Abstract: An autonomous impact detection device includes at least one impact detector; at least one wireless transmission device configured to transmit the information collected by the impact detector; at least one energy storage device configured to supply the impact detector and the wireless transmission device with energy; at least one Seebeck module configured to supply the storage device with energy when a temperature gradient is applied thereto; the wireless transmission device being configured to supply the storage device with energy when the temperature gradient to which the Seebeck module is exposed is not sufficient.

Abstract: A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

Abstract: A magneto acoustic emission detection method for fatigue damage of ferromagnetic metal components: First, generating an excitation magnetic field by using a sine wave voltage signal, gradually increasing a loading voltage until a magneto acoustic emission signal of a bimodal envelope with an obvious tail peak is acquired, and taking a corresponding voltage peak value as a reference voltage; second, generating an excitation magnetic field by using a square wave voltage signal equal to or higher than a reference voltage, and acquiring a magneto acoustic emission signal with a T-shaped envelope; and third, calculating the average value of peak-to-peak values of the magneto acoustic emission signal in multiple periods to serve as a characteristic parameter, and enabling the characteristic parameter to have inflection point change along with the development of the initiation and expansion of the fatigue crack, and giving a timely early warning for the failure of the component.

Abstract: The invention relates to a method for handling a rectifier of a turbojet of an aircraft, the rectifier having an axis defining the asymmetry thereof, said method comprising a step of placing the rectifier on the rollers of a supporting structure, the structure and the rollers thereof being arranged such that the axis of the rectifier is inclined at a non-null acute angle in relation to the horizontal, and a step of controlling, maintaining, assembling, handling, storing, deburring and/or cleaning the rectifier, during which the rectifier is pivoted about the axis thereof. The invention also relates to a trolley for handling a rectifier for an axial turbojet, said trolley comprising at least two of the lower rollers that have axes inclined in relation to the horizontal of said angle and at least one upper roller, the axis of which is inclined in relation to the vertical of said angle.

Abstract: The application relates to an apparatus (100) for fatigue testing a wind turbine blade specimen (10), and to a method using such an apparatus (100). The apparatus (100) comprises first and second support assemblies (120, 130) and an actuator (140) for cyclically deflecting the specimen (10) in a first transverse direction. The first and second support assemblies (120, 130) comprise first and second holders (121, 131) for holding first and second ends (12, 14) of the specimen (10), respectively, such that the longitudinal direction (16) of the specimen (10) extends between the first and second holders (121, 131). The first and second support assemblies (120, 130) are arranged such that the first and second holders (121, 131) are rotatable about a second transverse direction perpendicular to the first transverse direction and to the longitudinal direction (16) of the specimen (10).

Abstract: A sound measurement system intended to be installed on a motor vehicle, the system comprising: a microphone, an element for supporting the microphone, mechanical means for protecting the microphone against various projections (water, dust, etc.) from the environment of the vehicle, and mechanical means for protecting the microphone from airborne noise originating from the routing of the sound wave between the source and the measurement (cavity noise) and from the environment of the measuring system (turbulence around the measuring device), the various mechanical protection means being separate or combined. A motor vehicle may be provided with such a system.

Abstract: Methods, apparatus, and articles of manufacture are disclosed. An example apparatus includes a pre-amplifier to condition an acoustic emission signal based on an acoustic emission source, a demodulator to generate demodulated acoustic emission data based on combining the acoustic emission signal with a chirp signal, and a transmitter to transmit the demodulated acoustic emission data to a data acquisition system.

Abstract: The current disclosure determines if structural faults exist and extracts geometric features of the structural faults from acoustic emission waveforms, such as crack length and orientation, and can evaluate the structural faults online, during normal operation conditions.

Abstract: A device and method for detecting delamination in a panel of laminated composite. The device comprises an ultrasonic probe with a plurality of elementary transducers, an electronic device in communication with the elementary transducers, and a display device. The transducers emit an ultrasonic pulse and receive a pulse reflected by an element in the panel. The received pulses are grouped into clusters of healthy, or non-damaged, zones and damaged zones. The dimensions of the damaged zones are based upon the limits formed by healthy zones. A display of the defect with dimensions is produced on the display device. A scale image of the defect with dimensions, via paper or digital overlay, can be placed on the panel.

