Abstract: A system for power management of air data probes is provided. The system comprises a power source in an aircraft, and two or more air data probes electrically connected to the power source. Each of the air data probes comprises a body structure coupled to a fuselage of the aircraft, and at least one electrical heater coupled to the body structure and in electrical communication with the power source. A switching mechanism is coupled between the power source and the electrical heater of each of the air data probes. The switching mechanism is controllable such that the electrical heater of each of the air data probes is electrically connectable to the power source in parallel or in series.

Abstract: An air data probe is provided. The air data probe includes a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air, at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element, and a heater element integrated into the tube of the pitot probe on the outside of the dams. The at least three dams are oriented within the tube of the pitot probe in such a way that the dam locations are configured for two or more installations of the air data probe.

Abstract: An air data probe is provided. The air data probe includes a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air, at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element, and a heater element integrated into the tube of the pitot probe on the outside of the dams. The at least three dams are oriented within the tube of the pitot probe in such a way that the dam locations are configured for two or more installations of the air data probe.

Abstract: A probe assembly includes a heat source; and a probe tip configured to enhance conduction of heat provided by the heat source into a front end tip of the probe. The probe tip includes: a first region having high thermal conductivity in at least a z-direction, wherein the z-direction is parallel to an axis along which the probe tip is extended; and at least one additional region having thermal characteristics different from the first region.

Abstract: Systems and methods for icing resistant total air temperature probes are provided. In one embodiment, a total air temperature data probe comprises: a probe base; a probe body comprising: a first interior airflow passage comprising a first annulus; a temperature sensor positioned within the first annulus; a heating element; a notched intake port positioned at a distal end, wherein the probe body provides a conductive thermal path from the heating element to the intake port, the intake port including an open channel extending inward into an intake aperture of the probe body, and a cutaway region that defines a recessed second face inset from the first face and exposes the open channel at least partially from the leading edge. The notched intake port further comprises a slot inset from the recessed second face that traverses across at least a portion of the intake aperture perpendicularly to the open channel.

Abstract: In one embodiment, 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.

Abstract: A multi-part air data probe sensor assembly facilitating rapid replacement is provided. One example air data probe sensor assembly comprises a mount plate interface including at least one mount plate electrical connector configured to mate with electrical lines of an aircraft and at least one mount plate pneumatic connector configured to mate with pneumatic tubes of an aircraft; and a detachable sensor body having at least one sensor electrical connector that is coupled with the at least one mount plate electrical connector and at least one sensor pneumatic connector that is coupled with the at least one mount plate pneumatic connector; and a mechanical seal provided between the mount plate interface and the detachable sensor body, wherein the mechanical seal is composed of a moisture blocking material.

Abstract: A probe assembly includes a heat source; and a probe tip configured to enhance conduction of heat provided by the heat source into a front end tip of the probe. The probe tip includes: a first region having high thermal conductivity in at least a z-direction, wherein the z-direction is parallel to an axis along which the probe tip is extended; and at least one additional region having thermal characteristics different from the first region.

Abstract: An air data probe comprises an elongated body structure having a proximal end and a distal end, with the elongated body structure including an outer surface and an opposing inner surface that defines an interior channel. A probe tip is located at the distal end of the elongated body structure, with the probe tip including an outer surface and an inner surface that are contiguous with the outer an inner surfaces of the elongated body structure. The probe tip has an opening in communication with the interior channel that allows outside air to pass from the probe tip into the interior channel. An electrical heater cable is coupled to the elongated body structure and the probe tip. The electrical heater cable comprises a compact double layer helix portion coupled to the elongated body structure or the probe tip, or coupled to both the elongated body structure and the probe tip.

Abstract: A probe portion of an air data probe is provided. The probe portion includes an endoskeleton structure having an outer surface, a heater cable disposed along the outer surface of the endoskeleton structure, a porous cover, surrounding the endoskeleton structure and heater cable, and a braze filler that substantially fills gaps between the heater cable and the endoskeleton structure and that substantially fills gaps in the porous metal cover.

Abstract: An aircraft electric taxi system diagnostics and prognostics evaluation method, including receiving, with a computer, an electronically recorded first performance parameter of a first electric taxi system of a first aircraft during a taxi operational event at an airport; and comparing the first performance parameter with a first performance factor statistical model generated in response to the first performance parameter and first comparative performance parameters; and calculating a first performance parameter difference based on the comparison.

