Abstract: A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present.

Abstract: Ambient temperature for a temperature sensor can be calculated using a mobile temperature sensor system that samples air from the boundary layer around a mobile platform and passes the air through a measurement cell containing two flush-mounted or embedded sensor elements. A common reference voltage can be applied by control circuitry to minimize drift in the sensor element readings and to calculate the ambient temperature.

Abstract: Provided is a test tool for an airspeed indicator of an aircraft, including: a cylinder portion including an insertion groove with a predetermined amount of space, and of which one end is sealed by a cover and includes an injection portion on the cover so that the insertion groove passes through a pitot tube, and of which another open end includes a protruded step around its inner circumferential surface; a piston portion being inserted into the insertion groove to reciprocally move within the insertion groove, and including a protrusion portion having a size and a shape corresponding to an aperture of the insertion groove, and a bar-shaped knob portion being extended from the protrusion portion; and a display portion being formed of a transparent material on an outer surface of the cylinder portion to display a location of the protrusion portion reciprocally moving within the cylinder portion.

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 method of determining an estimate of the de-trended turbulence intensity TI in a proposed site for a wind farm including the steps of measuring the wind speed at a predetermined sampling frequency fs during a number of time periods pz; calculating in each time interval pz wind speed statistical parameters Vmean, ?v and a wind speed trend parameter k in real time for each new wind speed measure xj as a function of the values of said parameters Vmean, ?v, k for the prior wind speed measure xj-1 and the new wind speed measure xj; storing the parameters Vmean, ?v, k obtained at the end of each time interval pz; determining the de-trended turbulence intensity TI in said proposed site using said stored parameters Vmean, ?v, k. The invention also refers to an apparatus for acquiring the data needed for the calculation of the de-trended turbulence intensity TI.

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: A method and device for determining the air turbulence likely to be encountered by a first aircraft may use a turbulence indication from a second aircraft so as to make and use a prediction of the impact of the turbulence on the first aircraft if it is located in a particular position.

Abstract: The present invention relates to a method and a measuring device for measuring and displaying the overlap between a rear edge of an aircraft wing and a front edge of a landing flap fixed thereto. In accordance with the invention, only the difference in the positions of the rear edge of the aircraft wing and the front edge of the landing flap relative to the longitudinal direction of the aircraft is determined. For this purpose, a first sensor is positioned, as a reference of sorts, at one of the two positions, for example at the rear edge of the aircraft wing, and the display is then reset to zero or to another reference value. By positioning the second sensor, which is also rigidly connected to the calliper, at the other respective position, for example at the front edge of the landing flap, the difference between the front edge of the landing flap relative to the rear edge of the aircraft wing is established.

Abstract: A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft.

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: Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit.

Abstract: A method and an assembly for sensing a process parameter are provided. The sensor assembly includes a base, a pedestal including a body extending between a leading edge and a trailing edge in a direction of fluid flow past the body, a first edge of the pedestal coupled to the base, a second edge opposes the first edge. The sensor assembly also includes an airfoil extending from the pedestal, a leading edge of the airfoil aligned with the leading edge of the pedestal, the airfoil extending in a direction of a flow of fluid along the second edge. The sensor assembly further includes a sensor element extending from the second edge spaced apart from the airfoil by a first gap, and a shield at least partially surrounding the sensor element, the shield spaced apart from the airfoil by a second gap defining a fluid flow inlet to the sensor element.

Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.

Abstract: An air data system and method for a ducted fan air-vehicle is described. The air data system includes a plurality of air pressure sensors placed around a lip of an air duct of the ducted fan air-vehicle. The air data system calculates the speed and direction of airflow surrounding the ducted fan air-vehicle based on pressure data measured across the lip of the air duct. Additionally, the air data system may estimate forces generated by airflow surrounding the air-vehicle.

Abstract: A total air temperature probe includes an inlet through which airflow enters a primary airflow passage through the probe. A sensor flow passage is connected to the primary flow passage. Bleed ports extend between the primary airflow passage and a cross-port which extends laterally across the probe. An aspiration aperture in the cross-port couples the cross-port to an internal cavity of a strut of the probe. The aspiration aperture can be centered within the cross-port to provide symmetrical deicing heater error behavior of the probe during changes in angle of attack. An aspiration tube couples the internal cavity of the probe to a pressure source.