Abstract: An assembly for demonstrating sound transmission properties includes a base portion and a tray portion partially defining a transmission aperture is removably inserted into a portion of the base portion. A first sound-reducing tile having a first sound transmission property is placed in the tray portion and a sound generating device disposed in an interior volume of the base portion emits sound that is attenuated by the first sound-reducing tile as the sound exits the transmission aperture. A second sound-reducing tile having a second sound transmission property is placed in the tray portion and the sound generating device disposed in the interior volume of the base portion emits sound that is attenuated by the second sound-reducing tile as the sound exits the transmission aperture. A sound measuring device disposed outside the interior volume device can compare the first and second sound transmission properties.

Abstract: An example modular environmental control chamber (MECC) includes an outer chamber formed by an outer chamber housing section enclosing an outer face of a section of fuselage and an inner chamber formed by an inner chamber housing section enclosing an inner face of the section of fuselage. An outer chamber airflow delivery and return system includes an outer chamber blower for directing temperature-controlled air to the outer chamber through an air inflow aperture of the outer chamber housing section and an outer chamber air return duct connected to an air outflow aperture of the outer chamber housing section. An inner chamber airflow delivery and return system includes an inner chamber blower for directing humidity-controlled air to the inner chamber through an air inflow aperture of the inner chamber housing section and an inner chamber air return duct connected to an air outflow aperture of the inner chamber housing section.

Abstract: Various embodiments include apparatuses for performing maintenance on a gas turbine (GT) nozzle, along with related methods. One apparatus can include: a nozzle engagement sled for releasably engaging the nozzle, the nozzle engagement sled including: a sled body; a locking member coupled with the sled body, the locking member sized to complement a slot in the nozzle; a sled slot within a side of the sled body, the sled slot for engaging a rail within the GT; and at least one wheel for transporting the sled body within the GT.

Abstract: A method for estimating rotational speed of a system includes receiving vibrational data from a sensor, estimating a speed from the vibrational data to create estimated speed data, and filtering the estimated speed data through an adaptively weighted filter to minimize incorrect speed estimation.

Abstract: A system for supporting maintenance of an aircraft is provided. The system includes a plurality of database importers. The database importers import a plurality of datasets from a plurality of data sources to a database with a composite dataset including data of the plurality of datasets. The system also includes a database-management system (DBMS) to manage the database. The system further includes a client application coupled to the DBMS. The client application receives a user request for a demand for replacement aircraft parts for maintenance during an in-service lifecycle of the aircraft. In response to the user request, the client application predicts and thereby produces a prediction of the demand based on the data retrieved from the composite dataset.

Abstract: A characteristic of a component having an engineered internal space can be analyzed by recording acoustic signals produced by fluid flow through the internal space at controlled flow rates, and determining one or more acoustic frequencies and acoustic intensities that are indicative of the characteristic of the component. A state and/or a source of the component can be predicted based on the results of such analysis.

Abstract: To provide an aircraft strength testing apparatus that, using a curved specimen, can produce a desired stress safely and quickly by reliably applying an internal pressure, and moreover allows any resulting damage to be reliably observed. A testing apparatus 1 that applies an internal pressure, equivalent to a differential pressure between the outside and the inside of a section to be tested of a fuselage of an aircraft, to a curved specimen 10 corresponding to the section to be tested, includes: a pressure vessel 22 between which and the specimen 10 a cavity 23 is formed; and rods 25 that restrain the specimen 10 against the internal pressure. The pressure vessel 22 faces the outer side of the specimen 10. By reducing the pressure inside the cavity 23, an internal pressure is applied to the specimen 10.

