Abstract: A rain-resistant, drainless, heated air data probe assembly may comprise a probe having a central channel, one or more peripheral channels, and a heating element. In addition, inner surfaces of the channels may include hydrophilic surfaces, and the outer surface of the probe may include hydrophobic surfaces. The hydrophobic outer surface may reduce water ingress into the channels of the probe, and the hydrophilic inner surfaces may cause dispersion of water that has entered the channels. The heating element may further cause evaporation or running off of water on the outer surface, and may cause evaporation of dispersed water within the channels, which may further eliminate the need for a drain at a terminal end of the probe assembly.

Abstract: Improvements in thin film sensors are disclosed. These can be used for aircraft applications. Dielectric isolation washers can be provided between a pressure sensor and an exterior metal housing of a sensor assembly. In this manner, high voltage inputs from a lightning strike or other source that reach the sensor housing are not transmitted to the sensor. Dielectric washers, insulators, and potting compounds can thus isolate a metal thin film pressure sensor from adjacent metal components (e.g., using non-conducting insulating materials like Torlon, zirconia and nylon). Besides their high dielectric strength, these materials exhibit compressive strength and resistance to wear, creep and corrosion. Desirable thicknesses for these components are provided. The described thin film pressure sensor embodiments can attain a dielectric rating of 1500 VAC.

Abstract: Ice accumulation and shedding mitigation devices associated with sensor probes extending into a stream of air entering an aircraft engine are provided. An exemplary device comprises a wedge-shaped blade configured to be exposed to the stream of air and disposed upstream of the sensor probe. The wedge-shaped blade has two faces meeting at a leading edge oriented to face the stream of air.

Abstract: A corrosion-resistant air data probe includes a hollow tube having at least one opening, an inner surface of the hollow tube defining an interior cavity, a heating element, and a continuous layer of a braze material. The heating element is disposed adjacent to the inner surface, within the interior cavity. The continuous layer of the braze material completely covers the heating element and covers at least a portion of the inner surface.

Abstract: A method of measuring air data of an aircraft is provided. The method includes emitting, by a laser disposed on the aircraft, laser light into air outside the aircraft, the laser tuned to induce a laser-induced plasma channel (LIPC) in the air. The method also includes sensing, by a sensor system disposed on the aircraft, at least one property of the LIPC. The method further includes computing, by a computing device disposed on the aircraft, the air data of the aircraft based on the at least one property of the LIPC.

Abstract: There is disclosed an aircraft configured to collect air data, the aircraft comprising: a wing structure; a forebody, forward of the wing structure; an afterbody, backward of the forebody; a skin covering the wing, the forebody and the afterbody; at least one recess formed at the skin, the recess being configured to affect the pressure of air flowing at the recess; at least one ambient sensor port for measuring ambient air pressure at the skin; and at least one recess sensor port for measuring the air pressure at the recess.

Abstract: An air data system with a digital interface includes least one air data component, a receiving system and at least one digital connection. The at least one digital connection is between the receiving system and the air data component. A method for transmitting data in an air data system with a digital interface includes measuring at least one air data parameter with at least one air data component. The method includes generating a digital signal representative of the at least one air data parameter with the at least one air data component, sending the digital signal to a receiving system, and processing the at least one air data parameter with the receiving system.

Abstract: An air data probe includes a probe head defining a longitudinal axis between a forward tip and aft base. A port opening is defined in the forward tip. A first conduit is in fluid communication with the port opening to guide fluid flow from the port opening to a first chamber. The first chamber is downstream from the port opening. A second conduit, offset radially and circumferentially from the first conduit, is in fluid communication with the first chamber to guide fluid flow from the first chamber to a second chamber. The second chamber is downstream from the first chamber. The offset between the first and second conduits is configured to prevent particle ingestion from the port opening from entering the second conduit.

