| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 073583000 | Of aircraft or related structural element | 10 |
| 20100011861 | DEVICE FOR NON DESTRUCTIVE TESTING OF A COMPONENT BY ANALYZING RADIATION DISSIPATION - A device for non-destructive testing of a component by analyzing radiation dissipation when the component is stressed by mechanical stresses. The device includes measuring means for determining a surface radiation field of the component. The measuring means are integrated in a flexible housing for covering a region of the surface of the component to be tested. The device enables an initial crack upon stress concentration on a surface of the component and the presence of a crack upon propagation of the crack to be detected. The disclosed embodiments are useful for non-destructive testing of aircraft components, but may be used in all industrial sectors where testing the integrity of components is important, such as the automotive, railway, marine and nuclear industries. | 01-21-2010 |
| 20110030476 | LASER ULTRASONIC MULTI-COMPONENT IMAGING - 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. | 02-10-2011 |
| 20110146406 | METHODS AND APPARATUS FOR VIBRATION TESTING USING MULTIPLE SINE SWEEP EXCITATION - 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. | 06-23-2011 |
| 20110219878 | METHOD AND APPARATUS FOR MEASURING THE STRUCTURAL INTEGRITY OF A SAFE-LIFE AIRCRAFT COMPONENT - 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. | 09-15-2011 |
| 20130340528 | DEVICE FOR EXCITING A LANDING GEAR OF AN AIRCRAFT WHILE ON THE GROUND - 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. | 12-26-2013 |
| 20140053649 | MONITORING UNIT AND METHOD FOR DETECTING STRUCTURAL DEFECTS WHICH CAN OCCUR IN AN AIRCRAFT NACELLE DURING USE - 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. | 02-27-2014 |
| 20140202248 | IMPACT DETECTION AND ACOUSTIC EMISSION DATA PROCESSING - A method and apparatus for processing measurements of an acoustic wave, the acoustic wave being within a member ( | 07-24-2014 |
| 20140311244 | DEVICES, SYSTEMS AND METHODS OF DETECTING DEFECTS IN WORKPIECES - Device and method for detecting a defect in a workpiece with a broadband transducer ( | 10-23-2014 |
| 20160061686 | VIBRATION EXCITATION SYSTEM FOR AIRCRAFT AND AIRCRAFT - 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. | 03-03-2016 |
| 20160076931 | ASSEMBLY AND METHOD OF COMPONENT MONITORING - A method of component monitoring for machinery having multiple rotating elements, which are rotated at different rotational speeds, the method including sampling data from the vibration sensor at a sampling frequency at least as great as the fastest rotational speed of the multiple rotating elements to form a data set and determining an actual rotational frequency for at least some of the rotating elements during the sampling of the data. | 03-17-2016 |
