A fluid sensing device includes an outer shell, a three-axis force and moment balance, a strut, and a centerbody. The outer shell has an inlet at a first end of the outer shell, an aft vent at an opposing second end of the outer shell, and an interior space connecting the inlet and the aft vent. The three-axis force and moment balance is positioned in the interior space of the outer shell. The strut is connected to the outer shell and the three-axis force and moment balance such that the strut supports the three-axis force and moment balance in the interior space. At least a portion of the centerbody is positioned in the interior space of the outer shell. The centerbody is connected to the three-axis force and moment balance such that the three-axis force and moment balance is configured to measure force, moment, and/or movement of the centerbody.

A pressure and temperature probe includes a probe head, a probe tip extending from the probe head and ending with a sensor face, a pressure channel extending into the probe tip through the sensor face, and a temperature channel extending into the probe tip through the sensor face. A pressure sensor is in fluid communication with a pressure channel and a temperature sensor in fluid communication with the temperature channel. The temperature channel extends parallel to the pressure channel, and the temperature channel is fluidly separate from the pressure channel. The sensor face can be configured to minimally intrude the flowpath of a working fluid, thereby minimizing disruption of the flowpath. The probe can be configured on a gas turbine engine.

Systems and methods for icing resistant total air temperature probes with air jets are presented. In one embodiment, a probe comprises: a base having a forced air input port; and a body having leading and trailing edges extending from the base, the body comprising: a first interior airflow passage; a temperature sensor positioned within the first airflow passage; a notched intake port at a distal end of the body including an open channel extending into an intake aperture, and a cutaway region defining a recessed second face inset from the first face and exposes the open channel. The intake aperture opens into the first interior airflow passage, the notched intake port comprising air jet ports at a tip of the notched intake port; and a heated airflow passage through the body and isolated from the first interior airflow passage, coupling the forced air input port to the air jet ports.

A probe includes a housing defining a flow passage for a first fluid and having an entrance port and an exit port, a sensor configured to sense a parameter of the first fluid and positioned within the flow passage, and a hoop ejector connected externally to the housing such that a channel of the hoop ejector surrounds the exit port. The hoop ejector has a plurality of holes configured to port a second fluid from the channel such that the first fluid is aspirated from the flow passage and out through the exit port.

Systems and methods for enabling charged (ionized) air mass measurement for reliable air data computation onboard an aircraft. Ionic charge sensing may be used to derive air data having improved reliability. The systems and methods for ionic charge sensing employ an emitter electrode and two or more collector electrodes, which electrodes are disposed in proximity to the exterior skin of the aircraft and exposed to ambient air. The emitter electrode is positioned forward of the collector electrodes. The system further includes a solid-state ionic air data module that converts currents from the collector electrodes into air data parameter values. More specifically, the ionic air data module is configured to sense currents induced in the collector electrodes in response to corona discharge produced by the high-voltage emitter electrode.

An aircraft air data system includes a first air data probe disposed on a first side of the aircraft, a second air data probe disposed on a second side of the aircraft, a first plurality of static pressure sensing ports disposed on the first side of the aircraft, and a second plurality of static pressure ports disposed on the second side of the aircraft. Each of the first air data probe and the second air data probe include a barrel portion configured to extend into an oncoming airflow, a total pressure sensing port, and an integrated total pressure sensor. Each of the first plurality of static pressure sensing ports is connected to one of a first plurality of integrated static pressure sensors. Each of the second plurality of static pressure sensing ports is connected to one of a second plurality of integrated static pressure sensors.

A total air temperature probe includes a housing having inner surfaces defining an airflow passage, a first section of the airflow passage of the housing having an airflow inlet scoop with a first cross-sectional area and an inertial separation bend downstream of the airflow inlet scoop, wherein the airflow passage is configured to be substantially straight; and a second section of the airflow passage of the housing having a main exit channel and an elongated outlet with a second cross-sectional area, wherein the airflow passage is contoured to direct particle deflections to the elongated outlet, wherein the second section is downstream from the first section, and wherein the first cross-sectional area is greater than the second cross-sectional area

An air data probe is provided. The air data probe comprises an inner body having an outer surface, an outer body having an inner surface, a thin film heating system having a first surface and a second surface, a first thermally conductive adhesive disposed between the first surface and the outer surface, a second thermally conductive adhesive disposed between the second surface and the inner surface; and wherein the thin film heating system comprises one or more thin film heaters having one or more heating elements disposed in a thermally conductive, electrical insulator.

A probe system is configured to receive thermal images of the probe system from a thermal imager and includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational voltage is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to provide the operational voltage and receive the thermal images from the thermal imager. The control circuit is further configured to monitor the thermal images over time and determine a remaining useful life of the probe system based upon the thermal images over time.

Sensor assemblies and methods of de-icing or preventing ice formation are provided. Compressed air may be supplied to a vortex tube. The vortex tube may separate the compressed air into a first stream and a second stream, the first stream hotter than the second stream. A sensor body may be warmed by the first stream, and the second stream may be directed away from the sensor body