Of Aircraft Patents (Class 702/144)
  • Patent number: 11320224
    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.
    Type: Grant
    Filed: July 30, 2020
    Date of Patent: May 3, 2022
    Assignee: Armaments Research Company, Inc.
    Inventors: William Deng, Michael Canty
  • Patent number: 11293709
    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.
    Type: Grant
    Filed: July 30, 2020
    Date of Patent: April 5, 2022
    Assignee: Armaments Research Company, Inc.
    Inventors: William Deng, Michael Canty
  • Patent number: 11293712
    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.
    Type: Grant
    Filed: August 18, 2020
    Date of Patent: April 5, 2022
    Assignee: Armaments Research Company, Inc.
    Inventors: William Deng, Michael Canty
  • Patent number: 11293711
    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.
    Type: Grant
    Filed: August 18, 2020
    Date of Patent: April 5, 2022
    Assignee: Armaments Research Company, Inc.
    Inventors: William Deng, Michael Canty
  • Patent number: 11225882
    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.
    Type: Grant
    Filed: May 30, 2019
    Date of Patent: January 18, 2022
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Heiko Mikat, Nikhil Reddy Podduturi, Juan Carlos Cabrejas
  • Patent number: 11215416
    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.
    Type: Grant
    Filed: July 30, 2020
    Date of Patent: January 4, 2022
    Assignee: Armaments Research Company, Inc.
    Inventors: William Deng, Michael Canty
  • Patent number: 11131519
    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.
    Type: Grant
    Filed: August 18, 2020
    Date of Patent: September 28, 2021
    Assignee: Armaments Research Company, Inc.
    Inventors: William Deng, Michael Canty
  • Patent number: 10746563
    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.
    Type: Grant
    Filed: May 9, 2018
    Date of Patent: August 18, 2020
    Assignee: Rosemount Aerospace Inc.
    Inventors: Jaime Sly, Brian Brent Naslund
  • Patent number: 10365296
    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.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: July 30, 2019
    Assignee: Innovative Solutions & Support, Inc.
    Inventor: Shahram Askarpour
  • Patent number: 10358232
    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.
    Type: Grant
    Filed: June 27, 2017
    Date of Patent: July 23, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Nicolas Certain, Lionel Pignier
  • Patent number: 9932127
    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.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: April 3, 2018
    Assignee: Rosemount Aerospace Inc.
    Inventors: Kaare Josef Anderson, Brian Daniel Matheis, Derrick D. Hongerholt, William Kunik
  • Patent number: 9779185
    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
    Type: Grant
    Filed: March 25, 2013
    Date of Patent: October 3, 2017
    Assignee: ASELSAN ELEKTRONIK SANAYI VE TICARET ANONIM SIRKETI
    Inventors: Inci Yuksel Ergun, Melih Gunay
  • Patent number: 9096330
    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.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: August 4, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Visvanathan Thanigai Nathan, Thanga Anandappan
  • Patent number: 9052392
    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.
    Type: Grant
    Filed: November 15, 2011
    Date of Patent: June 9, 2015
    Assignee: Mitsubishi Electric Corporation
    Inventors: Kenji Inomata, Masahiro Watanabe, Hiroshi Araki, Takahisa Murakami
  • Publication number: 20150025835
    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.
    Type: Application
    Filed: July 11, 2014
    Publication date: January 22, 2015
    Inventors: Gregory Baral-Baron, Xavier Lacondemine, Elisabeth Lahalle, Gilles Fleury
  • Patent number: 8914253
    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.
    Type: Grant
    Filed: December 8, 2010
    Date of Patent: December 16, 2014
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: James H. Africa, Jr., Thomas G. Poley, Joshua C. Hickland
  • Patent number: 8914164
    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.
    Type: Grant
    Filed: August 2, 2013
    Date of Patent: December 16, 2014
    Assignee: Honeywell International Inc.
    Inventors: Visvanathan Thanigai Nathan, Thanga Anandappan
  • Patent number: 8868257
    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).
    Type: Grant
    Filed: May 16, 2012
    Date of Patent: October 21, 2014
    Assignee: Airbus Helicopters
    Inventors: Alain Kirchhofer, Patrick Garcia, Francois Mandonnaud
  • Publication number: 20140257745
    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.
    Type: Application
    Filed: July 27, 2012
    Publication date: September 11, 2014
    Inventor: Robert Schegerin
  • Publication number: 20140229139
    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.
