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 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.

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 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 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 pitot probe assembly that is formed from modular, replaceable components, and is flexible. The configuration of the pitot probe assembly allows the pitot probe assembly to absorb and/or dissipate impact energy, and the modular, replaceable components allow for quick and easy repair of the pitot probe assembly. The pitot probe assembly can be configured as a total pressure pitot probe assembly or as a pitot static probe assembly.

A pitot probe assembly that is formed from modular, replaceable components, and is flexible. The configuration of the pitot probe assembly allows the pitot probe assembly to absorb and/or dissipate impact energy, and the modular, replaceable components allow for quick and easy repair of the pitot probe assembly. The pitot probe assembly can be configured as a total pressure pitot probe assembly or as a pitot static probe assembly.

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.

A system, power management system and method are disclosed. The power management system includes a pitot tube, one or more heating elements disposed in the pitot tube, and one or more power switches, wherein each power switch of the one or more power switches is coupled to a respective heating element and configured to energize or de-energize the respective heating element in response to a control signal. The power management system also includes a temperature detector coupled to the pitot tube and configured to determine a temperature of the pitot tube, and a processor complex coupled to the one or more power switches and the temperature detector and configured to output the control signal to energize or de-energize at least one of the heating elements through a respective at least one of the respective one or more power switches in response to at least the determined temperature of the pitot tube or a detection of a fault.

A system, power management system and method are disclosed. The power management system includes a pitot tube, one or more heating elements disposed in the pitot tube, and one or more power switches, wherein each power switch of the one or more power switches is coupled to a respective heating element and configured to energize or de-energize the respective heating element in response to a control signal. The power management system also includes a temperature detector coupled to the pitot tube and configured to determine a temperature of the pitot tube, and a processor complex coupled to the one or more power switches and the temperature detector and configured to output the control signal to energize or de-energize at least one of the heating elements through a respective at least one of the respective one or more power switches in response to at least the determined temperature of the pitot tube or a detection of a fault.