Abstract: Aircraft air data is estimated using a neural network trained to be independent of any signals from air data sensors whose values are based on air flow pressure measurements.

Abstract: A method of facilitating piloting a hybrid rotorcraft having at least one propulsive rotor provided with a plurality of first blades and a lift rotor provided with a plurality of second blades, the hybrid rotorcraft having a power plant. The method includes a step of displaying on a single indicator a first pointer, the position of which along a movement path varies as a function of a first power from the power plant that is consumed by the propulsive system, and of displaying a second pointer, the position of which varies as a function of a second power of the power plant that is consumed by the lift rotor, a variable space between the first pointer and the second pointer representing a power margin from the power plant that is not used so long as the first pointer is situated between the first end and the second pointer.

Abstract: Systems and methods are provided for firearm monitoring and remote support of a plurality of firearms within a deployment location, wherein each firearm includes one or more sensors that record sensor information used to produce a signal, a response infrastructure configured for deployment to the deployment location, and a server device running application software that uses the signals received from each of the firearms to detect a threat within the deployment location and causes the deployment of the response infrastructure to the deployment location, wherein the response infrastructure supports users of the plurality of firearms in addressing the detected threat.

Abstract: Systems and methods are provided for firearm monitoring and remote support of a plurality of connection points within a deployment location, wherein each connection point of the plurality of connection points is configured to receive signals produced at one or more firearms proximate to the connection point within the deployment location, wherein each connection point of the plurality of connection points is further configured to communicate the received signals to a server device located outside of the deployment location, and a server device, wherein the server device runs application software that receives the signals from each of the connection points and uses the sensor information included in the signals to detect a threat within the deployment location.

Abstract: Methods, apparatuses, and systems for predicting radio altimeter failures are provided. An example method may include determining a first plurality of altitude values associated with a first radio altimeter, determining a second plurality of altitude values associated with a second radio altimeter, calculating a first level feature based at least in part on the first plurality of altitude values and the second plurality of altitude values, and determining a radio altimeter failure indicator based at least in part on the first level feature.

Abstract: Systems and methods are provided for weapon systems monitoring and remote support, including application software that receives signals from a plurality of weapons, each weapon including a plurality of sensor types. A connection point may receive signals from the weapons within a deployment location, including sensor information recorded using sensors associated with the weapons and video from at least one camera. The application software may receive the signals from the connection point and process the signals to generate a graphical user interface representing positions and orientations of the weapons within the deployment location, the graphical user interface further presenting video of areas in proximity to each of the firearms, where the application software automatically updates the graphical user interface based on signals indicating changes in the positions and orientations of one or more of the weapons and related video content.

Abstract: Systems and methods are provided for weapon monitoring, including monitoring a plurality of users, each of the plurality of users having a respective one of a plurality of weapons, receiving signals from the plurality of weapons regarding usage thereof, displaying, via a display device, a graphical representation of geospatial positioning of the weapons, and providing, in response to detecting the change in operating state, an updated graphical representation, the updated graphical representation providing indicia of the change in the operating state.

Abstract: Systems and methods are provided for weapon monitoring and action tagging, including storing a defined weapon action, wherein the defined weapon action is defined based on an inertial measurement from a weapon, the inertial measurement data indicative of at least one of a movement of the weapon, an orientation of the weapon, or a direction of the weapon, receiving sensor information from a weapon, wherein the sensor information includes inertial measurement data, evaluating the sensor information to determine the presence of the defined weapon action, and displaying, in response to determining that the defined weapon action occurred, indicia communicating the occurrence of the defined weapon action to a viewer via a graphical interface.

Abstract: Systems and methods are provided for weapon systems monitoring and remote support, including a connection point that receives signals from a plurality of weapons systems within a deployment location, the signals including weapon system type for each of the plurality of weapons systems and sensor information recorded using sensors of the weapons systems. A server device may run application software that receives the signals from the connection point and processes the signals to generate a graphical user interface representing positions and orientations of the weapons systems within the deployment location. The graphical user interface may further represent cones of fire for each of the weapons systems, wherein the application software automatically updates the graphical user interface based on signals indicating changes in the positions and orientations of one or more of the weapons systems.

