optical based guided waves system for inspection and monitoring of assets. The system has a magnetostrictive-based wave emitter for signal generation and a network of optical fiber sensors for detection, both mechanically coupled to the asset, a device with embedded software for hardware control and signal processing, and a framework capable of providing visual and analytic insights about the condition of the structure of interest. The enhancement of flaw detection, location and characterization abilities of the system are obtained through the use of high sensitivity and passive fiber optics sensors with very small size, distributed and multi-parameter sensing capabilities.

According to embodiments, an ultrasonic inspection apparatus comprises: an ultrasonic array probe having a plurality of ultrasonic elements; an estimated shape reflected wave arrival time calculator for computing the estimated shape reflected wave arrival time for the estimated shape reflected wave on the basis of the estimated sound velocity in the test object; an actual shape reflected wave arrival time extractor for extracting the actual shape reflected wave arrival time on the basis of the actual shape reflected wave; a shape reflected waves time difference calculator for computing the difference by subtracting the actual shape reflected wave arrival time from the estimated shape reflected wave arrival time as shape reflected waves time difference; and a delay time calculator for computing the delay times for mutually shifting the timings of ultrasonic wave transmission and ultrasonic wave reception by the ultrasonic elements, considering the shape reflected waves time differences.

According to embodiments, an ultrasonic inspection apparatus comprises: an ultrasonic array probe having a plurality of ultrasonic elements; an estimated shape reflected wave arrival time calculator for computing the estimated shape reflected wave arrival time for the estimated shape reflected wave on the basis of the estimated sound velocity in the test object; an actual shape reflected wave arrival time extractor for extracting the actual shape reflected wave arrival time on the basis of the actual shape reflected wave; a shape reflected waves time difference calculator for computing the difference by subtracting the actual shape reflected wave arrival time from the estimated shape reflected wave arrival time as shape reflected waves time difference; and a delay time calculator for computing the delay times for mutually shifting the timings of ultrasonic wave transmission and ultrasonic wave reception by the ultrasonic elements, considering the shape reflected waves time differences.

An acoustic air data sensor for an aircraft includes an acoustic transmitter, an acoustic receiver, an acoustic signal generator, timing circuitry, speed of sound determination circuity, and communication circuitry. The acoustic transmitter is located to transmit an acoustic signal through an airflow stagnation chamber that is pneumatically connected to an exterior of the aircraft and configured to receive and stagnate airflow from the exterior of the aircraft. The acoustic receiver is positioned at a distance from the acoustic transmitter to receive the acoustic signal. The pulse generator causes the acoustic transmitter to provide the acoustic signal. The timing circuitry determines a time of flight of the acoustic signal from the acoustic transmitter to the acoustic receiver. The speed of sound determination circuity determines, based on the time of flight and the distance, a speed of sound through air in the stagnation chamber. The communication circuitry outputs the speed of sound.

A method of processing data for a driving automation system, the method comprising steps of: obtaining sound data from a microphone of an autonomous vehicle; processing the sound data to obtain a sound characteristic; and updating a context of the autonomous vehicle based on the sound characteristic.

A gas analyzer uses continuous sonic signals through a conduit to determine the composition of a gas in the conduit. A transmitting transducer drives sonic signals at a fixed frequency and a second transducer receives the sonic signals. The phase shift between two signals corresponds to the speed of sound through the gas and is related to the composition of the gas. The electronic versions of these signals are processed by lowering, or dividing, the fixed frequency which expands the range of phase shift measurement and allows the determination of an expanded range for the gas composition. In an ozone generation system, the gas analyzer is highly suitable for determining the composition of gases derived from air as a gas of known composition and a calibration point.

Aerial vehicles may be outfitted with one or more ultrasonic anemometers, each having ultrasonic transducers embedded into external surfaces. The transducers may be aligned and configured to transmit acoustic signals to one another, and receive acoustic signals from one another, along one or more paths or axes. Elapsed times of signals transmitted and received by pairs of transducers may be used to determine air speeds along the paths or axes. Where two or more pairs of transducers are provided, a net vector may be derived based on air speeds determined along the paths or axes between the pairs of the transducers, and used to generate control signals for maintaining the aerial vehicle on a desired course, at a desired speed or altitude, or in a desired orientation. The transducers may be dedicated for use in an anemometer, or may serve multiple purposes, and may be reoriented or reconfigured as necessary.

Aerial vehicles may be outfitted with one or more ultrasonic anemometers, each having ultrasonic transducers embedded into external surfaces. The transducers may be aligned and configured to transmit acoustic signals to one another, and receive acoustic signals from one another, along one or more paths or axes. Elapsed times of signals transmitted and received by pairs of transducers may be used to determine air speeds along the paths or axes. Where two or more pairs of transducers are provided, a net vector may be derived based on air speeds determined along the paths or axes between the pairs of the transducers, and used to generate control signals for maintaining the aerial vehicle on a desired course, at a desired speed or altitude, or in a desired orientation. The transducers may be dedicated for use in an anemometer, or may serve multiple purposes, and may be reoriented or reconfigured as necessary.

An acoustic air data sensing system includes an acoustic transmitter, a plurality of acoustic receivers, and a skin friction sensor. The acoustic transmitter is located to transmit an acoustic signal into airflow about an exterior of a vehicle. Each of the acoustic receivers is located at a respective angle from a wind angle reference line and a respective distance from the acoustic transmitter. The skin fiction sensor is positioned in a boundary layer region of the airflow that interacts with the acoustic receivers and transmitter. Based on time of flight values of the acoustic signal from the transmitter to each of the receivers and a skin friction measurement from the skin friction sensor as inputs to a transformation matrix, the acoustic air data sensing system outputs, from the transformation matrix, the true airspeed, the relative wind angle, and the speed of sound for operational control of the vehicle.