Abstract: A sensor is fixed on an aircraft structure by a joining system which includes at least one enclosure in which is positioned at least one transducer, at least one passage configured to allow at least one conducting element to pass through the enclosure, at least one flexible connection connecting each transducer present in the enclosure to said enclosure and at least one binder joining together the enclosure and the structure. This joining system makes it possible to limit the spread of the deformations of the structure toward the transducer or transducers and ultimately the risks of malfunction.

Abstract: A sensor is fixed on an aircraft structure by a joining system which includes at least one enclosure in which is positioned at least one transducer, at least one passage configured to allow at least one conducting element to pass through the enclosure, at least one flexible connection connecting each transducer present in the enclosure to said enclosure and at least one binder joining together the enclosure and the structure. This joining system makes it possible to limit the spread of the deformations of the structure toward the transducer or transducers and ultimately the risks of malfunction.

Abstract: The invention relates to a device for the detection of defects in a recess, comprising a longitudinal hollow body (107), a movement conversion means (109) housed in said body (107) and installed free to move along the longitudinal direction, and at least one sensor (11) coupled to said body (107) and to said conversion means (109) such that longitudinal translation of the conversion means will move said sensor (11) in transverse translation between a retracted position and an extended position.

Abstract: The invention relates to a non-destructive inspection method using eddy currents for detecting flaws in a metal structure (3) by means of an array (5) of coils attached to a surface (31) of said structure (3) comprising activation of the coils, measurement of the electrical signals representative of the eddy currents, and evaluation over time of a variation in the electrical signal of each of the coils (511-536) by taking as a reference an edge effect corresponding to a specific electrical signal emanating from at least one coil installed at the edge of the surface, the level of said variation being indicative of the presence of the flaws in the structure.

Abstract: A device for non-destructive control of a component analyzes distribution of a leakage magnetic field emitted by the component when it is subjected to an exciting magnetic field, includes means for generating an exciting magnetic field inside the component to be tested, and means for detecting and measuring the distribution of the magnetic field. The set of means is integrated in a flexible housing to form a device in the form of a flexible coating for being fixed on a region of the surface of the component to be tested. The disclosed embodiments are useful for non-destructive testing of aircraft components, but may also be used in all industrial sectors where testing the integrity of components is important, such as the automotive, railway, marine or nuclear industry.

Abstract: The invention relates to a device for the detection of defects in a recess, comprising a longitudinal hollow body (107), a movement conversion means (109) housed in said body (107) and installed free to move along the longitudinal direction, and at least one sensor (11) coupled to said body (107) and to said conversion means (109) such that longitudinal translation of the conversion means will move said sensor (11) in transverse translation between a retracted position and an extended position.

Abstract: 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.

Abstract: A device for non-destructive testing of a structure likely to contain a defect, including microsensors for measuring vibratory waves emitted by the structure at different points of a surface of the structure, the aforementioned microsensors being integrated in a flexible housing capable of adhering on the surface of the structure to be tested. The disclosed embodiments are applicable to all industrial sectors where testing of the integrity of structures is important, in particular in areonautics.

Abstract: The invention relates to a non-destructive inspection method using eddy currents for detecting flaws in a metal structure (3) by means of an array (5) of coils attached to a surface (31) of said structure (3) comprising activation of the coils, measurement of the electrical signals representative of the eddy currents, and evaluation over time of a variation in the electrical signal of each of the coils (511-536) by taking as a reference an edge effect corresponding to a specific electrical signal emanating from at least one coil installed at the edge of the surface, the level of said variation being indicative of the presence of the flaws in the structure.

Abstract: A device for measuring the illumination of a light bulb wherein it has a sensor for measuring the illumination of the bulb and a device for measurement and comparison of the value of illumination of the bulb to at least one threshold.

Abstract: The invention concerns a device for detecting and eliminating a layer of ice formed on the surface of an aircraft structure (6) or a liquid that has infiltrated inside of a structure and/or into the material of the structure. According to the invention, the device comprises at least one pair of subnetworks of conductive elements (2a, 2b), each subnetwork comprising at least one series of conductive elements (3), said subnetworks being arranged in such a way that the interfitting between the conductive elements (3) of the first subnetwork and the conductive elements (3) of the second subnetwork forms a network of capacitive sensors (1), said conductive elements being embedded in an insulating material (4), each subnetwork of conductive elements being incorporated into a flexible substrate (5, 5a, 5b) so that the entire assembly forms a flexible covering.

Abstract: 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.

Abstract: A device for non-destructive testing of a structure likely to contain a defect, including means for measuring vibratory waves emitted by the structure at different points of a surface of the structure, the measuring means being integrated in a flexible housing capable of adhering on the surface of the structure to be tested. The disclosed embodiments are applicable to all industrial sectors where testing of the integrity of structures is important, in particular in areonautics.

Abstract: A device for non-destructive control of a component analyzes distribution of a leakage magnetic field emitted by the component when it is subjected to an exciting magnetic field, includes means for generating an exciting magnetic field inside the component to be tested, and means for detecting and measuring the distribution of the magnetic field. The set of means is integrated in a flexible housing to form a device in the form of a flexible coating for being fixed on a region of the surface of the component to be tested. The disclosed embodiments are useful for non-destructive testing of aircraft components, but may also be used in all industrial sectors where testing the integrity of components is important, such as the automotive, railway, marine or nuclear industry.

Abstract: The subject of the invention is a system for measuring the state of panels in real time, particularly of one or more composite panels, characterized in that it has a network of very fine waveguides connected to a series of transducer sensors that are designed to send and receive signals in the waveguides, these sensors being themselves connected to a computer device such as a microprocessor device.

Abstract: A device for measuring the illumination of a light bulb wherein it has a sensor for measuring the illumination of the bulb and a device for measurement and comparison of the value of illumination of the bulb to at least one threshold.

Abstract: The subject of the invention is a system for measuring the state of panels in real time, particularly of one or more composite panels, characterized in that it has a network of very fine waveguides connected to a series of transducer sensors that are designed to send and receive signals in the waveguides, these sensors being themselves connected to a computer device such as a microprocessor device.

Abstract: The non-destructive test of a structure (10) such as an aircraft fuselage is done by placing an X-ray source (16) on one side of the structure, and placing a digital camera (24) on the other side. The microcomputer (28) analyzes the image output by the digital camera in real time. If this image is unusable, at least one setting of the source (16) is modified immediately and a new acquisition is made without wasting any time. The adjustment can then be made manually or using a slaving system. The adjustment may relate to the wave length of the X-ray beam, the dose level or the pose time if the fault concerned is related to the gray level of the image. If a directional source is being used, the defect may also have an influence on the sharpness of the image and may be caused by an alignment problem.

Abstract: The non-destructive test of a structure (10) such as an aircraft fuselage is done by placing an X-ray source (16) on one side of the structure, and placing a digital camera (24) on the other side. The microcomputer (28) analyses the image output by the digital camera in real time. If this image is unusable, at least one setting of the source (16) is modified immediately and a new acquisition is made without wasting any time. The adjustment can then be made manually or using a slaving system. The adjustment may relate to the wave length of the X-ray beam, the dose level or the pose time if the fault concerned is related to the gray level of the image. If a directional source is being used, the defect may also have an influence on the sharpness of the image and may be caused by an alignment problem.