Abstract: A minimum aerodynamic interference support for models in a cryogenic wind tunnel includes two main pieces: a front sting substantially parallel to the longitudinal axis of the model and a blade, integrated together and describing an obtuse angle. The support is connected to the model by means of the blade, being the model such that it emulates a tail section and/or wings of an aircraft. The front sting of the support comprises an extension, extended horizontally underneath a frontal zone of the fuselage of the model, starting from the point where the blade starts and extending past the point where the blade is connected to the model, in such a way that the length and area dimensions of the cross-section of the extension are obtained by applying the aerodynamic principle, area rule, to the ensemble made up by the front sting, the blade, the model and the extension.

Abstract: A system and method for a pressure based load measurement system are provided. The system includes two pressure orifices arranged on a top surface and a bottom surface of an airfoil. The pressure differential between these two points is determined and an estimate of the aerodynamic load generated by the airfoil is determined from a linear correlation between pressure differential and load. The location of the orifices may be optimized using analytical or experimental techniques and a least squares empirical curve fit may be used to fit the data collected.

Abstract: An improved design for a force gradient using a proximity sensor is disclosed. A force gradient comprises a shaft having a first end and a second end. The switch includes a spring contained between the first end and the second end and a non-contact proximity sensor mounted on the second end. The spring has a first position and is compressed to a second position so that the non-contact proximity sensor signals an AFCS to change state.

Abstract: Pitot probes are described that are designed to prevent water blockage of the probe's air pressure orifice. The pitot probes are small, inexpensive, light weight and do not require power for heat generation. This makes the pitot probes particularly useful for use on UAV's and other small aircraft where size, cost, weight and power constraints are a major concern. The pitot probes utilize passive methods in the form of geometrical and material configurations to prevent blockage of the pitot probes by water droplets. The probes can also include water reservoirs that store collected water.

Abstract: A method of applying a test load to a landing gear mounted on an aircraft, the method comprising parking the aircraft with at least one tire of the landing gear on a platform; and moving the platform so as to apply the test load to the landing gear via the tire. An array of six platforms is mounted on a sliding chassis in a recessed oil bath. The platforms can be independently rotated to apply torque. The spacing between the platforms can be adjusted to adapt for different landing gear configurations.

Abstract: A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present.

Abstract: This invention relates to a method and system for increasing safety in chemical application from an aircraft. Wind speed, wind direction and other critical flight parameters are measured, calculated, recorded, and visually or audibly announced during the aircraft flight via onboard equipment, which parameters provide a means for the aircraft pilot to control chemical spray application and for unassisted automatic chemical spray cutoff and for limiting spray application outside an application zone or target area. Such parameters also provide a means for indicating the lift reserve of the aircraft and a means for determining atmospheric stability near the ground and providing the pilot with a record of the meteorological conditions at a particular location. The method and system of the present invention also provide a means for predicting appropriate aircraft upwind offset distance to compensate for predicted chemical spray drift.

Abstract: A process for monitoring the validity of a speed cue of an aircraft may include computing a coefficient of lift, which is representative of the lift of the aircraft, on the basis of values of static and total pressure. A first value of angle of incidence is computed on the basis of the computed coefficient of lift, and a second value of angle of incidence is determined. The difference between the first and second values of angle of incidence is computed, and the absolute value of the difference is compared with a predetermined threshold value. Based on the comparison, the speed cue is deemed valid if the absolute value of the difference is below the threshold value and deemed invalid otherwise.

Abstract: A method for determining total pressure distribution across a fan entry plane of a fan situated within a fan casing provided with struts which are positioned upstream of the fan, with respect to the normal air flow direction through the fan.

Abstract: The invention relates to a method of protecting aircraft in flight against clear air turbulence (CAT). Consider an aircraft occupying a position P and moving horizontally at a speed V, a plane PH0 being the horizontal plane passing through P. According to the invention, the method includes performing at least one pair of evaluations of air temperature TB, TC at two points B, C which have positions that are symmetrical relative to the plane PH0. At least one pair of horizontal air speed evaluations are performed VHB, VHC at the two points B, C; An air temperature gradient is determined; A horizontal air speed gradient is determined; An index signifying a presence of CAT is determined; The preceding steps are repeated; A trend is analyzed over time of the index.

Abstract: A nose section for a heated air pressure probe includes a barrier having a wall which blocks the direct longitudinal intake of air from an inlet, and diverts the air through one or more bypass ports. A heater is located in the barrier. Both the wall and the heater are located near the front of the inlet.

