Flight Condition Indicating System Patents (Class 701/14)
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Publication number: 20150073628Abstract: A system and method are provided for integrating and displaying the collective cue and the pitch and roll cue of a helicopter display with a flight path marker providing a moving reference showing the aircraft flight path.Type: ApplicationFiled: September 9, 2013Publication date: March 12, 2015Inventors: James Alexander Nicholls, Patricia May Ververs, Gang He, Marc Lajeunesse, Mark Sutter
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Patent number: 8977482Abstract: An apparatus for generating flight-optimizing trajectories for a first aircraft includes a receiver capable of receiving second trajectory information associated with at least one second aircraft. The apparatus also includes a traffic aware planner (TAP) module operably connected to the receiver to receive the second trajectory information. The apparatus also includes at least one internal input device on board the first aircraft to receive first trajectory information associated with the first aircraft and a TAP application capable of calculating an optimal trajectory for the first aircraft based at least on the first trajectory information and the second trajectory information. The optimal trajectory at least avoids conflicts between the first trajectory information and the second trajectory information.Type: GrantFiled: September 28, 2012Date of Patent: March 10, 2015Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Mark G. Ballin, David J. Wing
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Patent number: 8977484Abstract: A method is provided for inferring the aircraft intent of an aircraft from an observed trajectory. Aircraft performance data relating to that type of aircraft is retrieved from memory, along with atmospheric conditions along the observed trajectory. An initial set of candidate aircraft intents is generated. Each aircraft intent provides an unambiguous description of how the aircraft may be flown that allows a determination of an unambiguous resulting trajectory. A computer system calculates a trajectory defined by each candidate aircraft intent and forms a cost function from a comparison of each calculated trajectory to the observed trajectory. An evolutionary algorithm evolves the initial candidate aircraft intents, wherein the evolutionary algorithm uses a multi-objective cost function to obtain a cost function value that measures the suitability of each candidate aircraft intent.Type: GrantFiled: August 22, 2013Date of Patent: March 10, 2015Assignee: The Boeing CompanyInventor: Marco La Civita
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Patent number: 8976042Abstract: Present novel and non-trivial system, device, and method for combining image data received from two or more vision systems are disclosed. A system may be comprised of a first vision source, a second vision source, and an image generator (“IG”). The first vision source may be could configured to generate a first image data set and a depth buffer data set, and the second vision data source could configured to generate a second image data set. The IG could be configured to receive both the first and second image data sets; the depth buffer data set; and generate a third image data set as a function of both image data sets, the depth buffer data set, and a pixel cutoff distance that may be fixed or variable. In addition, the pixel cutoff distance may be determined as a function of input variable data.Type: GrantFiled: September 24, 2012Date of Patent: March 10, 2015Assignee: Rockwell Collins, Inc.Inventors: Daniel Y. Chiew, Roger L. Yum, Travis S. Vanderkamp, Alexander D. Reid, Carlo L. Tiana, Weston J. Lahr
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Publication number: 20150066254Abstract: Methods and systems for determining a change of speed of an aircraft for enabling the avoidance of conflicts between aircraft trajectories. The method of determining a change in speed of an aircraft, comprises the steps of: defining a merge point and a tie point; monitoring a first aircraft; determining when the first aircraft passes the tie point; providing trajectory data; predicting a trajectory of a second aircraft using the trajectory data; defining a minimum permissible longitudinal spacing; predicting a longitudinal spacing between the first and second aircraft at the merge point based on the predicted trajectory; and if the minimum permissible longitudinal spacing is greater than the predicted longitudinal spacing then calculating a proposed change in speed of the second aircraft that will result in the longitudinal spacing between the first and second aircraft at the merge point being greater than or equal to the minimum permissible longitudinal spacing.Type: ApplicationFiled: August 28, 2014Publication date: March 5, 2015Inventors: Christian Grabow, Lars Fucke
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Patent number: 8972083Abstract: A technique for identifying, projecting, displaying, and enhancing the thermal capacity for an aircraft is disclosed wherein the thermal capacity is defined as the amount of time or range the aircraft can continue until a thermal limit is exceeded.Type: GrantFiled: August 20, 2012Date of Patent: March 3, 2015Assignee: PC Krause and Associates, Inc.Inventors: Kevin M. McCarthy, Eric A. Walters, Alex J. Heltzel
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Patent number: 8972101Abstract: A method of predicting a horizontal stabilizer system fault in an aircraft, where the method includes receiving data relevant to a characteristic of the pitch of the aircraft during flight, comparing the received data to a reference pitch characteristic, predicting a fault in the horizontal stabilizer system based on the comparison, and providing an indication of the predicted fault.Type: GrantFiled: August 28, 2013Date of Patent: March 3, 2015Assignee: GE Aviation Systems LimitedInventors: Christopher Joseph Catt, Mark John Robbins
