Provided are a shape model setting circuitry for setting a shape model of a target structure, a crack candidate plane in the shape model, and an observation plane of the shape model, an estimation model generator for generating an estimation model obtained from a numerical analysis of a structural analysis model by sequentially changing a boundary condition of the crack candidate plane in the structural analysis model generated from the shape model, and a crack state analyzer for estimating a position and a size of the crack by obtaining a distribution of load and displacement in the crack candidate plane at the same time by probabilistic inference through the application of an observation plane deformation vector indicating deformation of the observation plane obtained from measurement values, the estimation model, and a latent variable indicating presence or absence of the crack in the crack candidate plane.

A system for measuring a deformation of a structure configured to be installed on an aircraft includes deformation sensor means configured to be associated with the structure and to assume an electrical resistance value indicative of the deformation of the structure and having two short-circuited electrical connection terminals to recreate a closed circuit, magnetic field excitation means having a laser generator and configured to generate a magnetic field concatenated with the closed circuit to generate an induced current, electromagnetic radiation, transmission means having an antenna and configured to emit an electromagnetic radiation, value of the electromagnetic radiation being a function of the electrical resistance of the deformation sensor means, electromagnetic radiation receiving means having an antenna and configured to receive the electromagnetic radiation transmitted by the electromagnetic radiation transmission means, and control means for determining the deformation of the structure as a function of the value of electromagnetic radiation received.

Systems, methods, and apparatuses for inspecting a tank containing a flammable fluid are provided. A vehicle configured to inspect the tank can include a propeller, a battery, a control unit, an inspection device, and a ranging device. The battery provides power to the propeller, the control unit, the inspection device, and the ranging device. The control unit generates a map of the tank and determines a first position of the vehicle on the map. The propeller moves the vehicle through the flammable fluid in the tank. The inspection device includes a pulsed eddy current array to obtain inspection data indicating a quality of a tank wall. The control unit causes the propeller to move the vehicle from the first position to a second position within the tank. The control unit obtains first inspection data indicating the quality of the tank wall, and stores the first inspection data.

A pressure sensor for a pipe includes: a flexible strip; at least one strain sensing element; and a tensioning device. A first end of the flexible strip passes through a second end of the flexible strip. Between the first end of the flexible strip and the second end of the flexible strip, the flexible strip includes the at least one strain sensing element. The pressure sensor is attachable to the pipe. The first end of the flexible strip extends through or past the second end of the flexible strip. The tensioning device tensions the pressure sensor around the pipe.

A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from hub arms of a propeller hub, which in turn extend radially outwardly from a central axis extending through the propeller and a propeller drive shaft, is provided. The method comprises obtaining measurements representative of the strain in each of at least some of the hub arms using strain sensors, each of the strain sensors being provided on a respective hub arm. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.

Concrete can be one of the most durable building materials and structures made of concrete can have a long service life. Consumption is projected to reach approximately 40 billion tons in 2017. Despite this the testing of concrete at all stages of its life cycle is still in its early stages although testing for corrosion is well established. Further many of the tests today are time consuming, expensive, and provide results only after it has been poured and set. Embodiments of the invention provide concrete suppliers, construction companies, regulators, architects, and others with rapid testing and performance data regarding the cure, performance, corrosion of concrete at different points in its life cycle based upon a simple electrical tests that remove subjectivity, allow for rapid assessment, are integrable to the construction process, and provided full life cycle assessment. Wireless sensors can be embedded from initial loading through post-cure into service life.

A method of mounting a rail monitoring member/element at a mounting location of a rail for rail traffic, in particular on a railway track, is disclosed. The rail monitoring member includes a strain sensor member with a carrier on which a strain gauge, being an optical fiber with a fiber Bragg grating, is fixed. The method steps include: determination of the temperature of the rail and/or rail monitoring member at the mounting location; checking whether the determined temperature is within a predefined temperature interval; providing heating or cooling application to the rail and/or rail monitoring member at the mounting location, if the determined temperature is not within the predefined temperature interval; positioning and adhesively fixing of the carrier of the rail monitoring member at the mounting location. The method can be carried out easily and allows reliable and accurate monitoring of the rail using a strain sensor member.

According to one embodiment, a structure evaluation system of the embodiments includes a plurality of sensors, an arrival time determiner, a reliability calculator, and a map generator. The plurality of sensors detect elastic waves. The arrival time determiner determines arrival times of the elastic waves using elastic waves detected by the plurality of respective sensors. The reliability calculator calculates reliabilities related to measurement waveforms of the elastic waves on the basis of the arrival times. The map generator generates a first map on the basis of the calculated reliabilities or the reliabilities and a distance.

A sensor for measuring the fatigue life of a structure subjected to repetitive loads is disclosed. The sensor includes a backing material arranged for securement to the structure, and a foil arranged for securement to the backing material. The foil includes a conductive path along which electrical current flows at an initial resistance measured prior to the structure being subjected to repetitive loads. A crack initiation feature in the form of a notch is located on the conductive path. In response to repetitive loads applied to the structure, one or more cracks propagate from the crack initiation feature across the conductive path to cause electrical resistance to increase whereby the progression of fatiguing of the structure may be determined.

A multi-layer insulation includes a plurality of layers that are laminated on each other. A detection layer that is at least one of the plurality of layers has a piezoelectric film, and a pair of electrode parts installed on both surfaces of the piezoelectric film.