Abstract: A structural health management system may include a structural health management apparatus including a carbon nanotube element configured to generate an electrical output in response to a deformation of the carbon nanotube element, a piezoelectric element configured to actuate in response to an electrical voltage applied to the piezoelectric element, electrode elements coupled to the carbon nanotube element and the piezoelectric element, and a controller communicatively coupled to the structural health management apparatus, wherein the controller is configured to convert the electrical output into data representing a measurement value of a structural abnormality and to initiate application of the electrical voltage to the piezoelectric element to counter the structural abnormality upon the measurement value being equal to or greater than a predetermined threshold value.

Abstract: The present invention provides a vibration excitation system which allows a vibration exciter to be easily mounted on/removed from a wing. The present invention is a vibration excitation system for an aircraft which imparts vibration to a main wing of an aircraft subjected to a test flight, for evaluation of vibration resistance to flutter. A vibration exciter which generates vibration is removably mounted on the main wing through a fixing structure. It is preferable that the fixing structure transmit the vibration of the vibration exciter as a shearing force to a front spar and a rear spar of the main wing.

Abstract: A system for reconstructing sensor data in a rotor system that comprises a rotating component of the rotor system, a plurality of sensors in the rotating component to sense at least one of loads and motion characteristics in the rotating component and to generate sensor data, and an analysis unit to generate reconstructed sensor data from the sensor data using numerical analysis for low-rank matrices.

Abstract: A resonant frequency testing system for airfoils comprises a broach block, a clamp, an acoustic speaker, a laser vibrometer, and a control processor assembly. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp has a torque-actuated shutoff, and is disposed to lock the airfoil in the broach block slot under a fixed clamping force. The acoustic sensor is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer is oriented towards the airfoil location to sense vibration signatures of the airfoil when excited by the sonic pulses. The control processor assembly is configured to control the acoustic speaker and laser vibrometer, to decompose the sensed vibration signatures into resonant frequencies of the airfoil, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil.

Abstract: A method and a system for inspection of gas turbine are presented. An inspection tool is attached on a track which is permanently positioned on site with respect to the gas turbine. The inspection tool includes an extendible shaft with a proximal end attached on the track and a distal end carrying a sensor. The inspection tool moves along the track for accessing an inspection port of the gas turbine by the shaft. A control system is coupled to the inspection tool for controlling the inspection tool for the inspection of the gas turbine. The method and system enable an automated engine inspection which allows for the engine to have been inspected and reviewed by an engineer without having to send the engineer on site.

Abstract: Methods and systems for automated asset tracking within an aircraft are disclosed. In one example, a method for use in automated tracking of assets in a vehicle utilizing a robotic vehicle is provided. The method includes receiving inspection data concerning the vehicle and the assets. A navigation path is generated thorough the vehicle. The robotic vehicle traverses the navigation path and locates at least one asset with the vehicle along the navigation path. An identification of the asset located within the vehicle is transmitted to a remote computing device and stored in a database associated with the remote computing device.

Abstract: A method and apparatus for inspecting an object is provided. Movement of inspection vehicles relative to a surface of the object is controlled using a controller. Generation of data about the object by sensor systems configured to generate the data when the sensor systems are in a configuration with respect to a location on the object for inspection and receiving power from the inspection vehicles is controlled using the controller. The data generated by the sensor systems is stored.

Abstract: Device and method for detecting a defect in a workpiece with a broadband transducer (10), a driving circuit connected to the transducer to operate the transducer in a actuator mode, a signal output circuit connectable to operate in a sensor mode, a control for selectively connecting the transducer to the driving circuit or signal output circuit wherein the driving circuit includes at least a pair of oscillators for generating signals of at least frequencies F1 and F2 and a summer for summing the signals to provide a driving circuit for the transducer.

Abstract: An apparatus for lifting an aircraft may include a plurality of lifting mechanisms mounted on a supporting surface. Each lifting mechanism may be configured to impart an upward force on a component of the aircraft for lifting the aircraft off the supporting surface. The apparatus may include a beam structure configured to be mounted to the lifting mechanisms. The apparatus may also include a lifting beam suspended from the beam structure. A measurement device may be mounted to the lifting beam and may be configured to engage a jack point associated with the component to determine a weight of the aircraft when the aircraft is lifted off the supporting surface.