Abstract: Improvements in thin film sensors are disclosed. These can be used for aircraft applications. Dielectric isolation washers can be provided between a pressure sensor and an exterior metal housing of a sensor assembly. In this manner, high voltage inputs from a lightning strike or other source that reach the sensor housing are not transmitted to the sensor. Dielectric washers, insulators, and potting compounds can thus isolate a metal thin film pressure sensor from adjacent metal components (e.g., using non-conducting insulating materials like Torlon, zirconia and nylon). Besides their high dielectric strength, these materials exhibit compressive strength and resistance to wear, creep and corrosion. Desirable thicknesses for these components are provided. The described thin film pressure sensor embodiments can attain a dielectric rating of 1500 VAC.

Abstract: An aircraft airflow sensor probe configured to correct measurements based on aircraft movement includes a vane assembly configured to sense a direction of local airflow outside an aircraft, at least one accelerometer configured to detect aircraft movement, a sensor configured to sense and output a rotational position of the vane assembly, and an angle of attack processor configured to determine at least a measured angle of attack of the aircraft based on the rotational position of the vane assembly. The angle of attack processor further configured to determine a correction value based on the aircraft movement data provided by the at least one accelerometer and output a corrected angle of attack of the aircraft.

Abstract: Apparatus and associated methods relate to detecting turbulence of an airstream over an airfoil surface of an aircraft using a sequence of acoustic transducers attached to the airfoil surface of the aircraft along a path. Each of the sequence of acoustic transducers is configured to detect acoustic waves indicative of airstream condition proximate the acoustic transducer. A processor is configured to determine, for each of the sequence of acoustic transducers, a level of turbulence of the airstream proximate the acoustic transducer.

Abstract: An unmanned aerial vehicle (UAV) includes a housing forming a central body of the UAV and including an internal compartment, one or more electrical components disposed within the internal compartment and configured to affect operation of the UAV, and an inertial measurement unit (IMU) disposed in an external compartment external to the central body. The IMU is isolated from the internal compartment such that a barometric pressure in the external compartment is independent of a barometric pressure in the internal compartment.

Abstract: An aircraft airflow sensor including a vane assembly configured to sense a direction of local airflow outside an aircraft, at least one port arranged on the vane assembly, and at least one transducer arranged with the vane assembly configured to measure a pressure within the vane assembly. The at least one transducer being in fluid communication with the at least one port. The aircraft airflow sensor also includes a shaft configured to rotatably hold the vane assembly and allow rotational movement of the vane assembly.

Abstract: A corrosion resistant apparatus for an air data probe with a sleeve being cylindrical in shape with a first end and a second end, at least one circumferentially extending groove on an outside of the sleeve configured to accommodate coils of a heater, and a bore at a center of the sleeve and extending between the first end and the second end configured to provide a pneumatic pathway that allows atmospheric conditions to reach measurement equipment of the air data probe.

Abstract: An air data probe includes a faceplate, a body connected to the faceplate, and a heating system comprising a coil, the coil being connected to the faceplate. The coil generates an electromagnetic field that couples with the body to heat the body.

Abstract: An air data system for an aircraft includes a multi-function probe (MFP) and an inertial reference unit (IRU). The MFP is positioned to sense a pressure of airflow about an exterior of the aircraft. A first electronics channel of the MFP is electrically coupled to the IRU to generate air data parameter outputs based on the pressure sensed by the MFP and inertial data sensed by the IRU.

Abstract: A method and a device for determining and displaying a flyaway distance for a rotorcraft in the event of an engine of the rotorcraft failing, and while taking account of the height of waves being overflown by the rotorcraft. The method includes a first determination for determining a flyaway distance of the rotorcraft in the event of a failure of an engine and under current flying conditions, a second determination for determining a maximum altitude of the waves being overflown by the rotorcraft and displaying the flyaway distance and the maximum altitude on a display instrument of the rotorcraft indicating the relative height of the rotorcraft or else its altitude. A safety margin is preferably added to the maximum altitude of the waves, or else to the flyaway distance of the rotorcraft.