Abstract: A method for determining a measured variable comprises the following steps: a) providing a data record comprising values of a plurality of input variables and values of the measured variable; b) ascertaining correlations between the values of the input variables and the values of the measured variable; c) creating a sensor model on the basis of the ascertained correlations; d) acquiring at least one further value of at least one of the input variables; and e) determining a value of the measured variable on the basis of the at least one further value of at least one of the input variables and the sensor model wherein the values of at least one of the input variables in steps a) and/or e) have been determined, in turn, according to steps a) to e). Further, a sensor system and a gas turbine engine are provided.

Abstract: A weapon monitoring and remote support system monitors firearms and other assets within a deployment location, and includes a graphical user interface providing a top-down geographic view of the deployment location and coverage areas of weapons within the deployment location, the coverage areas representing positions and orientations of the weapons determined based on sensor information received from one or more sensors of each of the weapons. The graphical user interface may automatically update according to received sensor information, where the updated graphical user interface represents a change to at least one of the coverage areas of weapons, and output instructions for displaying or rendering the graphical user interface to one or more computing devices.

Abstract: Systems and methods are provided for weapon system monitoring and virtual deployment presentation, including a connection point that receives signals from a plurality of weapons within a deployment location, the signals including sensor information recorded using sensors of the weapons, a server device running application software that receives the signals from the connection point and processes the signals to generate a virtual reality depiction of the deployment location, and a graphical user interface presenting a field of view of the virtual reality depiction of the deployment location with icons indicating at least one of the positions, orientations or affiliations of the plurality of weapons.

Abstract: A system and method for an aircraft includes an air data system and an acoustic sensing system. The air data system includes a pitot tube positioned to sense a pitot pressure of an airflow about an exterior of the aircraft, and an angle of attack vane positioned to sense an angle of attack of the aircraft. The pitot pressure and the angle of attack are used to determine first air data parameters. The acoustic sensing system is configured to emit acoustic signals about the exterior of the aircraft and sense the acoustic signals as sensed data. The sensed data is used to determine second air data parameters.

Abstract: Methods and systems for compensating for the absence or loss of a sensor measurement in a heading reference system such as an aircraft attitude and heading reference system, integrated standby unit, or vehicle inertial system, provides an estimate of the lost sensor measurement by estimating the bank angle after a detected vehicle turn. The estimate of the bank angle may also be used to estimate the vehicle's speed. Additionally, when the lost sensor measurement is a temperature measurement, the described methods and systems offer an improvement over estimating air temperature using a standard (e.g., ISA) model. The methods and systems also allow for the refinement of computed estimates using filtering techniques, such as low-pass or Kalman filtering. The methods may be iteratively repeated for each detected turn in order to maintain an accurate estimate of the lost sensor measurement or other estimates, such as vehicle speed.

Abstract: A method and a device for detecting that a rotorcraft is approaching a vortex domain. After previously determining a limit advance speed threshold and a limit vertical speed threshold defining a limit for said rotorcraft entering into a vortex domain, a predictive advance speed and a predictive vertical speed for said rotorcraft are calculated, said predictive vertical speed being calculated differently depending on the value of said instantaneous advance speed. Thereafter, said predictive advance speed and said predictive vertical speed are compared with said thresholds, which may be thresholds with hysteresis, in order to determine whether said rotorcraft is approaching a vortex domain, and if so to signal this situation to a pilot of said rotorcraft.

Abstract: In one example, a method includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.

Abstract: The present invention relates to a system comprising threat evaluation and sensor/weapon assignment algorithm operating units which are adapted such that they will operate any threat evaluation and sensor/weapon assignment algorithm, a simulation and analysis unit which is adapted such that it will form the area, in which threat evaluation and sensor/weapon assignment algorithms will be operated, as a virtual scenario by forming an air picture in accordance with the data it receives, an external communication unit which is in communication with the simulation and analysis unit; which can communicate correspondingly with a threat evaluation and sensor/weapon assignment algorithm operating unit; which is adapted such that it will transfer the current scenario information to the threat evaluation and sensor/weapon assignment algorithm when it is necessary and transfer the engagement results to the simulation and analysis unit by taking them back, and a communication unit which is adapted such that it will transf

Abstract: A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.

