A probe head of an air data probe includes an insert, a portion of a heater, an outer shell, a tip weld, and a braze. The insert includes a first end, a second end opposite the first end, and a body portion extending between the first end and the second end. The body portion includes a groove. The portion of the heater is positioned within the groove. The outer shell surrounds the insert and the portion of the heater. The outer shell includes a tip portion defining a first end of the outer shell and a body portion extending from the tip portion defining a second end of the outer shell. The tip weld is between the outer shell and the first end of the insert, and the braze is between the insert and the second end of the outer shell adjacent a second end of the insert. The portion of the heater is hermetically sealed between the insert and the outer shell.

An air data probe is disclosed. The air data probe may include a probe body having an interior cavity and coated by a protective shell. A sensing port may be disposed in the air data probe and may extend through the probe body. The sensing port may also be lined by the protective shell. The protective shell may be made of an austenitic nickel-chromium alloy, or stainless steel, or any relatively corrosion resistant material. The probe body may be made of nickel, or a nickel alloy, or any relatively thermally conductive material. The protective shell may be joined to the probe body by additive manufacturing, such as laser cladding. In this manner, an air data probe capable withstanding high temperatures without corrosion and yet also being relatively thermally conductive is disclosed.

An air data probe is disclosed. The air data probe may include a probe body having an interior cavity and coated by a protective shell. A sensing port may be disposed in the air data probe and may extend through the probe body. The sensing port may also be lined by the protective shell. The protective shell may be made of an austenitic nickel-chromium alloy, or stainless steel, or any relatively corrosion resistant material. The probe body may be made of nickel, or a nickel alloy, or any relatively thermally conductive material. The protective shell may be joined to the probe body by additive manufacturing, such as laser cladding. In this manner, an air data probe capable withstanding high temperatures without corrosion and yet also being relatively thermally conductive is disclosed.

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of operating aircraft for flight in close formation includes establishing a communication link between a first aircraft and a second aircraft, assigning to at least one of the first aircraft or the second aircraft, via the communication link, initial positions relative to one another in the close formation, providing flight control input for aligning the first and second aircraft in their respective initial positions, tracking, by at least one aircraft in the close formation, at least one vortex-generated by at least one other aircraft in the close formation, and based on the tracking, providing flight control input to adjust a relative position between the first aircraft and the second aircraft.

A flow measuring device for monitoring and measuring the flow of gaseous material, specifically high temperature gas using a low pressure drop measurement system, is provided. The device is adapted to fit within the pipeline of a flow system and may be installed wherever flow measurement is needed. In one embodiment, the device comprises a housing, multiple averaging pitot tubes to determine the total velocity and static pressure measurements, a differential pressure gauge to display the pressure, and a valve or valves to cut off flow as needed. Additionally, the present invention utilizes a means for cooling the temperature of the gas, thus negating the need for very expensive gauges capable of operating under very high temperatures. Overall, the flow measuring device herein provides a more efficient and cost-effective product and method to measure the flow of a liquid or gas, specifically a high temperature gas.

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of sensing three dimensional (3D) airflow by an aircraft includes: collecting measurements characterizing airflow near the aircraft; analyzing the collected measurements; creating, by a processor, a computer model predicting one or more 3D airflow patterns parameter values based on the analyzing; obtaining one or more additional measurements characterizing airflow near an aircraft of the plurality of aircraft, and evaluating an error between an airflow parameter value predicted by the computer model and the one or more additional measurement.

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of sensing three dimensional (3D) airflow by an aircraft includes: collecting measurements characterizing airflow near the aircraft; analyzing the collected measurements; creating, by a processor, a computer model predicting one or more 3D airflow patterns parameter values based on the analyzing; obtaining one or more additional measurements characterizing airflow near an aircraft of the plurality of aircraft, and evaluating an error between an airflow parameter value predicted by the computer model and the one or more additional measurement.

A method of inspecting an air data probe for damage or misalignment on a mounting surface includes retrieving reference data for the air data probe from a database, capturing images of the air data probe via a camera and generating dimensions from the captured images of the air data probe via a feature extractor. An alignment calculator analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify misalignment of the air data probe, and analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify damage of the air data probe. A maintenance recommendation for the air data probe is generated and outputted, based on the identified misalignment or damage of the air data probe.

A method of inspecting an air data probe for damage or misalignment on a mounting surface includes retrieving reference data for the air data probe from a database, capturing images of the air data probe via a camera and generating dimensions from the captured images of the air data probe via a feature extractor. An alignment calculator analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify misalignment of the air data probe, and analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify damage of the air data probe. A maintenance recommendation for the air data probe is generated and outputted, based on the identified misalignment or damage of the air data probe.

A flow generator (21) for a respiratory therapy system configured to deliver a breathable gas flow to a patient comprises a housing (27) comprising an inlet (28) and an outlet (25) and a gas flow path between the inlet (28) and outlet (25). An impeller is mounted within the housing (27) for rotation about an axis, the impeller configured to be rotationally driven by a motor to provide a gas flow along the gas flow path. Various embodiments are disclosed in which the flow generator (21) further comprises a sensor (23) mounted in the housing (27) in the gas flow path and configured to detect a property of the gas flow. The sensor (23) may be mounted in the outlet (25) so as to project into the gas flow path. Flow generator may comprise an axial inlet (28) and a tangential outlet (25). In another embodiment the sensor (23) may be mounted in the inlet (28).