A device for detecting anomalies in an aircraft turbine engine by acoustic analysis, the device not an onboard device and including: a mobile module including a directional system for acquiring acoustic signals from the turbine engine; a processor for processing the signals, which is suitable for generating a damage report; a transmitter for transmitting the damage report; a server capable of exchanging data with the mobile module, the server including a receiver for receiving the damage report; and a storage device suitable for storing the damage report.

A device for detecting anomalies in an aircraft turbine engine by acoustic analysis, the device not an onboard device and including: a mobile module including a directional system for acquiring acoustic signals from the turbine engine; a processor for processing the signals, which is suitable for generating a damage report; a transmitter for transmitting the damage report; a server capable of exchanging data with the mobile module, the server including a receiver for receiving the damage report; and a storage device suitable for storing the damage report.

A shaker test system with a class D power amplifier having an analog to digital converter to receive an analog input signal and convert the analog input signal to a digital signal, pulse width modulation logic coupled to the analog to digital converter to provide a delay time to a delay line to control a transition time of a pulse width modulated signal responsive to an output of the analog to digital converter, and a class D power output stage coupled to the delay line and responsive to the pulse width modulated signal to provide an output of the class D power amplifier stage. The class D amplifier allows use of a low cost microcontroller to obtain very small pulse width increments using a low cost microcontroller to provide a low cost shaker test system incorporating the class D power amplifier.

A detection system 1 contains a sensing device 10 including a vibration unit 11 for applying vibration to the inspection target 100, the vibration unit 11 attached to the inspection target 100, a driving circuit 12 for supplying an electric signal to the vibration unit 11 for driving the vibration unit 11 and a sensor 13 for detecting vibration of the inspection target 100 caused by the vibration applied from the vibration unit 11; and a detection processing device 20 for receiving vibration information related to the vibration of the inspection target 100 detected by the sensor 13 from the sensing device 10 and detecting the state change of the inspection target 100 based on the vibration information. The vibration unit 11 includes a coil 112, a spring 113, and a magnet 114b.

An instrument for performing order analysis on a rotational machine. An input module receives periodic motion data, and machine characteristic data that is associated by time with the periodic motion data. A processor module receives the periodic motion data and the machine characteristic data, applies a Goertzel module to the periodic motion data and the machine characteristic data, and thereby creates an order data set comprising magnitude of machine characteristic data versus order of normalized periodic motion data.

An impact test system includes a head model having a head exterior component; a skull component; a brain component; a fluid component; an interior cavity surface; and a translucent cover, wherein the head model is coupled with a mount, the brain component and fluid components are configured within the interior cavity, and wherein the translucent cover is configured over a portion of the brain component and fluid component. A mount is configured to a least partially restrain the head model. A camera is configured to take a plurality of images of the brain and the fluid components through the translucent cover when the head model is under an impact force.

A method for characterizing a spot weld, including acquiring a sequence of A-scans from an ultrasonic phased array, wherein the A-scans describe individual portions of a field of view of the phased array; manually applying an interface gate and a flaw gate to each individual A-scan within the sequence of A-scans; calculating a gate ratio between a maximum amplitude under the interface gate and a maximum amplitude under the flaw gate for each individual A-scan; plotting the gate ratio for each individual A-scan as a function of location within the phased array field of view to generate a weld fusion map; using a predetermined threshold to differentiate fused locations from unfused locations on the weld fusion map; and calculating predetermined weld metrics, wherein the predetermined weld metrics include area, diameter, width, length, percent fused, or combinations thereof.

The present disclosure relates to the technical field of aerodynamic and acoustic measurement, in particular to a comprehensive performance test platform for acoustic liner. Based on this comprehensive performance test platform for acoustic liner, the stress of the measured acoustic liner under high sound intensity can be measured by using strain gauges arranged on the measured acoustic liner, the aerodynamic drag of the measured acoustic liner can be measured by using the drag balance, and the acoustic performance parameters of the measured acoustic liner can be calculated based on the sound pressure data obtained by the microphone array. With this test platform, the stress, the aerodynamic drag and the acoustic performance parameters of the measured acoustic liner can be measured simultaneously, which overcomes the problem of inaccurate experimental data obtained in inconsistent experimental conditions caused by conventional separate acoustic liner tests.

A method of evaluating a structural integrity of an aerial vehicle comprising one or more engines comprises selectively driving said engine/s of said aerial vehicle according to a driving pattern unsuitable to put or maintain the aerial vehicle in flight, recording a vibrational response of at least a part of the aerial vehicle to said selective driving of said engine/s, determining a plurality of modal parameters of said vibrational response, in particular an eigenfrequency of said vibrational response and/or a damping factor corresponding to said eigenfrequency, and classifying said structural integrity based on a deviation of said plurality of modal parameters from baseline modal parameters for said aerial vehicle.

The method for examining a clinched portion of a tubular body includes the steps of: giving an elastic vibration to a clinched body 90 formed by clinching a tubular body 91 with a clinch-target member 92; and acquiring, for each of a plurality of view areas 95 which differ from each other in the position in the circumferential direction of the tubular body 91, a vibration distribution optically and simultaneously measured within the view area 95 including a clinched portion 93 of the tubular body 91 and the clinch-target member 92, to determine whether or not the state of clinching is satisfactory over the entire clinched portion 93.