Abstract: A velocity measurement apparatus comprising: first and second surface profile sensors for acquiring first and second surface profile data, a memory for storing the first and second surface profile data, and a calculation unit for calculating a velocity of a moving object. Each surface profile sensors acquires the corresponding surface profile data by measuring signal levels of reflected waves corresponding to a radio wave emitted to a ground surface and then reflected from structures on the ground surface, and measuring propagation durations from the emission of the radio wave to the return of the respective reflected waves. The calculation unit compares the first and second surface profile data, determines a difference between their measurement times, and divides a distance between the first and second surface profile sensors by the difference between the measurement times to calculate the velocity of the moving object.

Abstract: The invention relates to the measurement of the speed of an aircraft by Doppler laser anemometry, the aircraft being equipped with a LiDAR using coherent detection.

Abstract: A computer-implemented analysis method is provided for identifying a flight trajectory of a bogey relative to earth's surface. The method includes a first step of obtaining first and second altitudes and velocities of the bogey separated by a first time interval. The second step calculates a first difference between the first and second velocities divided by the first time interval to obtain an acceleration vector. The third step determines the direction of the velocity vector. The fourth step determines whether direction of the second velocity vector exceeds an upward pointing threshold. The fifth step determines whether the acceleration vector is negative and substantially perpendicular to earth's surface as a second result being valid. The sixth step reports that the bogey represents a ballistic projectile in response to the first and second results.

Abstract: A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.

Abstract: A device (10) for defining a flight path (2) enabling an aircraft (1) to reach a destination (B), said device (10) including a digital terrain model (21) and a display screen (30), and being provided with generator means (15) for generating a flight path (2) including at least one flight segment (3) associated with a flying altitude. The device (10) includes a digital noise database (20) having volumes that are to be avoided, said device (10) having a computer (11) with a main memory (13) containing instructions for displaying on said display screen (30) and as an overlay on a first representation (31) of said terrain as provided by said digital terrain model (21): a second representation (41) of said volumes to be avoided; and a flight path (2) that has been generated by using said generator means (15).

Abstract: The present invention relates to a speed measurement system allowing the relative speed V of a moving body in relation to an ambient air mass to be measured independently of the atmospheric conditions, the moving body being designed to move at least at subsonic and transonic speeds.

Abstract: A method for determining the flight velocity of an aircraft comprising a flow body is provided. The method comprises acquiring a change in length of a structural component connected to the flow body; determining at least one aerodynamic force acting on the flow body based on the acquired change in length of the structural component connected to the flow body; determining a flow coefficient of the flow body; and calculating the incident flow velocity on the flow body, taking into account the determined flow coefficient and the determined aerodynamic force. With this method reliable determination of the flight velocity can take place without measuring the dynamic pressure.

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 distance measuring, device including a lookup table storing values to calibrate a Class AB amplifier to produce a pulse pair with the desired characteristics. The distance measuring device analyzes the characteristics of the output signal and recursively adapts the values stored in a lookup table to force the output the power amplifier to meet the required performance characteristics.

Abstract: The present invention relates to an inertial measurement device secured to a structure of a vehicle for which it is desired to measure speeds and/or accelerations, the device comprising at least one piece of moving equipment in rotation about a stationary axis of rotation Y relative to the structure, said moving equipment including at least two measurement device having respective sensitivity axes X? and Z? that are mutually orthogonal and that lie in a plane perpendicular to the stationary axis of rotation Y, a motor for driving the moving equipment in rotation, device for determining the angular position of the moving equipment, device for responding to the angular position of the moving equipment to determine the projection of the measurements taken in the rotary frame of reference axes X? and Z? by the said at least two measurement device onto a vehicle frame of reference X and Z.

Abstract: A system for determining the true airspeed vector, defined by a magnitude and by a direction, of an aircraft comprising a fuselage, comprises four laser anemometers each having a single measurement path so as to measure a local component of the true airspeed and being distributed in different locations around the fuselage of the aircraft; and means for calculating the magnitude and direction of the true airspeed vector of the aircraft using the four measurements of components of the true airspeed.

Abstract: For supporting a relative positioning, information on barometric pressure at a first device and information on barometric pressure at a second device is converted into a difference in altitude between the first device and the second device. The difference in altitude between the first device and the second device is then used in determining a position of the first device relative to the second device.