Abstract: An angle-of-attack sensor includes at least one acoustic transmitter is configured to provide an acoustic pulse. The first acoustic receiver is positioned at a radial distance from the at least one acoustic transmitter. The first acoustic receiver is configured to receive the acoustic pulse at a first time and provide a first receiver signal. The second acoustic receiver is positioned at the radial distance from the at least one acoustic transmitter aligned with an axis that extends through the at least one acoustic transmitter and the first acoustic receiver. The second acoustic receiver is configured to receive the acoustic pulse at a second time and provide a second receiver signal. The angle-of-attack circuitry is configured to determine a delay difference between the first and second receiver signals representative of a difference between the first time and the second time and determine an angle-of-attack based upon the delay difference.

Abstract: Improvements in thin film sensors are disclosed. These can be used for aircraft applications. Dielectric isolation washers can be provided between a pressure sensor and an exterior metal housing of a sensor assembly. In this manner, high voltage inputs from a lightning strike or other source that reach the sensor housing are not transmitted to the sensor. Dielectric washers, insulators, and potting compounds can thus isolate a metal thin film pressure sensor from adjacent metal components (e.g., using non-conducting insulating materials like Torlon, zirconia and nylon). Besides their high dielectric strength, these materials exhibit compressive strength and resistance to wear, creep and corrosion. Desirable thicknesses for these components are provided. The described thin film pressure sensor embodiments can attain a dielectric rating of 1500 VAC.

Abstract: An air data probe has a pitot tube with a tap at a forward end that defines an inner flow path. The inner flow path decreases in the cross-sectional area until reaching a throat. The inner flow path has cross-sections that are generally cylindrical and also has sections of removed material.

Abstract: A method for testing movement speed includes, but is not limited to: measuring a static pressure P0 of an inner cavity of a pressure hole of a mobile device (S100); aligning the pressure hole to a wind direction and measuring a total pressure P of the wind in a static state (S101); aligning the pressure hole to the wind direction in a moving process, and measuring a pressure Pm of the inner cavity of the pressure hole in a movement direction (S102); obtaining a current wind speed vf according to a correspondence relationship between a wind speed vf and a dynamic pressure P?P0; and obtaining a current relative movement speed vr according to a correspondence relationship between a relative movement speed vr and a pressure difference Pm?P0 (S103); and obtaining a current movement speed v according to the current relative movement speed vr and the current wind speed vf (S104).

Abstract: An aircraft-mountable inflow and outflow apparatus has an accumulating sleeve, an inflow line and at least one exit opening. The regulating sleeve has an entry opening. The inflow line has a supply-line connection for a respective supply line. The accumulating sleeve forms a first supply-line portion, is designed for insertion into a respective shaft of the respective inflow and outflow apparatus and is dimensioned such that, in a state in which the insert has been inserted into the respective shaft, the entry opening of the accumulating sleeve is located in the vicinity of an opening between a respective head part and the respective shaft of the respective inflow and outflow apparatus. Furthermore, the accumulating sleeve is connected to the supply-line connection for a respective supply line via the entry line, which constitutes a second supply-line portion.

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: A system and method of non-intrusive anemometry. The system comprises an acoustic transmitter disposed at a boundary of fluid flow and first and second acoustic receivers adapted to receive transmissions from the acoustic transmitter. A processor is coupled to the acoustic receivers to determine the time of arrival of the transmission at the acoustic receivers. The acoustic transmitter and acoustic receivers are arranged such that the acoustic transmitter is upstream from the first acoustic receiver which is in turn upstream from the second acoustic transmitter.