Abstract: A device for measuring air turbulence in the surroundings of an aircraft includes a measurement system having lidars which are mounted on the aircraft and which are intended to carry out, during a flight of the aircraft, twelve measurements of aerodynamic velocity in the environment surrounding the aircraft. The measurement system carries out the twelve measurements at four different measurement points, each time according to three predetermined axes. A central unit which, with the aid of the aerodynamic velocity measurements and of a first order predetermined mathematical model describing an aerodynamic velocity field as a function of twelve variables, determines an aerodynamic velocity field which exists in the environment of the aircraft and which is representative of the air turbulence.

Abstract: An air data sensor that determines a body's angle of attack, static air pressure, total air pressure, mach number, static air temperature and true air speed in one device using pressure and temperature readings. The air data sensor includes a probe that protrudes into an airflow to collect data, a base plate for attaching the probe to a body, and an electronics housing including electronics for interpreting the data collected from the probe.

Abstract: A method for displaying the direction of an external force relative to a craft is provided. The method comprises obtaining direction data for an external force, obtaining craft directional data, calculating the force's direction relative to the craft's direction, and displaying a graphical representation of the force's direction relative to the direction of the craft.

Abstract: A method and a device for obtaining the three components (u,v,w) of the air speed (TA) of an aircraft along its flight path, the device including an arm (2) provided with two pressure probes disposed at each of its ends, each probe having two pressure intakes.

Abstract: The present invention relates to pressure probes for measuring the aerodynamic flight parameters of an aircraft and more particularly those in which the orifices for measuring the static pressure and total pressure are located on a moving angle-of-attack or angle-of-sideslip measurement vane designed to be oriented in the direction of the wind. It consists of a pneumatic rotary joint employing flexible tubings rather than friction rotary joints between abutted parts of rigid tubings. Such a joint offers a much smaller resistance to the rotational movement of the moving vane, which consequently is oriented with greater accuracy in the direction of the wind.

Abstract: A vortex angle system includes one or more vortex angle sensors disposed on one or more wingtips of an aircraft. A summing circuit and computer compare signals from each sensor to provide a signal, which is indicative of the average vortex angle of the aircraft.

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: A system is described that is configured to determine a plurality of air data parameters for an air vehicle. The system includes a mass air flow sensor, a pressure sensor, and a controller. The mass air flow sensor is mounted to sense an air flow caused by movement of the air vehicle. The pressure sensor is mounted to sense a static pressure at the air vehicle. The controller is configured to receive signals from the mass air flow sensor and the pressure sensor and determine an air velocity and a static pressure using the received signals.

Abstract: Methods and systems for calculating atmospheric vehicle air data are disclosed. In one embodiment, a method of calculating air data includes acquiring one or more pressure measurements at locations on an outer surface of the aircraft; acquiring one or more measurements using an alternate navigation device; computing an indicated air data solution using the one or more measurements obtained using the alternate navigation device and an atmospheric model; computing corrections to the indicated air data solution using one or more other measured parameters, wherein the one or more other measured parameters include at least one of the one or more pressure measurements and the one or more measurements obtained using the alternate navigation device; determining a corrected air data solution using the indicated air data solution and the corrections; and providing the corrected air data solution for use in controlling the aircraft.

Abstract: Methods and systems for calculating atmospheric vehicle air data are disclosed. In one embodiment, a method of calculating air data includes acquiring one or more pressure measurements at locations on an outer surface of the aircraft; acquiring one or more measurements using an alternate navigation device; computing an indicated air data solution using the one or more measurements obtained using the alternate navigation device and an atmospheric model; computing corrections to the indicated air data solution using one or more other measured parameters, wherein the one or more other measured parameters include at least one of the one or more pressure measurements and the one or more measurements obtained using the alternate navigation device; determining a corrected air data solution using the indicated air data solution and the corrections; and providing the corrected air data solution for use in controlling the aircraft.

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.

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.

Abstract: A method for characterizing pressure sensors to improve accuracy in an air data system is described where the sensors include at least one static pressure sensor and at least one total pressure sensor. The method includes characterizing the static pressure sensor and the total pressure sensor to determine a static pressure sensor error, Pse, and a total pressure sensor error, Pte, and performing a second ratiometric characterization to reference the total pressure sensor error, Pte, to the static pressure sensor error, Pse.

Abstract: A vortex angle system includes one or more vortex angle sensors disposed on one or more wingtips of an aircraft. A summing circuit and computer compare signals from each sensor to provide a signal, which is indicative of the average vortex angle of the aircraft.

