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 test apparatus for torsional testing of a wind turbine blade is provided. The apparatus includes a test stand for rigidly supporting the wind turbine blade; a load frame for mounting on the wind turbine blade at a testing position along the length of the blade; and an actuator connected to the load frame for twisting the blade via the load frame. The load frame includes an outer frame to which the actuator is connected and a profiled insert held within the outer frame and defining a profiled aperture corresponding to the profile of the blade at the testing position. The profiled insert encloses and is in direct contact with the outer surface of the blade over substantially the entire profile of the blade. A system and method of torsional testing of a wind turbine blade and a load frame for the test apparatus are also provided.

The present invention relates to an apparatus and a method for determining a scaling factor for a strain measurement in a machine element, comprising steps for measuring a strain in a measurement surface portion by means of a strain measuring device; for measuring a displacement of a detection surface portion of the machine element by an optical scanning; for determining a displacement field on a surface of the machine element on the basis of a model of the machine element and the measured displacement of the at least one detection surface portion; for determining a strain field on the surface of the machine element on the basis of the determined displacement field and the model of the machine element; and for determining a scaling factor of the strain measuring device on the basis of the determined strain field and the measured strain in the measurement surface portion.

The invention provides a method for monitoring health state of blade root fastener, comprising the following steps: obtaining a sequence of acceleration signals representing the lateral vibration of the nacelle and a sequence of rotational speed signals representing the rotational speed of the rotor; analyzing the sequence of acceleration signals and the sequence of rotational speed signals to determine the amplitude of the nacelle at 2-time-frequncy of the rotational speed of the rotor; and determining the health state of the blade root fastener based on the amplitude. The invention also provides a system for monitoring the health state of the blade root fastener. Through the present invention, the health state of the blade root fastener can be determined with low cost and high precision, thereby improving the operation efficiency and operation safety of the wind turbine.

A device and a method for peeling tests, in order to test the peeling resistance of coupons each formed of a support and an adhesive. The device comprises: (i) a frame comprising rollers with parallel axes designed to maintain the coupon supported while guiding movement of the latter, (ii) a traction device comprising a vertical jack linked to an attachment element comprising a loop configured in order to cause detachment of the adhesive from the surface of the support, (iii) a device for measuring the force exerted by the jack in order to pull the loop during peeling, and (iv) a coupon, complex in shape, such as one derived from a reinforced vane. At least one roller is translationally adjustable in relation to other rollers and the coupon is specially prepared in order to facilitate carrying out the tests.

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.

This crack estimation device includes: a data determination unit which determines a shape model of a target structure to be inspected, and a crack occurrence plane and an observation plane in the shape model; an estimation data calculation unit which outputs an estimation model for estimating a state of the crack occurrence plane from a state of the observation plane, on the basis of a matrix that associates, with each other, the state of the crack occurrence plane and the state of the observation plane, obtained through numerical analysis of a structural analysis model generated from the shape model; and a crack estimation unit which estimates a state of a crack at the crack occurrence plane on the basis of the estimation model and a measurement value for the target structure actually measured at the observation plane.

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.

A method for creating a three-dimensional (3D) mark in a protective coating including at least one of a TBC and a bond coating over a metal part, is provided. The method may include positioning a mask over the protective coating, the mask including an opening pattern therein; and performing an abrasive waterjet process on the protective coating using the mask. The abrasive waterjet erodes a first portion of the protective coating exposed through the first opening pattern to create the 3D mark. The mask is removed, leaving the 3D mark in the protective coating. The 3D mark only partially penetrates through the protective coating. A metal part may include a metal body, a protective coating over the metal body, and the 3D mark in the protective coating, is also provided. The 3D mark in the protective coating may include an opening having a width of between 30 and 300 micrometers.

Provided is a control surface load simulation apparatus including a reaction force providing structure. The control surface load simulation apparatus includes a first support surface, a second support surface apart from the first support surface in a height direction, a control surface located between the first support surface and the second support surface, an actuator connected to the second support surface and configured to apply a certain load to the control surface, and a reaction force providing structure connected to the first support surface and the control surface to be movable relative to the first support surface and the control surface, the reaction force providing structure being configured to apply a reaction force corresponding to the load to the control surface.