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Patent number: 8965601Abstract: A present novel and non-trivial system, apparatus, and method is disclosed for presenting a flight director-dependent highway in the sky (“HITS”) pathway on an aircraft display unit. A processor receives flight plan data and flight director data, generates HITS data set representative of a flight director-dependent HITS pathway using flight plan data and flight director data, and provides the HITS data set to a display system for presentation of the flight director-dependent HITS pathway on a tactical display unit. Flight plan data provided to the processor may comprise of data sourced by a navigation system or HITS pathway data generated independently of flight director data. When presented on a tactical display unit, the flight director-dependent HITS pathway may be depicted with the flight director, where the proximal end of the HITS pathway aligns with the flight director.Type: GrantFiled: September 23, 2008Date of Patent: February 24, 2015Assignee: Rockwell Collins, Inc.Inventor: Sarah Barber
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Patent number: 8965603Abstract: A method and a device for protecting an aircraft in the flight phase, said aircraft exhibiting several configurations of slats and flaps, comprises the following steps: determining, for at least one configuration of slats and flaps, of a limit angle of incidence beyond which the aircraft runs a risk of stalling, determining a gain factor as a function of the normal acceleration of the aircraft, comparing the current angle of incidence of the aircraft with the limit angle of incidence weighted by the gain factor, and, emission of an alert indicating that the aircraft runs a risk of stalling, if the current angle of incidence of the aircraft is greater than the limit angle of incidence weighted by the gain factor.Type: GrantFiled: May 24, 2011Date of Patent: February 24, 2015Assignee: ThalesInventors: Bertrand Baillon, Julien Klotz, Laurence Mutuel
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Patent number: 8963742Abstract: A head-up display system includes an aircraft, a predicted flight path generation component that calculates a predicted flight path over a period of time, and a graphic generation component configured to generate a graphical display and project it onto a combiner configured to combine the graphical display with a visual exterior view. A synthetic vision system includes an aircraft, a predicted flight path generation component that receives one or more state parameters and calculates a predicted flight path over a period of time, and a synthetic terrain generation component configured to generate a synthetic view which is displayed on a display. The graphical display and/or the synthetic view includes a three-dimensional depiction of the predicted flight path over the period of time generated utilizing one or more three-dimensional transforms, one or more graphical images based on flight data, and a three-dimensional graphical depiction of a flight plan.Type: GrantFiled: December 2, 2011Date of Patent: February 24, 2015Assignee: Rockwell Collins, Inc.Inventor: Kirschen A. Seah
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Patent number: 8965602Abstract: An aerological phenomena alert device for an aircraft, which comprises onboard equipment capable of detecting meteorological phenomena, comprises: a module for collecting and storing meteorological data originating from the onboard equipment capable of detecting the meteorological phenomena, a module for creating a report from the collected meteorological data, a module for sending the report, a module for receiving reports sent by surrounding aircraft, a module for processing and consolidating the reports received, and for generating alerts when a report signals an aerological phenomenon, and a module for merging the data originating from aircraft and from meteorological stations, situated in a station on the ground and comprising a ground/air communication module for sending meteorological reports adapted to each aircraft according to its position in relation to an aerological phenomenon.Type: GrantFiled: August 28, 2012Date of Patent: February 24, 2015Assignee: ThalesInventors: Daniel Malka, Jean-Charles Marin, Engin Oder
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Patent number: 8958931Abstract: A computer-implemented system and method for the collection, filtering, and transmission of aviation information is disclosed. A plurality of flight information is received over a digital network at various remote locations, and the data is filtered prior to transmission to a central database for presentation and use. The database includes aviation information. The method of filtration is dynamically updated as to information concerning a specific flight based on one characteristic of the flight. As to aircraft being tracked, a determination is made as to which receiver should relay collected data, and that determination is periodically revised, such as to minimize transmission costs and maximize signal quality as aircraft positions change. Once the information is located in the central database, it is suitable for use in responding to user requests for flight tracking information is association with at least one identified flight.Type: GrantFiled: May 7, 2012Date of Patent: February 17, 2015Assignee: FlightAware, LLCInventors: Daniel Baker, David Cameron McNett, Karl Lehenbauer, Mark L. Duell, Jr.