Abstract: Disclosed is a method of and system for gathering off-body pressure signature data from a scaled model in a wind tunnel. The data is gathered using a probe having multiple longitudinally disposed static pressure ports. Because of the number of ports and their spacing, the probe is able to remain stationary in the tunnel for the entire range of Mach numbers and model positions to be tested. Thus, tunnel flow characteristics can be easily and effectively removed. The system also has an automated model positioning system which enables settings at different pitch, yaw, and roll angles. This enables the user to locate the model so that it can be traversed at a fixed distance above the probe while maintaining the desired angular orientation of the model. By repeatedly traversing the model at different angular orientations, a detailed and accurate off-body pressure distribution can be obtained. The wind tunnel test technique captures full off-body pressure signatures in a complete 360 degree azimuthal range.

Abstract: An air data system and method for a rotary aircraft is described. The air data system includes a plurality of flush ports connected via tubing to a plurality of air flow sensors that can measure air flow speeds as low as approximately 0.02 knots. The flush ports are arranged around a main rotor shaft and below a rotor hub of the rotary aircraft to help reduce the impact of rotor downwash. The flush ports and tubing permit air to flow into the air flow sensors, which allows the plurality of air flow sensors to measure speed and direction of cross-wind components of air flow surrounding the rotary aircraft.

Abstract: The invention relates to a device for ensuring safe movement of a moving part. The movement of the moving part is guided along or about an axis (4; 42) and is limited by at least one stop (1; 20; 51). The device comprises means for recording the exceeding of a nominal force by a force exerted on the stop (1; 20; 51) by the moving part along or about the axis (4; 42). The invention is particularly applicable to angle-of-attack sensors used in aeronautics.

Abstract: Methods and systems are described for a system for obtaining information regarding a flow. These methods and systems comprise a signal generator configured to generate an alternating current signal at a carrier frequency and a transformer arranged to receive the generated signal, wherein the transformer and carrier frequency are selected so that the generated signal resonates at the carrier frequency. The alternating signal is then used to cause plasma to form across a gap between two electrodes, wherein the voltage drop across the gap is directly proportional to the flow's velocity. This voltage may then be measured to determine the flow velocity.

Abstract: A wind gauge includes a wind vane. The wind vane includes at least one wing. The wind vane is adapted to assume a prescribed level position responsive to a prescribed corresponding wind speed incident on the wind vane.

Abstract: The present invention provides a first axial support that allows of the weathervane to rotate and a second axial support that prevents the weathervane from becoming dislodged from the first axial support.

Abstract: A structure for reducing turbulence and increasing flow uniformity in a flowing fluid in a wind tunnel, or a fluid channel, has a plurality of conduits or channels arranged into a conduit bundle. The conduit bundle has a number of parallel conduits with plurality of perforations on the inner side walls of the conduit. As the fluid flows through the conduit bundle the sides of the conduits reduce lateral turbulence while the perforations minimize pressure gradients in the flowing fluid in adjacent conduits, resulting in isotropic turbulence. The invention is particularly useful in testing aircraft, improving engine performance, and fluid mechanics applications.

Abstract: A pressure distribution measurement system for measuring a pressure distribution on a measurement object. A flexible sheet-form pressure detection member includes a plurality of pressure passages extending in parallel and a pressure detection hole opened in each of the pressure passages is affixed to a surface of an outer plate of a main wing W of an airplane. Each of the pressure passages is connected to a pressure measurement device via a pressure pipeline. Because the pressure detection hole is opened in the pressure detection member, that is, the pressure detection hole is not required to be opened in the outer plate of the main wing, the outer plate is not damaged. Further, because the flexible sheet-form pressure detection member conforms well to the three dimensionally curved surface of the outer plate and has a small thickness, the airflow is hardly disturbed at all, thereby enhancing pressure distribution measurement accuracy.

Abstract: A weather station with at least one element mounted on bearings on a housing or rack on a vertical axis for alignment with the direction of the wind and with a measuring device, which depending on the angle position of the element aligning in the direction of the wind provides an electrical signal, wherein the measuring device is an opto electric measuring device with at least two light paths. Each of the at least two light paths has its own light-emitting element and which have a common light detector and form a light path configuration, each light path is used to scan a group of markings, which are located around an axis of at least one screen in such a manner that the markings provide a code when scanning that defines the angle area of the position of the element aligning with the direction of the wind. The light-emitting elements determine the angle position of the element aligning with the direction of the wind.