A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

A control system operable includes a modified primary control parameter for an aircraft, the control system includes: a primary control parameter leg configured to output a demand in an aircraft primary control parameter; a primary control parameter compensation leg configured to receive a change in absolute levels and/or spatial distributions of swirl angle and/or fan pressure at a primary control parameter relative to a reference and convert the change into the primary control parameter; a processor adapted to receive the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; compare the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; and generate a modified primary control parameter for the aircraft.

Disclosed are embodiments of a drone with a flattened tubular part protrudingly mounted on a module located on the fuselage of the drone, where the free distal end of the drone may also include a Pitot tube dynamic pressure front air intake. An internal duct may further connect the air intake to a pressure sensor mounted on the module. The tubular part may be mobile with respect to the module and may further include a means or mechanism for the mechanical coupling to a contractor mounted on the module. The tubular part may further include a light guide in light communication with a luminescent element mounted in the vicinity or at the level of the proximal end thereof. The tubular part may also include two sectionalized portions that are nested and in continuation of each other, where the base portion may be permanently linked to the module and a removable protruding portion may be located at the top base portion, which may include a front air intake and an internal duct.

Disclosed are embodiments of a drone with a flattened tubular part protrudingly mounted on a module located on the fuselage of the drone, where the free distal end of the drone may also include a Pitot tube dynamic pressure front air intake. An internal duct may further connect the air intake to a pressure sensor mounted on the module. The tubular part may be mobile with respect to the module and may further include a means or mechanism for the mechanical coupling to a contractor mounted on the module. The tubular part may further include a light guide in light communication with a luminescent element mounted in the vicinity or at the level of the proximal end thereof. The tubular part may also include two sectionalized portions that are nested and in continuation of each other, where the base portion may be permanently linked to the module and a removable protruding portion may be located at the top base portion, which may include a front air intake and an internal duct.

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 method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.

Described are various embodiments of an air-speed sensor, system and airspeed monitoring process digitally implemented thereby or in relation thereto. In one such embodiment, a sensor comprises a sensor casing having a leading surface and having plural distinctly oriented input ports defined therein to capture a respective air pressure at each one thereof; respective pressure sensors disposed within said casing in fluid communication with respective ones of said input ports to sense said respective air pressure for each one thereof; and a digital processor operatively coupled to each of said pressure sensors to digitally compute respective pressure ratios between said input ports and compare said ratios against designated pressure ratios corresponding to designated incident airspeed angles of incidence to output an airspeed incident angle and airspeed accordingly.

An assembly for monitoring air flow at a surface of a rotor blade of a wind turbine is provided. The assembly includes (a) a surface module adapted to be arranged at a predetermined location of the rotor blade surface, the surface module including two air inlets facing opposite directions along an axis, (b) a sensor module including two pressure sensors, wherein one of the two pressure sensors is in fluidic communication with one of the two air inlets and the other one of the two pressure sensors is in fluidic communication with the other one of the two air inlets, wherein the sensor module is adapted to output two pressure signals indicative of the pressures sensed by the two pressure sensors, and (c) a processing unit adapted to determine at least one of a flow direction and a flow speed along the axis based on the two pressure signals.

A system for monitoring a vehicle-borne probe includes a first edge device in communication with the probe and configured to sense data related to a characteristic of a heating element of the probe, a coordinator in communication with the first edge device and configured to receive a first data output from the first edge device and to incorporate the first data output into a data package, a cloud infrastructure in communication with the coordinator via a data gateway and configured to analyze the data package to estimate a remaining useful life and predict a failure of the probe, and a ground station in communication with the cloud infrastructure and configured to refine remaining useful life estimation and failure prediction techniques of the system.