Abstract: A method and apparatus for processing measurements of an acoustic wave, the acoustic wave being within a member (12) made of a composite material and caused by an impact to the member (12), the method comprising: analysing the measurements to detect an initial acoustic wave feature; analysing the measurements to detect the presence of further acoustic wave features, the further features occurring after the initial feature; if there are no further acoustic wave features, determining that the impact to the member (12) has not changed the structure of the member (12); if there are further features, determining a value of a function of the further acoustic wave features; if the determined value satisfies certain criteria, determining that the impact has changed the structure of the member (12); and if the determined value does not satisfy the criteria, determining that the impact has not changed the structure of the member (12).

Abstract: A defect detection system and method enable a fastened crystalline silicon product to generate micro-vibration by a micro-vibration excitation device, so as to enable the crystalline silicon product to generate an excitation signal, then to acquire the excitation signal by a acquisition device, so as to analyze the excitation signal acquired by the acquisition device in the time and frequency domain by an analysis detection device with a specific analysis, and to obtain an analysis result, at last, determine a defect state of the crystalline silicon product according to the analysis result.

Abstract: The present disclosure relates to a monitoring assembly for detecting structural detects. The monitoring assembly includes a composite sandwich structure with two distinct strata, a calculation unit and a plurality of sensors for generating signals representative of an amplitude or frequency of vibrations produced in a structure. Each sensor is formed by an electromechanical microsystem including a converter for converting mechanical energy into electrical energy. In particular, the calculation unit evaluates differences between a current transfer function resulting from the signals and a predetermined nominal transfer function, compares each of the differences with a respective detection threshold, and evaluates a size or a position of the structural defect in the structure.

Abstract: A device for exciting a landing gear of an aircraft while it is on the ground. The device includes an oblong bracing foot, a movable support on which the oblong foot is mounted and an arrangement for setting the gear into vibration.

Abstract: The present invention relates to a method of monitoring the effectiveness of a damper system, wherein the method consists in measuring the relative movements of two strength members, in filtering the measurements in order to isolate those that relate to the lead-lag resonant frequency of the blade, in rectifying the signal, in recording the signal, in comparing the rectified signal (S) with a threshold value (SL), in determining an initial time interval (T0) as soon as the rectified signal exceeds the threshold value (SL), in calculating the integrals of the signal from T0 to T0+? and from T0 to T0+p?, in calculating the ratio R of the integrals, and in comparing the ratio R with a limit value RL, and in activating and delivering an alert signal (V1) if the ratio R is greater than or equal to the limit value RL.

Abstract: In-line inspection methods are provided. The methods comprise measuring at least two parameters/properties of a prepreg and/or laminate during the manufacture thereof. In some embodiments, the data collected using the inline inspection methods may be processed and/or provided to a manual or automated controller, in order to provide a closed loop method for the manufacture of the prepregs and/or laminates. Apparatus for carrying out the methods are also provided, as are articles comprising a prepreg and/or laminate made using the apparatus.

Abstract: Nondestructive inspection of a plurality of aircraft hat stiffeners includes exciting cavities of the stiffeners with electromagnetic radiation, and analyzing electromagnetic field responses of the cavities to detect state changes of the stiffeners.

Abstract: A structural health monitoring system using ASICs for signal transmission, reception, and analysis. Incorporating structural health monitoring functionality into one or more ASICs provides a durable yet small, lightweight, low cost, and portable system that can be deployed and operated in field conditions. Such systems provide significant advantages, especially in applications such as armor structures.

Abstract: A safety system for testing high-pressure devices comprising an explosion-proof safety housing; a high-pressure pneumatics testing equipment located within the housing; a closeable access opening in the housing for inserting a high-pressure device for testing within the housing; a device located within the housing for coupling the high-pressure pneumatics testing equipment to the high-pressure device for testing; a control panel located outside the housing; and a device linking the high-pressure pneumatics testing equipment to the control panel for operating the high-pressure pneumatics testing equipment within the safety housing from the control panel.