Abstract: A moving-vane angle of attack probe is provided. The moving-vane angle of attack probe comprises: a vane having opposed first and second vane surfaces that define a leading edge and a trailing edge, the first and second vane surfaces, each extending between the leading edge and the trailing edge; a first vane opening located on the leading edge; at least one exhaust opening; a vane conduit extending between the first vane opening and the exhaust opening such that the first vane opening and the exhaust opening are in fluid communication, the vane conduit defining at least an interior chamber between the first and second vane surfaces; and a pitot-tube located within the interior chamber such that in use it receives air that enters the interior chamber via the first vane opening.

Abstract: A temperature and pressure probe (40) comprising an elongate outer tube (42) and elongate inner tube (56). Each tube having a peripheral wall (44, 58), a first open end (46, 60) and a second closed end (48, 62); the outer tube thereby defining an outer cavity (52) and the inner tube defining an inner cavity (66). The inner tube is located wholly within the outer cavity and is spaced from the outer peripheral wall (44) and second end (48). A temperature sensor (70) is located in the inner cavity. A pressure sensor (68) is located in the outer cavity. A vent pipe (76) is coupled between the inner peripheral wall and the outer peripheral wall, the vent pipe having a first end open to the inner cavity (66) and a second end open to vent outside the probe (40).

Abstract: A measurement unit for measuring a first static pressure of the ambient air in a first measurement zone of the aircraft, a measurement unit for measuring a second pressure of the ambient air, at least one static pressure probe, in a second measurement zone of the aircraft, the second pressure having a value lower than the first static pressure, a computation unit for estimating a Mach number using these two measured pressures and a data transmission unit configured to transmit the estimated Mach number to a user system.

Abstract: A method and system for determining an airspeed of an aircraft, known as assisted aircraft, comprises: a) determining a position; b) measuring a ground speed; c) receiving a plurality of messages from a plurality of other assisting, aircraft, each message containing a first item of information, indicating a position of an assisting aircraft, and a second item of information, indicating a wind speed at the position; d) estimating a wind speed at the position of the assisted aircraft by interpolating the wind speed values at the positions of the assisting aircraft obtained in step c); and e) computing a true speed of the assisted aircraft by using the vector difference between its ground speed, measured in step b), and the wind speed estimated in step d). The method can check operation of an anemometric subsystem aboard an aircraft, to compensate for any malfunction and/or to enable automatic piloting.

Abstract: The invention pertains to a method for verifying the consistency of the values (?1,?2,?3) given by the sideslip probes (1,2,3) of an aircraft and to a device implementing this method. This method is noteworthy in that it consists in consolidating the values of two sideslip probes by using the value of the incidence ?.

Abstract: Methods and apparatus to determine aircraft flight conditions are disclosed herein. An example apparatus disclosed herein includes a gaseous packet generator to generate a gaseous packet adjacent an aircraft. The example apparatus also includes a sensor array disposed on the aircraft to acquire information related to the gaseous packet. The example apparatus further includes a processor to determine at least one of a first characteristic of air flowing along the aircraft or a second characteristic of the aircraft based on the information.

Abstract: An ultrasonic airspeed and direction sensor system comprising an ultrasonic sensor array including an elongate base member for mounting to a vehicle, such as a helicopter, so as to extend outwardly from the vehicle. A number of radially extending support members are connected to the base member. The support members carry ultrasonic transducers arranged to define at least four bidirectional ultrasonic paths between respective pairs of the transducers, the ultrasonic paths being arranged into at least three non-coplanar sets. A processing system monitors the passage of ultrasonic signals along the paths to generate corresponding time of flight data, making a weighted selection containing at least one path from each of at least three sets, and processing the time of flight data for the selected paths, proportionate to the determined weighting, to generate airspeed and direction information.

Abstract: A system and method to display, when within an envelope of an ownship's flight path, a symbol representing wake turbulence from another aircraft based on aircraft type and flight parameters received from the other aircraft, the symbol being formatted to indicate the severity of portions of the wake turbulence. The format is modified periodically in accordance with the aircraft's flight path and a decay rate of the wake turbulence.

