An aircraft air data probe contamination monitor includes at least two air data sensor probes, a first probe located on one side of the aircraft, a second probe located on an opposite side of the aircraft, each probe being operable to generate a parameter value from an airflow passing the in-flight aircraft. The monitor also includes a processor operable to compare the generated parameter value from the first probe to the generated parameter value from the second probe to determine if one of the first probe and the second probe is contaminated.

A wind direction indicator for hunters includes a smoke generator, a housing, an electrical power source, an air pump and a switch all arranged such that the indicator may be actuated by a hunter using a single hand. The smoke generator may be a cartomizer as an example.

A wind direction indicator for hunters includes a smoke generator, a housing, an electrical power source, an air pump and a switch all arranged such that the indicator may be actuated by a hunter using a single hand. The smoke generator may be a cartomizer as an example.

An air data system includes an avionics system and a plurality of sensors associated with the avionics system, each of the sensors providing a signal indicative of a parameter used by the avionic system to determine the flight status of the aircraft. At least one air data probe is electronically coupled to the avionics system. At least one pitot static probe is coupled to a pressure transducer through pneumatic tubing, the pressure transducer is electronically coupled to the avionics system.

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.

Estimating the speed of an aircraft estimates three components of the speed vector (TAS, AOA, SSA) of an aircraft relative to the surrounding air. The static pressure is estimated on the basis of measurements of geographical altitude. A first intermediate variation of a linear combination of the three components of the speed vector of the aircraft relative to the surrounding air is estimated using explicitly the fact that the pressure measured by the static probe is falsified by a known quantity under the effect of the three components of this speed vector of the aircraft relative to the surrounding air. The process then estimates the three components of the speed vector of the aircraft relative to the air by likening the latter to the speed vector of the aircraft relative to an inertial reference frame and by using inertial measurements. The various estimates are fused to provide a final result.

A flow angle sensor includes a sensing element, a background component connected to and movable with the sensing element, the background component having a marker, a lens adjacent the disk, an image sensor axially aligned with the lens, a light source positioned to illuminate the disk, and an image processing system connected to the image sensor. The image processing system provides an angle of attack output based on a location of the marker sensed by the image sensor.

Systems and methods for detecting touch events with an accelerometer are disclosed. In one aspect, a method includes measuring first accelerometer data at a first rate, detecting a first touch event based on the first accelerometer data, in response to detecting the first touch event, measuring second accelerometer data at a second rate, determining whether a second touch event is detected based on the second accelerometer data, measuring third accelerometer data at the first rate in response to an absence of the second touch event being detecting in the second accelerometer data over a predetermined threshold period of time.

An aerodynamic measurement probe intended to measure a local angle of attack of an airstream flowing along the fuselage of an aircraft, comprises a support and a shaft that is able to rotate about a longitudinal axis with respect to the support. The support and the shaft are configured to form between one another a plurality of successive chicanes about the longitudinal axis. Each chicane makes it possible to transport liquid that has penetrated into the chicane: along a first path, under the effect of gravity, towards an evacuation circuit associated with the chicane and formed in the support, and along a second path, and counter to the effect of gravity, towards a successive chicane or towards the shaft. The evacuation circuit of each of the chicanes makes it possible to evacuate liquid out of the support under the effect of gravity moving away from the shaft.

A waterfowl decoy apparatus comprising a vertical shaft, a hinging mechanism that is movable between a deployed position and a closed position mechanically connected to the vertical shaft, a windsock support structural member having a first end pivotally connected to the hinging mechanism and a windsock slidably connected to the windsock support structural member. When the hinging mechanism is in the deployed position, the windsock support structural member and the windsock is perpendicular to the vertical shaft. When the hinging mechanism is in the closed position, the windsock support structural member and windsock is parallel to the vertical shaft.