Abstract: The invention relates to improved methods and apparatus for performing ground vibration tests (so-called “ground vibration tests”) on an airplane. In the method according to the invention, the airplane is jacked up essentially undamped (“rigidly”) in conventional holding points with lifting devices. For purposes of the ground vibration test, the airplane is then excited to vibrate in a known manner using a plurality of vibration exciters, and the vibrations are acquired with a plurality of measuring transducers, in particular accelerometers. A dynamic vibration model of the airplane theoretically calculated beforehand can here be adjusted. The boundary conditions are removed during or after the ground vibration test, meaning the influence of the lifting device is “mathematically canceled out”, so that the determined measured values reflect the so-called “free-free” state of the airplane, as if the airplane had actually been in free flight during the ground vibration tests.

Abstract: The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).

Abstract: An apparatus for inspecting samples that may include a curvature that varies from sample to sample comprises a scanning element, a feed mechanism, and a pivot mechanism. The scanning element transmits and receives a signal to and from the sample as the sample passes by, thereby building an image or profile of the sample. The feed mechanism includes a drive motor coupled to a series of pulleys and belts that form an open-ended chain. The pulleys rotate when driven by the drive motor and are coupled to an array of rollers that rotate as well to propel a inspection sample past the scanning element. The pivot mechanism includes a series of primary and secondary links that also form an open-ended chain. The primary links are coupled to the rollers and the combination pivots in unison to form an arc that matches the curvature of the sample in order to maintain a fixed distance between the sample and the scanning element.

Abstract: The structural integrity of a safe-life aircraft component on an aircraft is measured and assessed by a processing unit. The component includes a load-bearing metal element that is free from cracks. In the method, acoustic emissions generated in the metal element are converted into electronic signals. The acoustic emissions converted include relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks. The electronic signals are set to a processing unit. The processing unit processes over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made. Information providing a measure of the structural integrity of the aircraft component is outputted. Thus, deterioration of the structure of the component can be detected and monitored before a crack occurs.

Abstract: A multi-sine vibration testing method includes coupling a vibratory excitation source and a sensor to a test structure, then providing a reference signal to the excitation source, wherein the reference signal comprises a first sinusoidal waveform having a first frequency and a second sinusoidal waveform having a second frequency different from the first frequency. The first frequency and the second frequency each sweep between a corresponding start value and a corresponding end value, and the frequency response is measured from each of the sensors while providing the reference signal.

Abstract: A system for monitoring the free play in aircraft control surfaces includes one or more accelerometers secured in or on the aircraft control surfaces and a computer system connected to the one or more accelerometers and to one or more control surface actuators to selectively activated to selectively activate a control surface and send a reading from the control surface to the computer system. The computer system includes means to plot the readings from the one or more accelerometers on the control surfaces to plot a curve of the free play in the selected control surface. The method of the invention utilizes the one or more accelerometers placed in or on the aircraft control surfaces and connects them to the aircraft's flight control computer or a similar computer to receive signals originated by vibrating the control surfaces and plotting curves of the free play measured in the control surfaces.

Abstract: A structural health monitoring system and method uses a resonant transmission line sensor. A resonant transmission line sensor, which includes one or more sensor conductors and a dielectric material disposed at least proximate the one or more sensor conductors, is coupled to the structure. The dielectric material exhibits a dielectric constant that varies when at least a portion of the transmission line sensor is subjected to one or more stimuli. One or more resonant frequencies of the transmission line sensor are determined, and the determined one or more resonant frequencies are then correlated to the structural health of the structure.

Abstract: Techniques for ultrasonic determination of the interfacial relationship of multi-component systems are discussed. In implementations, a laser energy source may be used to excite a multi-component system including a first component and a second component at least in partial contact with the first component. Vibrations resulting from the excitation may be detected for correlation with a resonance pattern indicating if discontinuity exists at the interface of the first and second components.