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Patent number: 8958932Abstract: Systems and methods to mitigate instrument landing system (ILS) overflight interference are disclosed. An example method performing a first measurement of a position of an aircraft relative to a first location based on an instrument landing system, performing a second measurement of the position of the aircraft based on inertial measurements performed over a first time period occurring prior to the first measurement, performing a third measurement of the position of the aircraft based on inertial measurements performed over a second time period greater than the first time period and occurring prior to the first measurement, and generating guidance information based on a selected one of the first, second, or third measurements of the position of the aircraft.Type: GrantFiled: February 11, 2013Date of Patent: February 17, 2015Assignee: The Boeing CompanyInventor: Tim Murphy
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Patent number: 8958945Abstract: A method of providing maintenance to an aircraft having multiple aircraft systems and a method of operating an aircraft having multiple aircraft systems, with at least some of the aircraft systems outputting one or more visual indicia indicative of a status of a system of the aircraft where the method provides information based on such visual indicia. An aircraft system for at least one of operating and maintaining the aircraft, which may retrieve information based on such visual indicia.Type: GrantFiled: February 7, 2012Date of Patent: February 17, 2015Assignee: GE Aviation Systems LLCInventor: Norman Leonard Ovens
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Patent number: 8954208Abstract: A highly reliable aerodynamic coefficient estimate can be computed, and computation of this aerodynamic coefficient estimate enables accurate detection of control surface failure/damage while reducing a discomfort for passengers. A deflection angle command signal generation means (5) generates a deflection angle command signal for estimating an aerodynamic coefficient indicating the aerodynamic characteristics of an airframe. A kinetic state quantity acquisition means (6) acquires a kinetic state quantity of the airframe that is obtained as a result of a control surface provided on the airframe being moved based on the deflection angle command signal. A candidate value calculation means (7) calculates candidate values for estimating the aerodynamic coefficient from the kinetic state quantity using two or more different estimations. An aerodynamic coefficient estimate determination means (8) determines an aerodynamic coefficient estimate based on the candidate values.Type: GrantFiled: March 16, 2011Date of Patent: February 10, 2015Assignee: Mitsubishi Heavy Industries, Ltd.Inventor: Koichi Yamasaki
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Patent number: 8954260Abstract: Methods and systems are provided for assessing a target proximate a vehicle. A location and a velocity of the target are obtained. The location and the velocity of the target are mapped onto a polar coordinate system via a processor. A likelihood that the vehicle and the target will collide is determined using the mapping.Type: GrantFiled: June 15, 2010Date of Patent: February 10, 2015Assignee: GM Global Technology Operations LLCInventors: Daniel Gandhi, Chad T. Zagorski
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Patent number: 8954264Abstract: The different advantageous embodiments provide a system comprising an environmental waypoint insertion process and a processor unit. The processor unit is configured to run the environmental waypoint insertion process. The environmental waypoint insertion process is configured to receive information. The environmental waypoint insertion process determines whether and how to suggest additional waypoints for insertion into a flight plan to a subscriber.Type: GrantFiled: April 15, 2014Date of Patent: February 10, 2015Assignee: The Boeing CompanyInventors: Louis J. Bailey, Ryan D. Hale
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Patent number: 8948937Abstract: Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the energy of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given operational state.Type: GrantFiled: July 26, 2012Date of Patent: February 3, 2015Assignee: Airbus Operations SASInventors: Florian Constans, Mickael Lefebvre
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Patent number: 8948938Abstract: An alerts and procedures management system for an aircraft comprises a software kernel aboard the aircraft and a parameterization tool for the software kernel, which comprises a conversion module for converting a configuration file describing an operational need of the system into a database of binary parameters which is able to parameterize the software kernel. The software kernel comprises at least four elementary cells: a first cell for acquiring aircraft signals, a second cell for characterizing state variables of the aircraft, a third cell for computing at least one separate event, a fourth cell for scheduling the separate events for communication with the crew; each of the cells comprising a software engine parameterizable by the database.Type: GrantFiled: April 24, 2013Date of Patent: February 3, 2015Assignee: ThalesInventors: Xavier Chazottes, Stéphane Bertheau, Michel Mazenoux
