Abstract: A stress detection system includes a flexible two-dimensional structure, at least one electrically conductive textile filament, and an apparatus for generating and detecting an electric signal. The filament extends over a predetermined length in a portion of the flexible structure and has at least two points rigidly constrained to the structure. The apparatus is connected to the ends of the filament. The deformability of the filament is substantially equal to or greater than the deformability of the portion of the structure to which the filament is constrained.

Abstract: Systems and devices for angle of attack sensors are provided. Aspects include a vane, a faceplate, an annular region in the faceplate, and a thin film heater assembly attached to a surface of the annual region.

Abstract: A probe head of an air data probe includes a body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to a second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, a heater bore extending within the body, and an enhanced conduction area between heater bore and an exterior surface of the probe head. The inlet, the air passageway, the water dam, and the heater bore are all unitary to the body. The rod heater is positioned within the heater bore.

Abstract: A probe head of an air data probe includes a unitary body extending from a first end to a second end of the probe head and a rod heater. The body includes an inlet adjacent the first end of the probe head, an air passageway extending through the body from the inlet to the second end of the probe head, a water dam extending radially through the body such that the air passageway is redirected around the water dam, and a heater bore extending within the body. The rod heater is positioned within the heater bore.

Abstract: A pitot tube includes an outer tube extending from a first tube end to second tube end, the second tube end defining a tip portion of the pitot tube, the tip portion including an inlet opening. A tube sleeve inside of the outer tube at least partially defines a tube passage extending from the first tube end to the second tube end. The tube sleeve includes a sleeve outer surface having a sleeve body portion having a first outer diameter and a sleeve tip portion located at the tip portion of the pitot tube. The sleeve tip portion has a second outer diameter smaller than the first outer diameter. A heating element is located between the outer tube and the tube sleeve at at least the sleeve tip portion.

Abstract: A dynamic five-hole probe includes a pressure sensing part, a pressure measuring hole transition section, a pressure acquisition section, dynamic pressure sensors and flexible wall pressure buffering tubes, the pressure sensing part being provided with pressure measuring holes to sense three dimensional dynamic pressure components of an airflow; the pressure measuring hole transition section transits from an inlet end surface five-hole structure into an outlet end surface five-hole structure; the pressure acquisition section has therein a centrally symmetric pressure measuring hole structure; pressure sensor mounting holes are in communication with the five pressure measuring holes; each of the dynamic pressure sensors is mounted in a corresponding one of the sensor mounting holes to measure a dynamic pressure of the airflow. The pressure sensing part may have a diameter of 3 mm or less.

Abstract: An angle of attack sensor includes a vane assembly and a multi-piece faceplate adjacent the vane assembly. The faceplate includes a heated chassis defining a pocket and a mounting plate positioned adjacent the heated chassis and having an opening. The vane assembly has a portion that is positioned in the pocket of the heated chassis and extends through the opening of the mounting plate.

Abstract: An angle of attack sensor includes a housing having an open end and a closed end, a faceplate positioned on the open end of the housing, the faceplate having an opening, a vane assembly extending through the opening of the faceplate, a vane shaft connected to the vane assembly and extending within the housing, the vane shaft having a bore extending through the vane shaft, a bearing surrounding the vane shaft, a vane shaft seal surrounding the vane shaft adjacent the bearing, and a first vent hole extending from an interior surface of the vane shaft to an exterior surface of the vane shaft between the bearing and a first end of the vane shaft seal, the first vent hole being in fluid communication with the bore of the vane shaft.

Abstract: An acoustic air data sensor for an aircraft includes an acoustic transmitter, an acoustic receiver, an acoustic signal generator, timing circuitry, speed of sound determination circuity, and communication circuitry. The acoustic transmitter is located to transmit an acoustic signal through an airflow stagnation chamber that is pneumatically connected to an exterior of the aircraft and configured to receive and stagnate airflow from the exterior of the aircraft. The acoustic receiver is positioned at a distance from the acoustic transmitter to receive the acoustic signal. The pulse generator causes the acoustic transmitter to provide the acoustic signal. The timing circuitry determines a time of flight of the acoustic signal from the acoustic transmitter to the acoustic receiver. The speed of sound determination circuity determines, based on the time of flight and the distance, a speed of sound through air in the stagnation chamber. The communication circuitry outputs the speed of sound.

