A method for a large space structure collapse detection apparatus to detect collapse of a large space structure according to the present invention includes: measuring a change in external load with respect to at least one main member in the large structure; calculating a stress or stress sensitivity according to the measured change in the external load; and comparing at least one of the calculated stress or the calculated stress sensitivity with a predetermined collapse diagnosis reference value and determining a risk of collapse of the large space structure.

Accurate damage diagnosis is obtained using strain, typified by low-cycle fatigue damage and the like, representing a majority of the damage from age deterioration of a machine facility. A rotating electrical machine damage diagnostic system evaluates fatigue damage in a component of a rotating electrical machine based on a sensor. A strain range calculating section determines elastic strain and elastic stress in an evaluation area of the rotating electrical machine in terms of a quadratic function of a rotational speed of the rotating electrical machine detected by the sensor. Conversion of the elastic strain range and the elastic stress range into a total strain range is performed and a fatigue damage rate is calculated in the evaluation area of the rotating electrical machine from the total strain range resulting from the conversion. An integration section is provided for cumulating the fatigue damage rates to calculate a cumulated fatigue damage rate.

Disclosed is a method for measuring movement and/or deformation of a study part subjected to an external stress, the method implementing a color digital image acquisition device and image correlation unit. The method includes: acquisition (250) of a plurality of color digital images of the surface of the study part by way of the color digital image acquisition device during the application of an external stress on the study part, and processing (260) of the color digital images acquired in the step of acquisition of a plurality of color digital images so as to highlight contrasting details on variable scales.

A propeller health monitoring system for an aircraft includes an aircraft having one or more propellers that includes light in or on them. The system includes one or more receptors mounted to a fuselage or a nacelle of the aircraft, each receptor having a sensor surface which is able to detect a position for each light beam crossing over the sensor surface as the propeller rotates, such that the receptor generates a signal that is indicative of the position as a measure of blade tip trajectory for each passing propeller blade The system also includes a processing unit which analyses the signals from the receptor to determine health of the propeller blades of the one or more propellers based on where the beams of light from the propeller blades have crossed over the sensor surface.

According to a first aspect of the invention, there is provided a mobile bridge apparatus, comprising: one or more mobile bridge modules; and a plurality of sensors for sensing a deformation of the one or more mobile bridge modules.

A low power consumption multi-contact micro electro-mechanical strain/displacement sensor and miniature autonomous self-contained systems for recording of stress and usage history with direct output suitable for fatigue and load spectrum analysis are provided. In aerospace applications the system can assist in prediction of fatigue of a component subject to mechanical stresses as well as in harmonizing maintenance and overhauls intervals. In alternative applications, i.e. civil structures, general machinery, marine and submarine vessels, etc., the system can autonomously record strain history, strain spectrum or maximum values of the strain over a prolonged period of time using an internal power supply or a power supply combined with an energy harvesting device. The sensor is based on MEMS technology and incorporates a micro array of flexible micro or nano-size cantilevers. The system can have extremely low power consumption while maintaining precision and temperature/humidify independence.

A system and method for measuring dynamic properties of a structure, and for using the measured dynamic properties to assess the dynamic performance of the structure. The system and method measures dynamic properties of the structure such as frequencies of resonance, mode shapes, and non-linear damping, and uses them in an analysis of the structure to compare the dynamic response of the structure with the anticipated properties of a structure built according to applicable building code requirements. The system and method thus quantifies a risk of failure of the structure by determining a risk ratio that compares an as-is condition of the structure with an as-designed condition of the structure.

According to one embodiment, a structure evaluation system includes an impact imparting unit, a plurality of sensors, a position locator, and an evaluator. The impact imparting unit applies impacts to a second region different from a first region of a structure to which traveling sections of a vehicle, which travels on the structure, apply impacts. The plurality of sensors detect elastic waves generated in the structure. The position locator locates a position of a source of the elastic waves on the basis of the elastic waves detected by each of the plurality of sensors. The evaluator evaluates a deterioration state of the structure on the basis of a position location result of the position locator.

An optical monitoring device for monitoring curvature along a flexible medical instrument including optical fibers, a light source to inject light into the optical fibers, a light receiver configured to measure an optical characteristic of reflected light from the optical fibers, a processor to analyze the measured optical characteristic to determine a curvature of the optical fibers, compare the curvature with a threshold curvature, determine a location along the optical fibers of the determined curvature, store previous curvatures and their associated location along the fibers in a storage, analyze the stored curvatures by counting or summing curvatures determined at a given location over time to predict breakdown of the flexible medical instrument, and produce an indication when the stored curvatures determined at the given location over time predict breakdown of the flexible medical instrument at the given location.

The method for warning of risk of rupture or deformation of a part made of a composite material when it is subjected to a force relates to a part including a fibre-reinforced thermoplastic or thermohardenable matrix. The method includes arranging the fibers in a lattice structure produced by winding fibers to form bars that join together or intersect at nodes. The method includes designing at least one bar of the lattice and/or integrating, into the part, at least one additional bar with a determined location and tensile strength and associating, with the at least one bar, inside the part, a sensor to detect the rupture thereof. The method further includes associating, with the sensor, an emitter, outside the part, for a signal relating to the rupture.