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Patent number: 8948933Abstract: A flight management system (FMS) including a plurality of FMS components that can include a civil FMS component and a tactical FMS component. Each FMS component can have a processor programmed to execute an FMS software product. The FMS can also include a multi core FMS manager configured to control a plurality of flight management systems and coupled to the plurality of FMS components. The multi core FMS manager can include a plurality of FMS managers, each coupled to one of the FMS components, and a platform interface manager coupled to an avionics system. Each FMS manager can be adapted to transmit flight management data to, and to receive flight management data from, the FMS component to which it is coupled. The platform interface manager can be adapted to provide each FMS component access to the avionics system, such that an aircraft operator can control each FMS component via the FMS.Type: GrantFiled: November 15, 2011Date of Patent: February 3, 2015Assignee: Lockheed Martini CorporationInventors: Lester J. Pangilinan, John Olsen
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Patent number: 8942882Abstract: Systems and methods for managing the exchange of vehicle information between software modules with different safety importance. In one embodiment, a vehicle health management system includes a mission critical software module, a flight critical software module and a gatekeeper. The mission critical software module receives vehicle state information and provides it to the flight critical software module if the gatekeeper confirms the validity of the vehicle information.Type: GrantFiled: June 12, 2007Date of Patent: January 27, 2015Assignee: The Boeing CompanyInventors: Kevin Swearingen, Kirby J. Keller
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Patent number: 8942923Abstract: Method of determining navigation parameters for a carrier by a hybridization device comprising a Kalman filter (3) formulating a hybrid navigation solution on the basis of inertial measurements calculated by a virtual platform (2) and of raw measurements of signals emitted by a constellation of satellites delivered by a satellite positioning system (GNSS), characterized in that it comprises, the steps of: —determination, for each satellite, of at least one likelihood ratio (Ir, Ir?) between a hypothesis regarding a fault of a given nature of the satellite and a hypothesis regarding an absence of fault of the satellite, —declaration, of a fault of a given nature on a satellite as a function of the likelihood ratio (Ir, Ir?) associated with this fault and of a threshold value, —estimation of the impact of the declared fault on the hybrid navigation solution, and ?correction of the hybrid navigation solution as a function of the estimation of the impact of the declared fault.Type: GrantFiled: July 9, 2010Date of Patent: January 27, 2015Assignee: Sagem Defense SecuriteInventors: Didier Riedinger, Houcine Chafouk
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Patent number: 8942831Abstract: Apparatus and methods for controlling a system that operates responsive to a plurality of input control signals are disclosed. During operation the system generates a plurality of output status/control signals. A master controller has at least first and second controllers. The first controller outputs and inputs signals over a first communication path, and the second controller outputs and inputs signals over a second communication path. The first and second controllers output signals based on input signals received over the first and second communication paths, respectively, and also based on stored control data. A plurality of input/output modules are provided. Each of the input/output modules has first and second slave controllers. The first slave controller of each of the input/output modules inputs and outputs signals over the first communication path to the first controller, and the second slave controller outputs and inputs signals over the second communication path.Type: GrantFiled: August 9, 2010Date of Patent: January 27, 2015Assignee: EI Electronics LLCInventors: Karl A. Davlin, Adel George Tannous, Alan R. Loudermilk
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Patent number: 8942867Abstract: A procedure and a device for the determination of current airspeeds [13] of a rotorcraft [2] in a stationary flight regime and/or at low speeds. A calculation system [1] incorporates two pairs of polynomial calculation laws [9] [10] that are executable successively by pairs. A pair of first polynomial laws [9] calculates estimated airspeeds [11], consisting respectively of longitudinal and lateral airspeeds, and is constructed through multilinear regression based on parameters relating to simulated flight points [17] defined by means of a flight simulator [18]. A pair of second polynomial laws [10] calculates the current airspeeds based on the estimated airspeeds [11], and is constructed through multilinear regression based on parameters relating to test-flight points defined by means of test flights [25].Type: GrantFiled: June 5, 2013Date of Patent: January 27, 2015Assignee: Airbus HelicoptersInventors: Jerome Gardes, Jean-Paul Pinacho, Philippe Gaulene
