A method for detecting an object describable by a plurality of predetermined features comprises flying along the object and detecting several portions of the object using at least one recording unit. Each of the portions is detected multiple times from different positions of the recording unit to generate a set of images. Position and location information of the recording unit are associated to each image. Additionally, the method has recognizing features in the image sets and determining the positions and/or locations of the features using the position and location information of the images which contain the features.

Systems and methods for monitoring components are provided. A component has an exterior surface. A method includes performing a first analysis of a first image of a surface feature configured on the exterior surface of the component, the first image obtained by an imaging device. The method further includes adjusting a viewing parameter of the imaging device when a predetermined first analysis threshold for the first image is unsatisfied, and performing a subsequent first analysis of a second image of the surface feature, the second image obtained by the imaging device. The method further includes adjusting a distance between the imaging device and the surface feature when the predetermined first analysis threshold for the second image is unsatisfied, and performing a second analysis of a third image, the third image obtained by the imaging device.

A system for monitoring propeller health includes a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data. The system also includes a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the physics based algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller. In addition, the system includes an output device which is able to output an indication of the determined fatigue life consumption to an observer.

A sensor assembly for measuring a torsion of a rotor blade of a wind turbine generator system includes a first light source configured to generate light and a first transmitter-side polarizer disposed downstream thereof in a direction of light propagation and configured to generate linearly polarized light as a first transmission light. A second light source is configured to generate unpolarized light as a second transmission light. First and second detector elements are arranged and adapted to receive the first and second transmission light. A first receiver-side polarizer is disposed upstream of the first detector element in the direction of light propagation and a second receiver-side polarizer is disposed upstream of the second detector element in the direction of light propagation. An orientation of a polarization plane of the first receiver-side polarizer and an orientation of a polarization plane of the second receiver-side polarizer are different from one another.

A method for detecting defects in a composite structure, such as in an aircraft structure, that includes sending an optical signal down an optical fiber embedded in the composite structure and analyzing the optical signal at a detector. If it is determined that the optical signal is turning on and off or an increase in the bit error rate is occurring at the detector, the composite structure may be delaminating or the composite structure may be somehow damaged. If it is determined that the composite structure is damaged, the optical signal can be sent down a different optical fiber that may not be at a location where the composite structure is damaged, and a continuous beam of light can be sent down the optical fiber that is at the damaged part of the composite structure to determine whether the damage is increasing.

A coupon suitable for peeling tests, derived from a vane and comprising: (i) a portion of blade that comprises a frontside surface, a backside surface and a leading edge and/or trailing edge and (ii) a vane reinforcement that covers and is glued to at least a part of the frontside surface, a part of the backside surface and which extends beyond the leading and/or trailing edge. The reinforcement is split over the entire length of the leading edge and/or trailing edge such that the reinforcement is separated into two plates separate from one another and facing each other on either side of the slit beyond the leading and/or trailing edge. Furthermore, at least one of the plates furthermore comprises, beyond the leading and/or trailing edge, fastening means providing a hold to this same plate.

A load sensing system for sensing a load on a structure can include an optical load sensing element configured to change an optical state based on a force applied thereto, an optical source operatively connected to the optical load sensing element and configured to input an input optical signal to the optical load element, and an optical detector configured to receive a returned optical signal from the optical load sensing element. The optical detector can be configured to detect one or more frequency peaks of the returned optical signal and to use the one or more frequency peaks of the returned optical signal to correlate to a load value of the load and output the load value indicative of the load.

The present disclosure is directed to a method for estimating tower loads, such as tower deflection, of a wind turbine. The method includes receiving an estimate of slow variations in thrust of a tower of the wind turbine. The method also includes determining, via one or more sensors, tower accelerations of the tower of the wind turbine. Thus, the method also includes estimating the tower loads of the wind turbine as a function of the estimate of slow variations in thrust of the tower and the tower accelerations.

In order to provide a simplified inspection of an aircraft for the pilot, an aircraft inspection system is provided which includes at least one movable inspection unit, a position detection arrangement, and at least one data transfer interface. The at least one moveable inspection unit is moveable relative to an aircraft to be inspected. The at least one movable inspection unit includes at least one sensor for detecting a characteristic value, for verifying a characteristic and/or for determining a defect of an aircraft. The movable inspection unit is configured to generate monitoring data. When a defect or a characteristic value is detected, the position detection arrangement detects position data of the movable inspection unit in relation to the aircraft to be inspected, and assigns the position data to the monitoring data. The data transfer interface provides the position data with the assigned monitoring data as inspection data.

A device for optically monitoring a moving component includes at least one first camera, the image detection region of which can be controlled by a tracking device and which is configured to capture at least one image of at least a part of the moving component, wherein the device further includes at least one second camera, which is configured to capture at least one image of the moving component. The device further includes an open-loop or closed-loop control unit, which receives image data of the second camera and which generates an open-loop or closed-loop control signal and transmits the open-loop or closed-loop control signal to the tracking device.