    Type: Application
    Filed: February 6, 2014
    Publication date: August 14, 2014
    Inventors: Matthias HEGENBART, Nabankele-Martial SOMDA
  • Patent number: 8761970
    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.
    Type: Grant
    Filed: October 21, 2008
    Date of Patent: June 24, 2014
    Assignee: The Boeing Company
    Inventors: Melville Duncan Walter McIntyre, Andrew William Houck, Russell Tanner Bridgewater, Robert E. Freeman, Paul Salo, Douglas L. Wilson, Jonathan K. Moore
  • Patent number: 8744800
    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.
    Type: Grant
    Filed: September 22, 2011
    Date of Patent: June 3, 2014
    Assignee: Rockwell Collins, Inc.
    Inventor: Mark Billsberry
  • Patent number: 8738317
    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.
    Type: Grant
    Filed: June 9, 2011
    Date of Patent: May 27, 2014
    Assignee: Airbus Helicopters
    Inventors: Jean Paul Petillon, Antoine Carayon
  • Patent number: 8718971
    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.
    Type: Grant
    Filed: October 7, 2011
    Date of Patent: May 6, 2014
    Assignee: Thales
    Inventor: Jacques Mandle
  • Patent number: 8612172
    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.
    Type: Grant
    Filed: September 19, 2006
    Date of Patent: December 17, 2013
    Assignee: Nokia Corporation
    Inventors: Lauri Wirola, Kimmo Alanen
  • Patent number: 8566054
    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.
    Type: Grant
    Filed: November 20, 2009
    Date of Patent: October 22, 2013
    Assignee: The Boeing Company
    Inventors: Charlotte L. Schweigert, Thomas J. Small, John W. Porter
  • Patent number: 8552888
    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.
    Type: Grant
    Filed: March 31, 2011
    Date of Patent: October 8, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Jean-Damien Perrie, Valérie Brivet, Stéphane Saint-Aroman
  • Patent number: 8527233
    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.
    Type: Grant
    Filed: September 27, 2010
    Date of Patent: September 3, 2013
    Assignee: The Boeing Company
    Inventor: Melville Duncan Walter McIntyre
  • Patent number: 8515677
    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.
    Type: Grant
    Filed: July 12, 2010
    Date of Patent: August 20, 2013
    Assignee: Smart Drilling and Completion, Inc.
    Inventor: William Banning Vail
  • Patent number: 8509968
    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.
    Type: Grant
    Filed: March 20, 2012
    Date of Patent: August 13, 2013
    Assignee: The Boeing Company
    Inventors: Gregory T. Saccone, Ryan D. Hale, Nicholas P. G. Impert, Louis J. Bailey
  • Publication number: 20130204544
    Abstract: The disclosed embodiments relate to methods and systems for determining airspeed of an aircraft.
    Type: Application
    Filed: February 3, 2012
    Publication date: August 8, 2013
    Applicant: GULFSTREAM AEROSPACE CORPORATION
    Inventor: Jason Thomas
  • Patent number: 8467979
    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.
    Type: Grant
    Filed: October 8, 2010
    Date of Patent: June 18, 2013
    Assignee: Alluvial Joules, Inc.
    Inventor: Zbigniew S. Sobolewski
  • Patent number: 8352187
    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.
    Type: Grant
    Filed: November 20, 2009
    Date of Patent: January 8, 2013
    Assignee: Airbus Operations SAS
    Inventors: Jean-Damien Perrie, Guillaume Preaux
  • Publication number: 20120316824
    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.
    Type: Application
    Filed: December 8, 2010
    Publication date: December 13, 2012
    Applicant: United States Government, as represented by the Secretary of the Navy
    Inventors: James H. Africa, JR., Thomas G. Poley, Joshua C. Hickland
  • Patent number: 8306778
    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.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: November 6, 2012
    Assignee: Embraer S.A.
    Inventors: Bruno Paes Leao, Joao Paulo Pordeus Gomes
  • Patent number: 8234037
    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.
    Type: Grant
    Filed: May 19, 2008
    Date of Patent: July 31, 2012
    Assignee: Airbus Operations SAS
    Inventors: Philippe Goupil, Jean-Jacques Aubert
  • Publication number: 20120089362
    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.
    Type: Application
    Filed: October 7, 2011
    Publication date: April 12, 2012
    Applicant: THALES
    Inventor: Jacques MANDLE
  • Publication number: 20120078540
    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.