Abstract: An aerodynamic measurement probe intended to equip an aircraft. The probe comprises a tube intended to face substantially into a flow of air along the aircraft, the tube being open at a first of its ends. The probe further emits an electromagnetic wave directed towards a free zone situated in the extension of the tube on the side of the open end, the electromagnetic wave making it possible to reheat the water likely to be located in the free zone.

Abstract: Methods and apparatus to determine aircraft flight conditions are disclosed herein. An example apparatus disclosed herein includes a gaseous packet generator to generate a gaseous packet adjacent an aircraft. The example apparatus also includes a sensor array disposed on the aircraft to acquire information related to the gaseous packet. The example apparatus further includes a processor to determine at least one of a first characteristic of air flowing along the aircraft or a second characteristic of the aircraft based on the information.

Abstract: A system for displaying information obtained along the direction of flight of an aircraft is provided. The system includes a vane assembly pivotally mounted to the aircraft having a sensor mounted thereto. The vane comprises a pointing axis configured to continuously align with the direction of the flight path of the aircraft. A display device is operatively connected to the output of the sensor for providing a display along the actual flight path of the aircraft.

Abstract: An air data probe includes a probe head. The probe head defines a longitudinal axis with a forward tip and aft base and includes a wall tap port inlet defined in the probe head aft between the forward tip and the aft base. The wall tap port inlet opens on an angle relative to the longitudinal axis, wherein the wall tap port inlet has an elongated inlet perimeter configured to resist the formation of a meniscus, or otherwise reduce moisture induced pressure errors.

Abstract: The invention relates to a sensor device (4) for measuring a direction of incident flow (2) with which a flowing medium flows against the sensor device (4), having a flow body (1) which is set up to have the flowing medium flow around it, the flow body (1) having a plurality of pressure-sensitive or force-sensitive sensor elements (3) which are arranged on the outer surface of the flow body (1) or are arranged in the flow body (1) and are connected to the outer surface of the flow body (1), and the sensor elements (3) being arranged behind one another along the intended course (30) of the flow around the flow body (1). The invention also relates to an evaluation device for such a sensor device.

Abstract: A system and methods for non-optimal actuator detection are disclosed. A fluid valve controlling a fluid flow to a first actuator is activated, and the fluid valve is controlled to move the first actuator from an initial position to a first position and back to the initial position during a test interval. A measured valve position of the fluid valve is measured during the test interval, and a measured valve travel is calculated based on the measured valve position at an end of the test interval. A health status of the first actuator is determined based on the measured valve travel and an expected valve travel.

Abstract: A ship motion prediction system is described that includes a plurality of surface platforms and a central computer having a communications interface. The platforms each include a propulsion system for movement of the platform, a plurality of sensors operable for gathering sensor data relating to an environment proximate the platform, a processing device communicatively coupled to the propulsion system and the plurality of sensors, and a transceiver communicatively coupled to the processing device. The central computer includes a communications interface, and the processing device is programmed to transmit sensor data to the central computer via the transceiver and the communications interface. The central computer is programmed to transmit commands for operation of the propulsion system to the processing device via the communications interface and transceiver.

Abstract: A structural element of an aircraft includes a hollow part. An indicator provides a visual indication, for example by moving, if ice forms in a given region of the hollow part.

Abstract: The object of the present invention is to provide an air data sensor that does not require an external input of a reference velocity as a Doppler LIDAR, has a function of autonomously determining the absolute airspeed, and has no position error.

Abstract: A probe includes a stem having a tip that measures a wake produced by an object moving through a fluid. The probe includes temperature and pressure sensors co-located in the tip.

Abstract: The invention relates to an aeronautical probe designed to be mounted on the skin of an aircraft and comprising a probe body protruding from the skin of the aircraft and a heater for de-icing an external surface of the probe body. According to the invention, the heater comprises two self-supporting electrodes and heating resistive elements. Each electrode is formed of an electrically insulating substrate and of an electrically active portion forming one face of the electrode in question. Each resistive element is in contact with the faces of the electrodes. The notable advantages of the invention are that it makes it possible to reduce the operating temperature of the resistive elements and the phenomena of fatigue in the mechanical link between the electrodes and the resistive elements due to different expansion coefficients.

