Embodiments described herein utilize Non-Destructive Inspection (NDI) scan data obtained during a process performed on a surface of a structure to update a location of an NDI scanner on the surface. A subsurface feature within the structure is detected based on the NDI scan data, which are correlated with pre-defined position data for the subsurface feature. A measured location of the NDI scanner on the surface is corrected based on the pre-defined position data for the subsurface feature.

A method is provided including the steps: —first excitation of the object via a multifrequency signal; —detecting a first response signal of the object at one or multiple measuring points at the object; —transforming the first response signal from a time range into a frequency-dependent range; —selecting one or multiple frequencies, based on the frequency-dependent range; —second excitation of the object based on the selected frequencies; —detecting a second response signal of the object at one or multiple measuring points of the object; —ascertaining a mechanical parameter based on the second response signal.

The present invention relates to an airplane structure stiffener repair method based on measured data guidance. The method includes: respectively measuring point cloud data on a surface of a structure stiffener and point cloud data on a surface of a to-be-assembled position of a body; respectively extracting all assembly plane features in two point cloud data based on an RANSAC algorithm; performing pre-alignment according to the plane features; performing accurate alignment based on a signed distance constraint according to repair tolerance requirements; and calculating a repair allowance, and generating a machining path to serve as an accurate machining basis. According to the method in the present invention, a repair amount can be accurately calculated by virtue of an alignment algorithm of the signed distance constraint, and an envelope relationship during model matching is met.

An aviation component inspection device includes a camera, a display, an input device, and a computer. The camera is configured to capture images of an aviation component under inspection. The computer is configured to receive an image from the camera, evaluate the image with one or more machine-learning aviation component-detection models. Each machine-learning aviation component-detection model is previously trained to output at least one confidence score indicating a confidence that a corresponding aviation component is present in the image. The computer is configured to present, via the display, a list of candidate aviation components based on corresponding confidence scores output by the one or more machine-learning aviation component-detection models, and add data previously-associated with a selected candidate aviation component from the list to a digital inspection report responsive to receiving user verification, via the input device, confirming the selected candidate aviation component is present in the image.

A modular and autonomous assembly for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly comprises at least one electrical power source allowing the operation of the elements of the detection assembly independently of the turbine engine on which it is intended to be carried, at least one first sensor intended to be associated with the first impeller, at least one second sensor intended to be associated with the second impeller, and a main housing including a processing unit and storage means.

A method of determining the location and size of a crack in a blade includes measuring a time of arrival of a tip of the blade at an angular position in a rotation, using the time of arrival to calculate a displacement of the tip of the blade, and using the displacements to calculate a first vibration condition and a second vibration condition for the blade. The method also includes comparing the first vibration condition and the second vibration condition for the blade to a predetermined baseline first vibration condition and a predetermined baseline second vibration condition for the blade to determine a change in the first vibration condition and a change in the second vibration condition, and using the magnitude of the change in the second vibration condition relative to the change in the first vibration condition to determine the likely location of the crack and using the magnitude of the change in the first vibration condition and the change in the second vibration condition to determine the size of the crack.

The invention relates to a test stand comprising a support (19, 25) which is moveably connected to a wall (18, 18′, 18″), a base, a frame (26) of the test stand or another part of the test stand and can be moved on a predetermined path; an actuator (22) which is connected to the support and by means of which the support (19, 25) that can be moved on the predetermined path, two clamping devices (13) respectively comprising a ball joint, wherein one of the two clamping devices (13) is seemed to the support (19, 25) and the other of the two clamping devices (13) is arranged in an axis (10) with the first of the two clamping devices (13), such that a test body (1) is clamped between the two clamping devices (13) on outer surfaces of the test body and can be maintained by the clamping devices (13), and a test force exerted by a test body by moving the support (19, 25) through the first of the two clamping devices (13) acts essentially along the axis (10). The test body is fixed by means of an elastic element (23) in order to limit a rotation of the test body about the axis (10).

The present invention relates to a method and a system for tracking the motion of a blade of a wind turbine. One embodiment relates to a blade motion tracking system for installation on a wind turbine blade, where the wind turbine blade comprises a blade root and a blade tip. The system comprises at least one light module comprising at least a first light source, preferably adapted to emit light in the direction of the blade root. An optical measuring device is provided, preferably located at the blade root, adapted to receive light emitted from the first light source(s). The optical measuring device is preferably a position sensitive detector identifying the position of the first light source relative to the position sensitive detector. A single light source located at the tip of the blade, close to the tip of the or towards the tip of the blade, is sufficient to measure deflection of the blade. Advantageously the first light source is modulated with a predefined modulation frequency such that light from the first light source can be distinguished from ambient light and thereby minimize the influence of the ambient light conditions during detection.

A wind turbine rotor blade load emulator arrangement includes a support unit constructed to support a rotor blade during a fatigue test procedure; an exciter configured to deflect the rotor blade during a fatigue test procedure; and a stiffness augmentation assembly for mounting to the rotor blade over a mounting length, which stiffness augmentation assembly is realized to increase the stiffness of the rotor blade in the mounting length. A method of carrying out a fatigue test procedure on a wind turbine rotor blade uses such a load emulator arrangement.

Systems and methods of providing power to high-voltage sensors in power-limited environments through environmental energy harvesting are disclosed. The systems and methods are configured to intermittently power high-voltage sensors by repeatedly releasing stored energy in bursts. An environmental energy harvesting device generates a low-voltage power supply and is coupled to one or more capacitors to charge the capacitors to a high-voltage threshold. After such high-voltage threshold has been reached, the capacitors are discharged to provide a high-voltage power burst to a high-voltage sensor configured to inspect a component and generate an inspection result signal. The inspection result signal is received by an output module, which may further store or transmit to an external receiver a data signal indicating the inspection results.