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Publication number: 20150019048Abstract: A method for providing a display to a flight crew of an aircraft includes the steps of providing a synthetic image comprising a first field of view forward of a direction of travel of the aircraft and providing a sensory image overlaying at least a first portion of the synthetic image. The sensory image includes a second field of view forward of the direction of travel of the aircraft. At least a portion of the first field of view and a portion of the second field of view overlap one another. The sensory image is centered within the synthetic image with respect to a horizontal axis. The method further includes moving the sensory image so as to overlay at least a second portion of the synthetic image such that the sensory image is no longer centered with respect to the horizontal axis within the synthetic image.Type: ApplicationFiled: July 15, 2013Publication date: January 15, 2015Inventors: Kiran Gopala Krishna, Saravanakumar Gurusamy
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Publication number: 20150019049Abstract: Passenger aircraft includes seats, display screens facing the seats, and oxygen masks. When oxygen masks are deployed, imperative imagery is displayed that urges the passenger to at least don their oxygen mask, then optionally help others, etc. In some of these embodiments, the passenger aircraft further includes input devices. Each passenger can enter an input that indicates they have donned the mask, so as to see further imagery for guidance. These inputs could be stored in the flight data recorder for subsequent analysis. In some embodiments, passengers enter self-reported data using the input devices. The self-reported data can be stored in the flight data recorder for subsequent analysis of situations, such as when oxygen masks have been deployed.Type: ApplicationFiled: November 22, 2013Publication date: January 15, 2015Inventor: Peter Apostolos Kavounas
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Publication number: 20150019050Abstract: A device comprising a display unit which is configured to display, on a screen of the cockpit of the aircraft, a pitch bar illustrating a pitch order and means for adapting the direct gain of the pitch law used to the effective manual behavior of the pilot in order to obtain a homogeneous response from the aircraft.Type: ApplicationFiled: July 9, 2014Publication date: January 15, 2015Inventors: Simon Oudin, Guilhem Puyou, Jean Muller, Lilian Ronceray
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Publication number: 20150012155Abstract: The invention relates to an aircraft including a fuselage and a first measuring probe including means for measuring the local incidence, means for measuring the static pressure, and optionally means for measuring the total pressure.Type: ApplicationFiled: July 3, 2014Publication date: January 8, 2015Applicant: THALESInventor: Jacques MANDLE
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Patent number: 8930049Abstract: A method of using a light detection system for increasing the accuracy of a precision airdrop is described. Radiation is transmitted to target areas between an airborne vehicle and a dropzone target. Scattered radiation is received from the target areas. Respective wind characteristics are determined from the scattered radiation and a wind velocity map is generated, based on the respective wind characteristics, between the airborne vehicle, and at least the dropzone target. An aerial release point for the precision airdrop is computed based on the generated wind velocity map and a location of the dropzone target.Type: GrantFiled: May 31, 2012Date of Patent: January 6, 2015Assignee: Optical Air Data Systems, LLCInventors: Priyavadan Mamidipudi, Elizabeth A. Dakin, Daniel C. Dakin, Philip L. Rogers, Edgar K. Dede, Peter Gatchell, Madhukiran Panabakam, Lance Leclair, Chia-Chen Chang, Rupak Changkakoti
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Patent number: 8924047Abstract: In the field of the calculation of the approach trajectory of an aircraft, and relating to a method for determining a corrected lateral approach trajectory as a function of the energy to be reabsorbed before the landing, and also to a flight management system making it possible to determine the corrected lateral trajectory, a method comprises: determining an energy of the aircraft Eaero upon crossing the runway threshold on the basis of a predetermined approach trajectory and of a current state of the aircraft, said state comprising at least one current altitude, a current ground speed and a mass of the aircraft; comparing the energy Eaero with a predetermined maximum energy Emax, and when the energy Eaero is greater than the energy Emax, determining the corrected lateral approach trajectory as a function of the difference between the energy of the aircraft Eaero and the maximum energy Emax.Type: GrantFiled: March 7, 2013Date of Patent: December 30, 2014Assignee: ThalesInventors: Emmanuel Dewas, Vincent Savarit, Francois Coulmeau
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Patent number: 8924137Abstract: According to aspects of the embodiments, there is provided an apparatus and method to synchronize trajectories from independent systems such as from a flight management system and the ground Air traffic control during the entire history of a flight. Since a number of trajectory discrepancy factors will intervene during the lifetime of a flight, such as a change in flight intent, controller intervention, or large deviations of the actual flight from the predicted trajectory due to prediction errors, there is need to dynamically monitor these deviations and control a dynamic synchronization cycle. A dynamic trajectory synchronization algorithm attempts to bring each of the systems back into balance whenever a disturbance causes an imbalance.Type: GrantFiled: September 14, 2012Date of Patent: December 30, 2014Assignee: Lockheed Martin CorporationInventors: David So Keung Chan, Joel Klooster, Sergio Torres