Abstract: An air data probe system can include a pitot static system configured to sense at least one total pressure value of a flow at one or more locations, at least one static pressure value of the flow at the one or more locations, and, directly or indirectly, at least one differential static pressure value of the flow at the one or more locations. The system can include an angle of slip (AOS) module configured to determine a local angle of slip (LAOS) value at each location based on the at least one total pressure value at each location, the at least one static pressure value at each location, and the at least one differential static pressure value at each location.

Abstract: According to one implementation of the present disclosure, a method for determining angle-of-attack for an unpowered vehicle is disclosed. The method includes: determining a monotonic portion of a look-up curve of an angle-of-attack operating plot; during flight, determining, by an accelerometer disposed on the unpowered vehicle, first and second accelerometer outputs, where the first and second accelerometer outputs correspond to first and second body-fixed load factor measurements, respectively; determining an operating point on the monotonic portion by applying a quotient of the first and second accelerometer outputs to the angle-of-attack operating plot; and determining an angle-of-attack parameter corresponding to the determined operating point.

Abstract: A damper assembly for an angle of attack sensor includes a rotor including a conical portion, a damper housing in which the rotor is positioned, the damper housing being configured to be adjusted axially with respect to the rotor and including a tapered interior surface that matches a profile of the conical portion, and a locking mechanism adjacent the damper housing.

Abstract: An aircraft freestream data system can include a first ultrasonic air data system (UADS) configured to sense local acoustic properties at a first location on an aircraft, a first local air data module operatively connected to the first UADS and configured to determine first local air data of the first location and to output first local air data, and a freestream data module operatively connected to the first local air data module. The freestream data module can be configured to receive the first local air data from the local air data module, determine one or more freestream air data parameters based on at least the first local air data, and output the one or more freestream air data parameters to one or more aircraft consuming systems.

Abstract: An angle of attack sensor includes a vane assembly and a multi-piece faceplate adjacent the vane assembly. The faceplate includes a mounting plate having an opening and a heated chassis positioned adjacent the mounting plate and having a ring portion extending into the opening. The ring portion includes a narrow fore portion extending into the opening, a wide aft portion extending into the opening, and an aft-located ramp connected to the wide aft portion and extending through the opening beyond an exterior surface of the mounting plate.

Abstract: The angle of attack (AOA) of an airplane is calculated as the difference of the flight-path angle and the pitch angle. The pitch angle is available from an attitude monitoring device (e.g., pitch gyro), but the flight-path angle is not available from the basic instruments common in general aviation. This method determines the flight-path angle mathematically, and in particular, using inputs from indicated airspeed and GPS. The sine (trig function) of the flight-path angle is the value determined by dividing the vertical velocity, provided by onboard GPS, by the velocity along the flight path (e.g., indicated airspeed). The sine value is converted to the value of flight-path angle by referring to a sine lookup table.

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: Disclosed herein is a distributed pressure sensor system that quickly detects and counters changes in lift, onset of stall, and flutter. The distributed pressure sensor system may employ a plurality of integrated pressure ports distributed across the span of a wing's leading edge to gather differential pressure measurements. Based on the differential pressure measurements, the distributed pressure sensor system can estimate torque on the fuselage to provide a more efficient estimate for changes in lift, onset of stall, and/or flutter. These estimates may be applied as feedback to the aircraft's control system, thereby eliminating the latency in the existing platform dynamics.

Abstract: Systems and methods for the co-location of high-maintenance air data system components into one LRU are disclosed. In at least one embodiment, an air data sensing line-replaceable unit (LRU) comprises at least one pressure sensor and at least one probe or port coupled to the at least one pressure sensor. The at least one probe or port conduits air located outside the air data sensing LRU to the at least one pressure sensor. Further, the at least one probe or port and the at least one pressure sensor are connected to each other by a permanent connection.