Abstract: A model hull testing method, platform, and system are disclosed that acquire model hull performance data about one or more hulls in an open-water environment, preferably testing two hulls simultaneously as they encounter essentially the same sea state. Avoiding tow-tank testing by providing a powered watercraft as an open-water testing platform, the method proceeds by supporting the model hulls on the testing platform, so they float in outboard positions, and then by acquiring data about hull performance as the testing platform and model hulls move together through an open body of water. A complement of data acquisition components acquires digital and analog data about the testing environment and model hull performance, preferably including platform motion, time and location information, wave characteristics, apparent wind speed and direction, and model hull drag and motion, with all data being recorded on an onboard laptop computer for later processing and analysis.

Abstract: The subject matter of the invention is an arrangement for determining the pressure in an undercarriage tire of an aircraft, which arrangement has a measurement matrix (1) with a plurality of load sensors which are arranged in an area over which the aircraft tire can roll. The invention provides that the arrangement is designed to measure the pressure difference between two or more undercarriage tires.

Abstract: A model hull testing method, platform, and system are disclosed that acquire model hull performance data about one or more hulls in an open-water environment, preferably testing two hulls simultaneously as they encounter essentially the same sea state. Avoiding tow-tank testing by providing a powered watercraft as an open-water testing platform, the method proceeds by supporting the model hulls on the testing platform, so they float in outboard positions, and then by acquiring data about hull performance as the testing platform and model hulls move together through an open body of water. A complement of data acquisition components acquires digital and analog data about the testing environment and model hull performance, preferably including platform motion, time and location information, wave characteristics, apparent wind speed and direction, and model hull drag and motion, with all data being recorded on an onboard laptop computer for later processing and analysis.

Abstract: A static port apparatus for an aircraft having a static plate having inner and outer surfaces for fixture on the aircraft. The static plate including a first set of a plurality of port apertures and at least a second set of a plurality of port apertures. Each port aperture of the second set of port apertures is coaxially positioned with respect to each port aperture of the first set of port apertures.

Abstract: A static port apparatus for an aircraft having a static plate having inner and outer surfaces for fixture on the aircraft. The static plate including a first set of a plurality of port apertures and at least a second set of a plurality of port apertures. Each port aperture of the second set of port apertures is coaxially positioned with respect to each port aperture of the first set of port apertures.

Abstract: The invention relates to a probe for aerodynamic measurement of an airflow. The probe comprises a plate rotating about an axis, a transmitter for transmitting a sound wave and a receiver responsive to the sound wave, the transmitter and the receiver forming two elements which are integrally connected to the plate and are placed at separate positions on the plate, the probe furthermore comprising means for delivering information representing a time of flight of the sound wave between the two elements and a temporal variation of the information. In the case of using the probe on board a helicopter, the rotating plate is advantageously placed at the centre of the rotor of the helicopter while being integrally connected to it. This type of probe makes it possible to carry out aerodynamic measurements even at low airspeeds of the helicopter.

Abstract: The method and apparatus for tracking a center of gravity (COG) of an air vehicle provides a precise calculation and updating of the COG by disposing a plurality of acceleration measuring devices on a circumference of one or more rings in a manner that establishes redundancy in acceleration measurement. A multivariable time-space adaptive technique is provided within a high speed digital signal processor (DSP) to calculate and update the position of the COG. The system provides the capability of executing a procedure that reduces dispersion in estimating angular velocities and lateral accelerations of a moving vehicle and corrects the vehicle's estimated angular velocities and lateral accelerations. In addition, a consistency check of the measured values from the acceleration measuring devices is performed to assist in fault detection and isolation of a faulty accelerometer in the system.