    Type: Application
    Filed: September 27, 2010
    Publication date: March 29, 2012
    Applicant: THE BOEING COMPANY
    Inventor: Melville Duncan Walter McIntyre
  • Patent number: 8095251
    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.
    Type: Grant
    Filed: September 21, 2006
    Date of Patent: January 10, 2012
    Assignee: Airbus France
    Inventor: Guillaume Preaux
  • Patent number: 7941250
    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.
    Type: Grant
    Filed: September 26, 2008
    Date of Patent: May 10, 2011
    Assignee: Eurocopter
    Inventor: Bernard Certain
  • Patent number: 7907066
    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).
    Type: Grant
    Filed: September 26, 2008
    Date of Patent: March 15, 2011
    Assignee: Eurocopter
    Inventor: Bernard Certain
  • Publication number: 20100305782
    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.
    Type: Application
    Filed: May 26, 2010
    Publication date: December 2, 2010
    Inventors: David Linden, David William Yoel
  • Patent number: 7796054
    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.
    Type: Grant
    Filed: October 19, 2007
    Date of Patent: September 14, 2010
    Assignee: Vertical Power, Inc.
    Inventors: Marc Ausman, Kevin DeVries
  • Publication number: 20100131230
    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.
    Type: Application
    Filed: November 20, 2009
    Publication date: May 27, 2010
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Jean-Damien Perrie, Guillaume Preaux
  • Patent number: 7583200
    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.
    Type: Grant
    Filed: October 20, 2006
    Date of Patent: September 1, 2009
    Assignee: SNECMA
    Inventor: Valerio Gerez
  • Publication number: 20090089006
    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).
    Type: Application
    Filed: September 26, 2008
    Publication date: April 2, 2009
    Applicant: EUROCOPTER
    Inventor: Bernard CERTAIN
  • Patent number: 7428471
    Abstract: A user in locomotion on foot during an outing may identify a grade of a surface with at least one device supported by the user. A performance parameter of the user may be determined with the device based upon the grade of the surface, which may be based upon a measured physiological parameter of the user. An average foot contact time and an average pace of a user during a first outing may be identified and a relationship between them may be determined. No other average foot contact times or average paces identified during a different outing may be used to define the relationship. A single user-specific calibration contestant may define a relationship between foot contact times of a user and corresponding paces of the user, wherein no other user-specific calibration constants are used to define the relationship.
    Type: Grant
    Filed: October 27, 2006
    Date of Patent: September 23, 2008
    Assignee: NIKE, Inc.
    Inventors: Jesse Darley, Thomas P. Blackadar
  • Patent number: 7428472
    Abstract: A device supported by a user while the user is in locomotion on foot during an outing may monitor a performance parameter of the user. The performance parameter may comprise a pace and/or a speed of the user. Prior to the outing, the device may be configured to specify a first interval and second interval, corresponding to a first and second performance zone, respectively, for the outing. Each performance zone may be different from one another and each zone may comprise one of a zone of paces and a zone of speeds. During the first interval, an action may be taken with the device in response to determining that the monitored performance parameter has fallen outside of the first performance zone. During the second interval, an action may be taken with the device in response to determining that the monitored performance parameter has fallen outside the second performance zone.
    Type: Grant
    Filed: February 13, 2007
    Date of Patent: September 23, 2008
    Assignee: NIKE, Inc.
    Inventors: Jesse Darley, Thomas P. Blackadar
  • Patent number: 7315805
    Abstract: A discrete event simulation (DES) and method of model development provide affordable, accurate, pre-validated, reusable and portable models and simulations that capture the complexity, interdependencies and stochastic nature of the operations and support (O&S) of weapons systems. A model of the O&S problem is created based on a service use profile (SUP) that describes a logical structure of delivery, maintenance, deployment, testing policy, infrastructure and logistics constraints. That model is translated into a DES, preferably using a “toolkit” including common attributes for the weapons and pre-validated common blocks and sub-models that define higher level functionality. The DES calculates a time-based prediction of weapons availability, maintenance activities, and spare parts stock over a life cycle of the weapons system.
    Type: Grant
    Filed: February 5, 2004
    Date of Patent: January 1, 2008
    Assignee: Raytheon Company
    Inventor: Robert D Slater
  • Patent number: 7275013
    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.
    Type: Grant
    Filed: September 20, 2005
    Date of Patent: September 25, 2007
    Assignee: University of Notre Dame DuLoc
    Inventors: Eric Matlis, Thomas Corke, Sivaram Gogineni