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Patent number: 8924046Abstract: A combined stand-by instrument intended to be fitted to the instrument panel of an aircraft, and a method for calibrating the combined stand-by instrument, comprises anemobarometric sensors, inertial sensors, a magnetic field sensor, a screen and a computer making it possible to determine and to display on the screen an altitude, a speed, an attitude and a current heading of the aircraft on the basis of the sensors and to calibrate the magnetic field sensor. The computer is configured to allow the simultaneous display on the screen of the altitude, of the speed and of the attitude of the aircraft as well as a guide for the calibration of the magnetic field sensor.Type: GrantFiled: November 22, 2011Date of Patent: December 30, 2014Assignee: ThalesInventors: Damien Gerthoffert, Florent Colliau, Yves Jaulain
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Publication number: 20140379177Abstract: This invention easily estimates the amount of a utilizable torque in real time based on limited engine performance parameters, regardless of abrupt variations in the engine performance. A torque estimation apparatus (12) of a helicopter (10) stores in a storage apparatus (14) a measurement point that is a measured value of the torque of an engine (28) with respect to a measured value of an engine performance parameter that relates to performance of the engine that rotates a rotor (26) together with a time at which the measurement point is measured, generates an approximate expression based on the measurement point that is stored in the storage apparatus (14), and estimates the amount of a utilizable torque based on the generated approximate expression.Type: ApplicationFiled: March 14, 2013Publication date: December 25, 2014Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventor: Tetsuya Takasaki
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Patent number: 8918271Abstract: An electronic flight planning system is provided, arranged to implement a preferred method for identifying conflicts between flight plans for aircraft. In the preferred method, the system receives, as data input from one or more users, a plurality of flight plans each defining a flight by an aircraft; the system determines, for each aircraft and its respective received flight plan, a three-dimensional region of potential conflict, representative both of the uncertainty in the position of the aircraft and of a region of air exclusion appropriate for the aircraft or for the respective received flight plan; and the system determines, on the basis of the determined regions of potential conflict, whether one of the received flight plans is in conflict with any of the other received flight plans.Type: GrantFiled: April 26, 2011Date of Patent: December 23, 2014Assignee: BAE Systems PLCInventors: Steven Pendry, Timothy Hood
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Patent number: 8917191Abstract: A system for controlling an image displayed on a display unit of an aircraft is shown and described. The system includes an enhanced vision system that detects elements of an approach lighting system for display on the display unit. The system also includes a synthetic vision system that uses a database of navigation information and a determined aircraft location to generate synthetic display elements representing the approach lighting system. Display electronics of the system cause the detected elements from the enhanced vision system to be simultaneously displayed on the display unit within a same scene as the generated synthetic display elements from the synthetic vision system. Advantageously, the simultaneous display allows a pilot viewing the display unit to check for whether information provided by the enhanced vision system matches information provided by the synthetic vision system.Type: GrantFiled: September 22, 2011Date of Patent: December 23, 2014Assignee: Rockwell Collins, Inc.Inventors: Carlo L. Tiana, Kenneth A. Zimmerman, Robert B. Wood
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Patent number: 8914164Abstract: 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: GrantFiled: August 2, 2013Date of Patent: December 16, 2014Assignee: Honeywell International Inc.Inventors: Visvanathan Thanigai Nathan, Thanga Anandappan
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Patent number: 8914165Abstract: A Human Machine Interface includes a flight control system operable to communicate display data directly to a cockpit display system.Type: GrantFiled: March 29, 2011Date of Patent: December 16, 2014Assignee: Hamilton Sundstrand CorporationInventors: Christopher Noll, Steven A. Avritch
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Patent number: 8909395Abstract: A system and method for aircraft performance predictions for climb flight phase is disclosed. In one embodiment, a method of aircraft performance predictions for climb flight phase in a flight management system (FMS) includes determining current predicted aircraft state using a total energy of the aircraft. Further, excess energy available in an engine of the aircraft is computed. Furthermore, a change of speed of the aircraft is computed at a given point in the climb flight phase. Kinetic energy (KE) change required is then computed for the computed speed change. Remaining energy available is then computed based on the computed KE change. The aircraft performance predictions for the climb flight phase are then computed using the determined current predicted aircraft state.Type: GrantFiled: April 28, 2012Date of Patent: December 9, 2014Assignee: Airbus Engineering Centre IndiaInventors: Veeresh Kumar Mn, Dinesh Kumar Kushwaha, Chaitanya Pavan Kumar