Abstract: Embodiments of the present disclosure provide an apparatus and method for managing an orientation of a tab of a control surface of an aircraft comprising an elongate structure having a number of members configured to position the elongate structure to a control surface, a bracket located on the elongate structure, a plurality of indicators located along the elongate structure, and a data processor in communication with the plurality of indicators. The bracket may be positioned against an edge of a tab of the control surface. Each of the plurality of indicators may be configured to generate a number of measurements about an orientation of the tab on the control surface. The data processor may be configured to present information about the orientation of the tab on the control surface.

Abstract: A device calculates a first air speed representing an estimated air speed during flight using measurements of static pressure and total pressure onboard the aircraft. The device includes a storage device for storing in memory, in case of detection of a ground taxiing of the aircraft, the most recently determined value of static pressure corrected from induced aerodynamic effects. As a result, a second air speed representing the estimated air speed during the ground taxiing may be calculated by implementing a correction and using the most recently determined value of static pressure when the ground taxiing of the aircraft is detected. A method for automatically estimating an air speed of an aircraft is also provided.

Abstract: The different advantageous embodiments provide an apparatus and method for identifying an airspeed for an aircraft. In one advantageous embodiment, an apparatus is provided. The apparatus consists of a plurality of pitot-static probes. The plurality of pitot-static probes generate a first data. The apparatus also consists of a plurality of angle of attack sensor systems. The plurality of angle of attack sensor systems generate a second data. The apparatus also consists of a plurality of light detection and ranging sensors. The light detection and ranging sensors generates a third data. The apparatus also consists of a signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of light detection and ranging sensors.

Abstract: Methods and apparatus are described to use real-time measurement systems to detect the onset of compression induced microfracturing of fiber-reinforced composite materials. Measurements are described to detect the onset of compression induced microfracturing of fiber-reinforced composite materials to prevent catastrophic failures of aircraft components containing such materials. Methods and apparatus are described to prevent fluids and gases from invading any compression induced microfractures by coating surfaces of fiber-reinforced materials to reduce the probability of failure of such fiber-reinforced materials.

Abstract: Systems and methods for real-time efficiency and aircraft performance monitoring and delta efficiency calculations between various user- or system-selected phases of flight by determining an efficiency messaging index that gets translated into a messaging profile. That messaging profile is then used to obtain necessary flight and other information from multiple sources. The efficiency calculations and deltas can be used to determine real-time or post-processed benefits, which can then be used to optimize flight(s). Additionally, data is post-processed, which allows the calculation, storage and subsequent usage of efficiency coefficients to enhance the accuracy of the efficiency calculations. There are a number of ways to implement the architecture and order of processing.

Abstract: The disclosed embodiments relate to methods and systems for determining airspeed of an aircraft.

Abstract: The present invention is directed to a system for providing information to an athlete concerning the efficiency with which the athlete is using energy in moving relative to the ground or some other surface. In one embodiment, the system includes a plurality of pressure sensors that are associated with a shoe and generate pressure related data. The system further includes a processing system that processes the pressure data produced by the sensors to determine energy efficiency related information and make this information available to the wearer of the shoe so that the wearer can, if needed or desired, takes steps to improve their energy efficiency.

Abstract: A monitoring system including two laser anemometers and a selection logic device able to select, on the one hand, a value of the IAS air speed to be displayed on first display means and, on the other hand, another value of the IAS air speed to be displayed on second display means.

Abstract: A computer-implemented analysis method is provided for identifying a flight trajectory of a bogey relative to earth's surface. The method includes a first step of obtaining first and second altitudes and velocities of the bogey separated by a first time interval. The second step calculates a first difference between the first and second velocities divided by the first time interval to obtain an acceleration vector. The third step determines the direction of the velocity vector. The fourth step determines whether direction of the second velocity vector exceeds an upward pointing threshold. The fifth step determines whether the acceleration vector is negative and substantially perpendicular to earth's surface as a second result being valid. The sixth step reports that the bogey represents a ballistic projectile in response to the first and second results.

