An optical detection system includes a marker product and an optical encoding device. The marker product includes a substrate and at least one structural portion. The structural portion has a first surface, a second surface and a dividing axis. The first surface and the second surface are arranged on opposite sides of the dividing axis. A sidelong direction aligning the first surface with the second surface is parallel to a moving direction between the optical encoding device and the marker product. The optical encoding device is disposed adjacent by the marker product. The optical encoding device includes an optical projector and an optical encoder. The optical projector is configured to project the optical detecting signal onto the marker product. The optical encoder is configured to receive an optical reflecting signal from the marker product and encode intensity variation of the optical reflecting signal into digital data.

A computer-readable, non-transitory medium storing a program that causes a computer to execute a process is provided. The process includes acquiring a backward Rayleigh scattered light from an optical fiber composite overhead ground wire provided along an electrical power transmission line, determining each of spectral densities of each of frequencies of vibration of the optical fiber composite overhead ground wire, on a basis of the backward Rayleigh scattered light, estimating a wind speed of a wind hitting the electrical power transmission line, on a basis of a first spectral density of a first frequency band including a natural frequency of the optical fiber composite overhead ground wire, and estimating a wind direction of the wind, on a basis of a second spectral density of a second frequency band which does not include the natural frequency of the optical fiber composite overhead ground wire.

An angle of attack (AOA) sensor system is disclosed. The system comprises a plurality of pitot tube ports in a housing. The pitot tube ports include a set of positive angle pitot ports, a set of negative angle pitot ports, and a central pitot port. The central pitot port is aligned with a central chord line of a wing of the aircraft. A plurality of pitot tubes communicate with the plurality of pitot tube ports (at a first end), and with a plurality of pressure sensors (at a second end). A microcontroller is configured to generate a respective current AOA value for each pressure sensor based on a respective ram pressure measurement generated by each of the pressure sensors, and generate an AOA measurement of the aircraft by comparing each respective current AOA value to respective calibrated AOA values stored in a memory.

The present invention relates to a method for self-testing an angle-of-attack probe comprising the steps of controlling an angular excitation of a rotary element that is rotatable about its equilibrium position according to known excitation characteristics; acquiring angular measurements relating to the rotation of the rotary element, determining a parasitic torque applied to the rotary element on the basis of the angular measurements and of the excitation characteristics; comparing at least one component of the parasitic torque with at least one predetermined threshold and detecting an operating fault in the probe when said component exceeds the predetermined threshold.

A solar tracker system includes a photovoltaic panel and an actuator coupled to the photovoltaic panel and configured to actuate to rotate the photovoltaic panel around a base. A controller communicatively coupled to the actuator is configured to detect a direction from which wind is incident on the photovoltaic panel. Based on the direction from which wind is incident on the photovoltaic panel, the controller adaptively controls the actuator to set a stow position of the photovoltaic panel.

An electronic device is described. The electronic device may include a housing, a rotatable crown, and a self-mixing interferometry (SMI) sensor positioned within the housing. The rotatable crown may include an array of retroreflective surface features that reflect incident light back to a light source. Each retroreflective surface feature of the array of retroreflective surface features may be formed as a corner-cube with three perpendicular faces. The SMI sensor or associated processing electronics may compare originally emitted light with reflected light to identify a movement or distance of the rotatable crown with respect to the SMI sensor.

A method of health management and assessment for an air data probe comprises performing a calibration process for the air data probe prior to installation of the air data probe on a vehicle; performing an operational process after the air data probe is installed on the vehicle; computing residuals for individual pressure channels of the air data probe and an aggregated response function, based on outputs from the calibration process and the operational process; storing and trending the residuals over time; evaluating a trendline for the residuals against one or more threshold values; and announcing a message when one or more of the threshold values is exceeded, indicating that the health of the air data probe is compromised.

An angle of attack sensor includes a housing having an open end and a closed end, a faceplate positioned on the open end of the housing, the faceplate comprising a periphery at an outer edge of the faceplate, a central opening, and an exterior surface extending from the periphery to the central opening, and a vane assembly extending through the central opening of the faceplate. The exterior surface of the faceplate has a sloped profile from the periphery to the central opening.

A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor, configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor, configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor, configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.

An aircraft angle of attack and sideslip angle indicator includes a display responsive to angle of attack and sideslip angle measurements from an angle of attack sensor and a sideslip angle sensor on an aircraft. The display depicts angle of attack along a first (preferably vertical) axis, and sideslip angle along a second (preferably horizontal) axis, with the axes intersecting at a display datum which represents acceptable angle of attack and sideslip angle values from the aircraft. The display depicts the aircraft's current angle of attack and sideslip angle with respect to the display datum, thereby indicating to the pilot whether non-optimal (and perhaps dangerous) flight conditions are occurring.