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Patent number: 8907798Abstract: An ice detection system comprising a first group of sensors and a second group of sensors. The first group of sensors is located in a first group of locations on an aircraft. The first group of sensors in the first group of locations is configured to detect a first type of icing condition for the aircraft. The second group of sensors is located in a second group of locations on the aircraft. The second group of sensors in the second group of locations is configured to detect a second type of icing condition for the aircraft.Type: GrantFiled: January 5, 2012Date of Patent: December 9, 2014Assignee: The Boeing CompanyInventors: Charles Steven Meis, Cris Kevin Bosetti
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Publication number: 20140358334Abstract: Aircraft and instrumentation systems are provided. An aircraft includes a display surface, at least one projector, at least one deep sensor, and a controller. The display surface is configured to display images with aircraft information. The at least one projector is oriented to project the images onto the display surface. The at least one deep sensor is configured to generate a signal indicative of a location of an object relative to the display surface. The controller is configured to generate tasks when the signal generated by the at least one deep sensor indicates that the object is touching the display surface. The controller is further configured to generate tasks based on a movement pattern of the object that is indicated by the signal generated by the at least one deep sensor.Type: ApplicationFiled: May 30, 2013Publication date: December 4, 2014Inventors: Simón Octavio Colmenares, Ed Wischmeyer
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Publication number: 20140358335Abstract: An indication system and method for detecting and displaying the relative position during fuel transfer. The system comprises a first input device configured to be capable of detecting the extended length from the tanker aircraft of elongated hose and to be capable of sending the detected length of elongated hose to the control module. The control module is operably connected to a display and configured to be capable of receiving an input signal from the input device of hose extension, transforming it into a corresponding output signal of the position of the receiver aircraft inside a refueling range of limit positions and sending the corresponding output signal to the display, which is configured to be capable of displaying information indicating the position of the receiver aircraft inside the refueling range of limit positions.Type: ApplicationFiled: May 29, 2014Publication date: December 4, 2014Inventor: Unai Sanchez Ruiz
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Publication number: 20140358333Abstract: Embodiments are directed to determining, by a computing device comprising a processor, at least one parameter associated with a rotorcraft, obtaining, by the computing device, a profile of a vibration associated with the operation of the rotorcraft based on the at least one parameter, determining, by the computing device, an amplitude of the vibration using the profile, and determining, by the computing device, an airspeed of the rotorcraft based on amplitude.Type: ApplicationFiled: May 30, 2013Publication date: December 4, 2014Inventors: Matthew A. White, Harshad S. Sane
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Patent number: 8903571Abstract: Systems and methods communicate sensor data pertaining to detected weather between aircraft. An exemplary system has at least one sensor on a transmitting aircraft, wherein the sensor is configured to detect weather and configured to output sensor data. The system has a first transceiver on the transmitting aircraft that is configured to transmit a signal with the sensor data. And the system has a second transceiver on a receiving aircraft that is configured to receive the signal containing the sensor data transmitted by the first transceiver. The sensor data of the transmitting aircraft is fused with sensor data of the receiving aircraft for a geographic region of interest to extend the effective sensor coverage and to resolve at least one of a location conflict and a severity conflict between the sensor data of the transmitting aircraft and the receiving aircraft.Type: GrantFiled: August 18, 2008Date of Patent: December 2, 2014Assignee: Honeywell International Inc.Inventor: James C. Kirk
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Patent number: 8897932Abstract: Disclosed is a flight control support device which sets a flight restricted area W along a terrain, thereby achieving improvement in safety of a small aircraft A and sufficiently securing the degree of freedom of flight course selection of a pilot. The flight control support device includes a terrain information acquirer, an aircraft information acquirer, a flight restricted area setter which sets the flight restricted area W along the terrain on the basis of the terrain information acquired by the terrain information acquirer and the aircraft information acquired by the aircraft information acquirer, and a flight control supporter which supports flight control of a flying object on the basis of the flight restricted area set by the flight restricted area setter.Type: GrantFiled: June 7, 2010Date of Patent: November 25, 2014Assignee: Toyota Jidosha Kabushiki KaishaInventors: Kosuke Komatsuzaki, Masatsugu Ishiba