Abstract: An apparatus for inspecting samples that may include a curvature that varies from sample to sample comprises a scanning element, a feed mechanism, and a pivot mechanism. The scanning element transmits and receives a signal to and from the sample as the sample passes by, thereby building an image or profile of the sample. The feed mechanism includes a drive motor coupled to a series of pulleys and belts that form an open-ended chain. The pulleys rotate when driven by the drive motor and are coupled to an array of rollers that rotate as well to propel a inspection sample past the scanning element. The pivot mechanism includes a series of primary and secondary links that also form an open-ended chain. The primary links are coupled to the rollers and the combination pivots in unison to form an arc that matches the curvature of the sample in order to maintain a fixed distance between the sample and the scanning element.

Abstract: A solution for monitoring a property of an object and/or an area using a Micro-ElectroMechanical Systems (MEMS)-based monitoring device is provided. In an embodiment of the invention, the MEMS-based monitoring device includes a MEMS-based sensing device for obtaining data based on a property of the object and/or area and a power generation device that generates power from an ambient condition of the monitoring device. In this manner, the monitoring device can operate independent of any outside power sources or other devices. Further, the monitoring device can include a transmitter that transmits a signal based on the property. The monitoring device can be used to monitor a moving component of a machine, and can be integrated with a health monitoring system of the machine using one or more relay devices.

Abstract: A computer implemented method, apparatus, and computer usable program code for testing a material. A signal is sent into the material using the transmitter. The signal has a frequency range that falls within a selected frequency range to form a transmitted signal. An actual response to the transmitted signal is received at a sensor. A simulated response of the material to the transmitted signal is generated using a functional model capable of modeling responses of the material to different frequency ranges falling within the selected frequency range. The simulated response is compared to the actual response to determine if a change has occurred in the material.

Abstract: In an embodiment, an apparatus and method capable of determining the time and location of a projectile's impact is disclosed. In another embodiment, an apparatus and method capable of determining the time and location of a projectile's impact as well as the direction from whence the projectile came is disclosed.

Abstract: The present invention pertains to apparatus and methods for measuring elastic modulus (Young's modulus) of non-solid materials, including honeycomb ceramic materials used in the filtration and/or treatment of exhaust gasses, through a range of temperatures.

Abstract: An apparatus for detecting the presence of ice includes a sensory circuit including a sensor operable to be coupled to a surface exposed to moisture. The sensory circuit is operable to create an electromagnetic standing wave. A heating element is coupled to the surface and a first transmission line. A first source is coupled to the first transmission line and is operable to inject a driving signal into the first transmission line, the driving signal being operable to drive the heating element. A mixing element is coupled to the sensory circuit and first transmission line and is operable to produce a mixed signal from the driving signal and a measure of the standing wave. A comparator is operable to compare at least one characteristic of the mixed signal with reference data for determining the presence of ice contacting the sensor.

Abstract: Embodiments of the present invention relate to a device which may be permanently attached or removably attached to a material such as a vehicular glass window or airplane wing. This device may comprise of a converter sub-unit or vibrator and a coupler. These elements may be arranged to propagate mechanical motion generated by the converter sub-unit through the coupler and optionally into the edge of the attached material. The resulting vibration motion in the material, which could take the form of a longitudinal compression/rarefaction wave, transverse wave, or a combination of the two waveforms, may be of a sufficient magnitude so as to cause the adhesive bond between the material's surface and other solid debris, such as ice, to be broken. This allows the debris to fall away while not damaging the material. The vibration motion in the material may be also of sufficient magnitude to remove a liquid such as water from the material surface.

Abstract: An apparatus for detecting the presence of ice includes a sensor including a radio-frequency transmission line providing a characteristic impedance, a source coupled to the transmission line and operable to inject a wave into the transmission line, a summer operable to create standing wave, the standing wave including the sum of the injected wave and a reflected wave reflected by the end of the transmission line, the summer being connected between the source and the transmission line, and a detector for detecting the voltage of the standing wave. An embodiment may further include a comparator operable to compare the detected voltage with reference data for determining the presence of ice contacting the sensor.