Abstract: An air data probe includes a probe head defining a longitudinal axis between a forward tip and aft base. The probe includes a thermocouple having a sense end in the forward tip to measure the temperature in the forward tip. The probe includes a port opening defined in a side of the probe head and opening at an angle with respect to the longitudinal axis. The probe includes a bulkhead within the probe head. The bulkhead has a chamber in fluid communication with the port opening. The chamber includes a single chamber inlet having an elongated cross-sectional shape. The single elongated chamber inlet is in fluid communication with two downstream pressure conduits to provide redundancy in case one of the two pressure conduits is blocked.

Abstract: A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

Abstract: An air pressure probe (APP) relates to the field of aviation and is intended to determine aircraft flight parameters or wind tunnel flow parameters. The APP comprises a head part with intake holes located thereon, which are connected by channels to couplers, and a support, attached to the head part from behind. The surface of the head part is provided with flow vortex generators. The generators can be in the form of indentations or protrusions of various shapes on the surface of the air pressure probe, or in the form of ribs formed as a result of the mating of elements of the flat or curved planes that form the surfaces of the head part and the support. The technical result is an increased operational range of measurement and a wider field of practical application.

Abstract: An apparatus and method for sensing position according to flow velocity includes at least two pitot tubes each defining a central axis is along mutually orthogonal axes. Each of at least two pressure sensors is positioned in fluid communication with a corresponding one of the at least two pitot tubes. A controller receives outputs from the at least two pressure sensors and analyzes to determine at least one of an angular and translational velocity according to the outputs. A distance traveled is then determined according to the at least one of an angular and translational velocity. Corresponding methods of use and calibration are also disclosed.

Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.

Abstract: A method of forming a pitot tube includes forming a substantially cylindrical body portion including an outer surface, a tip portion having an inlet opening and an interior defining a flow passage, radially tapering the outer surface from the body portion toward the inlet opening, and disposing at least one electrical coil including one or more coil wraps along the flow passage of the pitot tube.

Abstract: An aerodynamic force sensing apparatus for providing an air data computer with information to calculate air data. The apparatus includes a plurality of vanes supportable in a vane array extending from a distal end of an airfoil of an aircraft, and one or more sensors configured to sense the response of one or more vanes of the vane array to aerodynamic forces and to transmit corresponding signals to an air data computer (ADC) for use by the ADC in calculating air data.

Abstract: A pressure sensor assembly for simultaneously providing a time-resolved total pressure measurement and steady state flow angles of an airflow. The assembly includes an outer shroud having a front face, a rear face and a central bore having a wall. A dynamic absolute pressure sensor is positioned within the bore and provides a time-resolved total airflow pressure measurement. First and second spaced apart static pressure ports extend from the front face of the shroud to the rear face of the shroud and adjacent to the bore. The pressure ports provide a pressure that can be measured by pressure probes, where a combination of the time-resolved total pressure measurement and pressure measurements from the probes provides a steady state flow angle of the airflow.

Abstract: An air data system includes an avionics system and a plurality of sensors associated with the avionics system, each of the sensors providing a signal indicative of a parameter used by the avionic system to determine the flight status of the aircraft. At least one air data probe is electronically coupled to the avionics system. At least one pitot static probe is coupled to a pressure transducer through pneumatic tubing, the pressure transducer is electronically coupled to the avionics system.

Abstract: An aerodynamic measurement probe intended to measure a local angle of attack of an airstream flowing along the fuselage of an aircraft, comprises a support and a shaft that is able to rotate about a longitudinal axis with respect to the support. The support and the shaft are configured to form between one another a plurality of successive chicanes about the longitudinal axis. Each chicane makes it possible to transport liquid that has penetrated into the chicane: along a first path, under the effect of gravity, towards an evacuation circuit associated with the chicane and formed in the support, and along a second path, and counter to the effect of gravity, towards a successive chicane or towards the shaft. The evacuation circuit of each of the chicanes makes it possible to evacuate liquid out of the support under the effect of gravity moving away from the shaft.

Abstract: 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.

Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.

Abstract: Present invention provides a high-precision pressure sampling head used in a Pitot tube flow sensor. The pressure sampling head includes a cylindrical pressure sampling head body. The cylindrical pressure sampling head body contains a total pressure channel and a static pressure channel. The axis of the total pressure channel and the axis of the static pressure channel are parallel to the axis of the cylindrical pressure sampling head body. Two inclined surfaces are formed on two opposite sides of the lower end of the cylindrical pressure sampling body. A first inclined surface intersects with the total pressure channel and thus a total pressure sensing hole is formed on the first inclined surface. A second inclined surface intersects with the static pressure channel and thus a static pressure sensing hole is formed on the second inclined surface.

Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.

Abstract: An air data sensor device using a flow around a cylinder is provided. The air data sensor device may include a sensor measurement unit which includes a sensor body provided in a cylindrical form including a hollow inside, a plurality of pressure measurement holes disposed on an outside of the sensor body, and a thermostat attached to one side of the sensor body, and a signal processing unit which includes a pressure sensor connected to the plurality of pressure measurement holes, and a microprocessor connected to the pressure sensor to perform calculation. A main pressure measurement hole having a high pressure value may be selected from the plurality of pressure measurement holes, pressure distribution may be calculated, and at least one of an angle of attack, a static pressure, and a total pressure may be calculated using the pressure distribution.

Abstract: A system and method involve determining the airspeed of a vehicle using the propagation time of an acoustic signal from a transmitter located at one end of the vehicle to a receiver located at the other end of the vehicle. A digital representation of the acoustic signal is created and stored within non-volatile memory within the transmitter, then converted into an electrical signal which is filtered, amplified, and input into a transducer contained within the transmitter. The transducer radiates an acoustic signal toward the receiver, which receives and filters the acoustic signal, converts it into a digital signal, and processes the digital signal to determine the acoustic signal propagation time. The acoustic signal may have a continuous wave form, a duty cycle of about 100%, a peak to average amplitude ratio of less than about 2.5, and Fourier components of substantially equal amplitude and random phase.

Abstract: A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.

Abstract: An aerodynamic measurement probe intended to measure a local angle of attack of an airstream flowing along the fuselage of an aircraft, comprises a support and a shaft that is able to rotate about a longitudinal axis with respect to the support. The support and the shaft are configured to form between one another a plurality of successive chicanes about the longitudinal axis. Each chicane makes it possible to transport liquid that has penetrated into the chicane: along a first path, under the effect of gravity, towards an evacuation circuit associated with the chicane and formed in the support, and along a second path, and counter to the effect of gravity, towards a successive chicane or towards the shaft. The evacuation circuit of each of the chicanes makes it possible to evacuate liquid out of the support under the effect of gravity moving away from the shaft.

Abstract: A method for determining a state of credibility of measurements of an incidence sensor of an aircraft is provided. This method includes at least one coherence test between incidence measurements from said incidence sensor, and the measurements of a flight characteristic of the aircraft, distinct from the incidence. The coherence test includes determining an incidence value from said incidence sensor, determining said flight characteristic of the aircraft, determining a value of at least one indicator of the coherence of the incidence value with the value of said flight characteristic, and activating a low state of credibility, in which the measurements of said incidence sensor are deemed unreliable, or an intermediate state of credibility, in which the measurements from said incidence sensor are deemed coherent with said flight characteristic, based on the value of said coherence indicator.

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 an angle measurement probe on board an aircraft, which comprises a fin, which can move in rotation about an axis, at least one first optical encoder and one second optical encoder, each comprising at least one disk, each disk being fixed at right angles to the central axis and being provided with at least two circular tracks, each track being provided with alternate opaque and transparent zones, means for processing the output signal from each encoder.

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 present inventions provides an apparatus and method for the parallel loading of multiple samples in a microarray containing a plurality of sub-arrays. The method makes use of a microarray containing multiple sub-arrays, a loading channel array, and a fluid handling robot or an assembly robot or machine.