Abstract: A method and system for monitoring and predicting the health of electro-mechanical systems and components includes collecting data for a fixed pattern of actuation of such system or component. This data is used to build statistical models that correspond to a normal state of the system or component. New measurements are compared to this model in order to monitor the health of the system or component. The comparison can be made using a distance calculation. The combination of new measurements with historical data provides the prediction for future health states of the system or component.

Abstract: A method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. The device includes units that count the number of overshoots of a threshold value by the current value of a quantity related to the positional slaving of an airfoil. Oscillatory fault is detected based on the number of overshoots of the threshold value being greater than the current value by a predetermined number.

Abstract: A system for determining the true airspeed vector, defined by a magnitude and by a direction, of an aircraft comprising a fuselage, comprises four laser anemometers each having a single measurement path so as to measure a local component of the true airspeed and being distributed in different locations around the fuselage of the aircraft; and means for calculating the magnitude and direction of the true airspeed vector of the aircraft using the four measurements of components of the true airspeed.

Abstract: The different advantageous embodiments provide an apparatus and method for identifying an airspeed for an aircraft. In one advantageous embodiment, an apparatus is provided. The apparatus consists of a plurality of pitot-static probes. The plurality of pitot-static probes generate a first data. The apparatus also consists of a plurality of angle of attack sensor systems. The plurality of angle of attack sensor systems generate a second data. The apparatus also consists of a plurality of light detection and ranging sensors. The light detection and ranging sensors generates a third data. The apparatus also consists of a signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of light detection and ranging sensors.

Abstract: The disclosed embodiments concerns a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes a device for measuring static air pressure, a device for measuring a side-slip angle of the aircraft, a device for measuring a dynamic pressure, a total air temperature and a angle of attack of the aircraft, and a data-processing device capable of determining anemobaroclinometric parameters from the measurements of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack, a least one laser anemometer to measure at least one true airspeed parameter of the aircraft.

Abstract: A method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator (1) that includes at least: first elements (1?) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; and third elements (3) for calculating the predictive vertical speed vAP of a rotorcraft, the third elements being connected firstly to the first and second elements via respective first and second connections (l1, l2) and containing in memory predetermined values for the minimum-power speed VY and a characteristic constant k that are constants relating to the rotorcraft of a given type of rotorcraft.

Abstract: A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes: first elements (1) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; third elements (3) constituting a database BDD relating to representing at least one instantaneous vortex domain; fourth elements (4) connected via first, second, and third connections (l1, l2, l3) respectively to the first, second, and third elements, the fourth elements being designed to detect the approach to a vortex domain by the rotorcraft; and fifth elements (5) for signaling the approach to a vortex domain by the rotorcraft, the fifth elements being connected to the fourth elements (4) via a connection (l4).

Abstract: An automated airborne video recording system for imaging pipeline or electric line rights-of-way, irrigation canals, or any other linear ground features. The system includes a gimbaled, stabilized camera system, a data recorder, and autonomous imager software that computes the shortest vector between the aircraft position and the pipeline based on the aircraft GPS and the Geographic Information Database. The system then commands the stabilized camera system to point directly at the pipeline regardless of the aircraft position and orientation, automatically collecting continuous NTSC or digital video of the entire right of way.

Abstract: A computer implemented function monitors the position of the magneto switch in an aircraft to provide real-time feedback of engine RPM drop during a magneto (mag) check and communicates whether parameters are within limits. The function can also monitor engine and groundspeed/airspeed data in an aircraft to verify the magneto switch is in the correct position during engine start, takeoff and flight and can provide an alert to the pilot if the switch is not in the correct position. The automated magneto check function provides an easy way to test the operation of the aircraft's engine-driven magnetos and provides additional safety by alerting the pilot to unsafe positioning of the switch.

Abstract: According to the invention, the monitoring system comprises two laser anemometers and a selection logic device able to select, on the one hand, a value of the IAS air speed to be displayed on first display means and, on the other hand, another value of the IAS air speed to be displayed on second display means.

Abstract: A method and system for detecting the variations of speed (R) of a rotor. Signals are measured representative of the march-past of the teeth of a measurement device secured to the rotor for a determined duration (T). The measurements are sampled, digitized and stored to obtain an initial digital vector (B). A detection signal is extracted around a known disturbing frequency (F). The detection signal is compared with a predetermined threshold (SO) and an alert message is delivered in the event of overshoot.