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Publication number: 20140343762Abstract: An interactive task organizer application may encourage a pilot to be more alert and engaged while operating the aircraft, despite that automation has made the job more passive. The interactive task organizer application may have access to flight data, and may use this data to create a virtual environment that encourages pilots to perform flight related tasks and to make visible explicit mission goals at a global and local level.Type: ApplicationFiled: May 16, 2013Publication date: November 20, 2014Applicant: AIRBUS OPERATIONS S.A.S.Inventors: Florence Buratto, Amelie Beaudroit
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Publication number: 20140343763Abstract: The display device (1) comprises data capture means (2), calculation means (3) and a display screen (4), said calculation means (3) being configured to calculate at least one maximum slope that the aircraft can adopt depending on the data received from the data capture means (2), said device (1) also being configured to display said calculated maximum slope on at least a portion (5) of the display screen (4), which is configured to display a vertical flight plan.Type: ApplicationFiled: May 14, 2014Publication date: November 20, 2014Applicant: AIRBUS OPERATIONS (SAS)Inventors: Thomas KOEBEL, Boris KOZLOW, Maxime WACHENHEIM
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Patent number: 8886369Abstract: A method and apparatus for displaying a predicted path on a vertical profile to operate a vehicle. A path is predicted for the vehicle in response to an event occurring. The path has a turning section and a straight section after the turning section. A portion of terrain relative to the path predicted for the vehicle is identified. A vertical profile view of the terrain is displayed, including the portion of the terrain relative to the path predicted for the vehicle.Type: GrantFiled: February 11, 2010Date of Patent: November 11, 2014Assignee: The Boeing CompanyInventors: Frank C. Sharkany, John Tarbaux
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Patent number: 8886372Abstract: Touch or proximity sensors are integrated into control devices such as knobs, dials or wheels incorporated in a user control panel. A control output processor detects whether any of the sensors are outputting signals indicating that a control device is being touched (or nearly touched) by a user. The control output processor causes an associated display area to be highlighted or otherwise modified on a display screen to indicate to the user which control device is being touched. This feature allows for “no-look” interaction with control panels, and keeps the user's eyes focused on the relevant displays where the control devices produce effects. This allows users to preview and verify that the correct control device is being manipulated prior to taking any (potentially erroneous) control actions.Type: GrantFiled: September 7, 2012Date of Patent: November 11, 2014Assignee: The Boeing CompanyInventors: Mark Ivan Nikolic, Stephen Minarsch
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Patent number: 8886450Abstract: The present invention is directed to a system and method for identifying maneuvers for a vehicle in conflict situations. A plurality of miss points are calculated for the vehicle and as well as object conditions at which the vehicle will miss an impact with the at least one other object by a range of miss distances. The miss points are displayed such that a plurality of miss points at which the vehicle would miss impact by a given miss distance indicative of a given degree of conflict is visually distinguishable from other miss points at which the vehicle would miss impact by greater miss distances indicative of a lesser degree of conflict. The resulting display indicates varying degrees of potential conflict to present, in a directional view display, a range of available maneuvers for the vehicle in accordance with varying degrees of conflict.Type: GrantFiled: February 20, 2007Date of Patent: November 11, 2014Assignee: Commonwealth Scientific and Industrial Research OrganisationInventors: David John Gates, Elliot Ashley Gates, Mark Westcott, Neale Leslie Fulton
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Patent number: 8884808Abstract: A system for detecting and determining remote atmospheric anomalies is furnished with a movable-beam anemometry probe for measuring the orthogonal projection onto the sighting axis, named the radial component, of a relative velocity remotely, with respect to a remote air mass by Doppler frequency shift. The system comprises means for determining wind heterogeneities remotely, on the basis of at least two successive measurements, at one and the same remote point, of the radial component of the relative velocity of the system with respect to the remote air mass, by said anemometry probe, the line of sight of said anemometry probe comprising said remote point during said successive measurements.Type: GrantFiled: February 1, 2010Date of Patent: November 11, 2014Assignee: ThalesInventor: Jacques Mandle