A system for collecting atmospheric data includes a frame and sensors to include a sonic anemometer for measuring wind data samples in each of three dimensions, and motion sensors for measuring angles of roll motion, pitch motion and yaw motion of the sonic anemometer. A tether is coupled to a cable payout/retriever, a lighter-than-air balloon, and the frame such that the payout/retriever and balloon control movement of the frame through a region of an atmosphere. A processor receives the wind data samples and the sensed angles, and maps the wind data samples to a fixed local horizontal reference plane of the sonic anemometer that is normal to a local gravitational vector at the region of the atmosphere to generate samples of compensated data. The processor averages samples of compensated data to generate averaged compensated data that is indicative of wind speed and wind direction in the region of the atmosphere.

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.

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.

A connector includes a shell, an insert that fits within the shell, and a socket that extends within the insert. The socket includes a hood, a body within the hood, an annular tine extending from the body within the hood, an annular lip extending around the tine adjacent an end of the tine, and a cavity formed within the tine.

A computer implemented method for estimating angles of attack and/or an angle of sideslip of a flying body includes the steps of: providing data or measurements representative of a time derivative of a module of a speed of the flying body with respect to an air; providing data or measurements representative of corresponding projections of coordinate accelerations on a Cartesian reference frame fixed to the flying body; and calculating the angles of attack and/or the sideslip on a basis of an mathematical relationship of the angles of attack and the sideslip with the coordinate accelerations and the time derivative of the module of the speed of the flying body with respect to the air.

According to an example aspect of the present invention, there is provided a sensor comprising at least one strut configured to be coupled to a surface of an object at a first end of the strut, a structure connected to a second end of the at least one strut, wherein the structure is V-shaped, U-shaped, curved or arched and configured to be coupled to the surface at both ends, a plurality of cavities positioned along the structure on both sides of the at least one strut, and a plurality of fibre-optic pressure transducers, wherein a single fibre-optic pressure transducer is arranged within each of the cavities, and wherein the sensor is configured such that at least some of the fibre-optic pressure transducers are arranged at different distances from the surface of the object.

A method can include vapor depositing a corrosion resistant coating to internal and external surfaces of a metallic air data probe. For example, vapor depositing can include using atomic layer deposition (ALD). The method can include placing the metallic air data probe in a vacuum chamber and evacuating the vacuum chamber before using vapor deposition. The corrosion resistant coating can be or include a ceramic coating. In certain embodiments, vapor depositing can include applying a first precursor, then applying a second precursor to the first precursor to form the ceramic coating.

A method, apparatus, and system for managing sensor system for an aircraft. A presence of erroneous sensor data generated by a set of external sensors on an exterior of the aircraft is detected. A set of deployable sensors is deployed in response to the erroneous sensor data being received from the set of external sensors on the exterior of the aircraft when an undesired environmental condition adverse to the set of external sensors on the exterior of the aircraft is absent. Sensor data is received from the set of deployable sensors.

In one embodiment, a method includes determining, by a controller, a first wind direction relative to a first vehicle and determining, by the controller, a first wind speed relative to the first vehicle. The method also includes calculating, by the controller, an absolute wind direction relative to ground using the first wind direction relative to the first vehicle and calculating, by the controller, an absolute wind speed relative to the ground using the first wind speed relative to the first vehicle. The method further includes calculating, by the controller, a second wind direction relative to a second vehicle using the absolute wind direction and calculating, by the controller, a second wind speed relative to the second vehicle using the absolute wind speed. A front end of the first vehicle and a front end of the second vehicle face different directions.

The measuring device includes a substrate intended to be arranged on an aerodynamic surface; a profiled element connected at one of its ends to the substrate, and configured to be oriented, under the effect of the fluid flow; a magnet that is secured to the profiled element and is configured to generate a magnetic field; and a measuring element that is configured to measure a value of the magnetic field and to convert this measured value of the magnetic field into an angle value indicating the direction of the fluid flow; the measuring device thus making it possible to measure and provide, in real-time, a numerical angle value with which it is possible to define with high precision the direction of the fluid flow relative to the aerodynamic surface.