Abstract: Systems and methods determine at least one air data parameter, such as an angle of attack (AOA), an angle of sideslip (AOS), a total pressure (pt), and/or a static pressure (ps), from information provided by four pressure sensors coupled to four ports on a surface of a vehicle. Each of the ports may be defined by at least a unit vector, wherein the unit vectors are oriented in different planes.

Abstract: A device and method for estimating a side-slip angle (?e) of an aircraft moving in the air includes a receiving unit which receives a measured side-slip angle (?l) presented locally by the air relative to the aircraft, and a determining unit which determines the side-slip angle (?e) of the aircraft as a function of the measured angle (?l) and of an information item about the incidence (?) of the aircraft.

Abstract: A temperature probe assembly is provided. The temperature probe assembly may comprise a housing formed of a first thermally conductive material and having an inner diameter defined by an inner bore, an insert formed of a second thermally conductive material disposed in the inner bore and having an outer diameter that is substantially equal to the inner diameter of the housing at a first temperature and a temperature sensor mounted within the insert. The second thermally conductive material has a thermal coefficient of expansion that is greater than the first thermally conductive material, such that the insert is insertable into the inner bore at the first temperature and is tightly locked in the inner bore at a second temperature that is greater than the first temperature.

Abstract: A temperature probe assembly is provided. The temperature probe assembly may comprise a housing formed of a first thermally conductive material and having an inner diameter defined by an inner bore, an insert formed of a second thermally conductive material disposed in the inner bore and having an outer diameter that is substantially equal to the inner diameter of the housing at a first temperature and a temperature sensor mounted within the insert. The second thermally conductive material has a thermal coefficient of expansion that is greater than the first thermally conductive material, such that the insert is insertable into the inner bore at the first temperature and is tightly locked in the inner bore at a second temperature that is greater than the first temperature.

Abstract: Systems and methods determine at least one air data parameter, such as an angle of attack (AOA), an angle of sideslip (AOS), a total pressure (pt), and/or a static pressure (ps), from information provided by four pressure sensors coupled to four ports on a surface of a vehicle. Each of the ports may be defined by at least a unit vector, wherein the unit vectors are oriented in different planes.

Abstract: The present inventions provides an apparatus and method for the parallel loading of multiple samples in a microarray containing a plurality of sub-arrays. The method makes use of a microarray containing multiple sub-arrays, a loading channel array, and a fluid handling robot or an assembly robot or machine.

Abstract: An air data system is described that includes a cone-shaped probe, a plurality of pressure transducers, and a processing device. The cone-shaped probe includes a first pressure port formed in a substantial tip of the probe and extending therethrough, and a plurality of pressure ports formed in a substantially evenly spaced circular pattern about a sloped surface of the probe and extending through the probe. The plurality of pressure transducers are each configured to receive at least one pressure transferred through at least one of the pressure ports and output one or more signals related to the pressures sensed. The processing device is configured to receive signals originating from the transducers. The processing device is further configured to calculate a static pressure, an angle of attack, and an angle of sideslip based on the received signals.

Abstract: A system for determining angle of attack and angle of sideslip of an air vehicle is described. The system includes a plurality of mass flow sensors, at least a portion of which are mounted to result in a differential in air flow across the respective mass air flow sensors. The system also includes a controller configured to receive signals from the flow sensors and determine at least one of the angle of attack and the angle of sideslip for the air vehicle.

Abstract: An air data module is provided that is relatively small, lightweight, low cost, uses relatively low power, and is relatively easy to install, test, and maintain. The air data module includes a housing that is adapted to be mounted to an external surface of an aircraft, and includes at least a sensor compartment and an interface electronics compartment formed therein. A pitot-static probe is coupled to the housing and extends therefrom, and has a static pressure passageway that is in fluid communication with the sensor compartment. A plurality of static pressure ports are formed in the pitot-static probe and are in fluid communication with the static pressure passageway. A pitot pressure inlet port is formed in a distal end of the pitot-static probe. A static pressure sensor and a differential impact or absolute pitot pressure sensor, for example, may be mounted within the module and used to sense static pressure and impact or pitot pressure, respectively.