Abstract: An air data probe includes a probe body. The air data probe also includes a housing surrounding the probe body, wherein a cavity is defined between the probe body and the housing. The air data probe also includes a heater element disposed within the cavity between the probe body and the housing. The air data probe also includes a low melting point metal disposed within the cavity between the probe body and the housing, wherein engaging the heater element causes at least a portion of the low melting point metal to transition from a solid state to a liquid state.

Abstract: A system method for predicting vehicle mission capability for a vehicle that is propelled by an engine includes collecting engine degradation data for the engine. Location independent engine degradation data are generated from the collected engine degradation data. The location independent engine degradation data are representative of engine degradation that is independent of locations associated with the mission. Predictions of location dependent engine degradation are calculated from the collected engine degradation data and the location independent engine degradation data. The location dependent engine degradation is representative of engine degradation due to movement through locations associated with the mission.

Abstract: A probe assembly includes a heat source; and a probe tip configured to enhance conduction of heat provided by the heat source into a front end tip of the probe. The probe tip includes: a first region having high thermal conductivity in at least a z-direction, wherein the z-direction is parallel to an axis along which the probe tip is extended; and at least one additional region having thermal characteristics different from the first region.

Abstract: Systems and methods for additive manufacturing for air data probes are provided. In at least one embodiment a probe comprises a support structure comprising one or more ports for receiving one or more fluids, the support structure comprising an endoskeleton mandrel having an opening for receiving a fluid; and a heating cable encircling an external surface of the endoskeleton mandrel. The probe also comprises an additive coating fused to the external surface of the endoskeleton mandrel and an external surface of the heating cable; and an internal assembly inside the support structure for carrying pressures from the one or more ports to one or more instruments that respond to the one or more fluids to provide a measurement.

Abstract: An air data probe includes a probe body. The air data probe also includes a housing surrounding the probe body, wherein a cavity is defined between the probe body and the housing. The air data probe also includes a heater element disposed within the cavity between the probe body and the housing. The air data probe also includes a low melting point metal disposed within the cavity between the probe body and the housing, wherein engaging the heater element causes at least a portion of the low melting point metal to transition from a solid state to a liquid state.

Abstract: A system for power management of air data probes is provided. The system comprises a power source in an aircraft, and two or more air data probes electrically connected to the power source. Each of the air data probes comprises a body structure coupled to a fuselage of the aircraft, and at least one electrical heater coupled to the body structure and in electrical communication with the power source. A switching mechanism is coupled between the power source and the electrical heater of each of the air data probes. The switching mechanism is controllable such that the electrical heater of each of the air data probes is electrically connectable to the power source in parallel or in series.

Abstract: A multi-part air data probe sensor assembly facilitating rapid replacement is provided. In one embodiment, an air data probe sensor assembly comprises a mount plate interface including at least one mount plate electrical connector configured to mate with electrical lines of an aircraft and at least one mount plate pneumatic connector configured to mate with pneumatic tubes of an aircraft; and a detachable sensor body having at least one sensor electrical connector that is coupled with the at least one mount plate electrical connector and at least one sensor pneumatic connector that is coupled with the at least one mount plate pneumatic connector; and a mechanical seal provided between the mount plate interface and the detachable sensor body, wherein the mechanical seal is composed of a moisture blocking material.

Abstract: An air data probe comprises an elongated body structure having a proximal end and a distal end, with the elongated body structure including an outer surface and an opposing inner surface that defines an interior channel. A probe tip is located at the distal end of the elongated body structure, with the probe tip including an outer surface and an inner surface that are contiguous with the outer an inner surfaces of the elongated body structure. The probe tip has an opening in communication with the interior channel that allows outside air to pass from the probe tip into the interior channel. An electrical heater cable is coupled to the elongated body structure and the probe tip. The electrical heater cable comprises a compact double layer helix portion coupled to the elongated body structure or the probe tip, or coupled to both the elongated body structure and the probe tip.

Abstract: Systems and methods for additive manufacturing for air data probes are provided. In at least one embodiment a probe comprises a support structure comprising one or more ports for receiving one or more fluids, the support structure comprising an endoskeleton mandrel having an opening for receiving a fluid; and a heating cable encircling an external surface of the endoskeleton mandrel. The probe also comprises an additive coating fused to the external surface of the endoskeleton mandrel and an external surface of the heating cable; and an internal assembly inside the support structure for carrying pressures from the one or more ports to one or more instruments that respond to the one or more fluids to provide a measurement.