Warning Signal Or Alarm Patents (Class 701/9)
  • Patent number: 10272888
    Abstract: Systems and methods for an aircraft emergency and park brake system are disclosed. The emergency and park brake system may comprise an emergency and park brake controller. The emergency and park brake controller may be configured to receive brake signals from mechanical and electrical inputs, generate a braking command comprising data from the brake signal, and transmit the braking command to control braking force. The emergency and park brake controller may receive brake signals from multiple locations including from the aircraft and from a remote location.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: April 30, 2019
    Assignee: Goodrich Corporation
    Inventors: Efrem E. Ayichew, Eric Daniel Cahill
  • Patent number: 10049081
    Abstract: A system for documenting the state of a component, for example a component present on board a transport device; the use of such a system in a transport device; a transport device having such a system; an associated method for documenting the state of a component; and a computer program for executing the method. The transport device may be an aircraft. The system comprises a central logbook equipment and at least one mobile recording device, the mobile recording device comprising a recording unit for recording items of multimedia information relating to the state of the component, and a transmitting unit for transmitting the recorded items of multimedia information to the central logbook equipment. The central logbook equipment is configured to generate a multimedia logbook entry on the basis of the transmitted items of multimedia information, and to store the generated multimedia logbook entry.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: August 14, 2018
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Wolfram Henkel
  • Patent number: 9909878
    Abstract: An approach for triggering the conveyance of guidance information based on the current line-of-sight of the user is described. A guidance platform processes and/or facilitates a processing of sensor information associated with a device, a user of the device, or a combination thereof to determine (a) line-of-sight information to at least one navigation element, (b) one or more user behavior patterns, or (c) a combination thereof. The guidance platform then determines a timing, a frequency, or a combination thereof of at least one presentation of guidance information based, at least in part, on the line-of-sight information.
    Type: Grant
    Filed: March 5, 2012
    Date of Patent: March 6, 2018
    Assignee: HERE Global B.V.
    Inventor: Jerome Beaurepaire
  • Patent number: 9696160
    Abstract: A method and apparatus for determining routes vehicles (4, 6), the method comprising: measuring positions of a first vehicle and a second vehicle (6); providing a specification of a region (12) having a fixed position in relation to the first vehicle (4); using the measurements and the region specification, determining a first route for the first vehicle (4) and a second route for the second vehicle (6). Determining the routes comprises: constructing a graph (34) within a joint state space (X) of the vehicles (4, 6); identifying, within the graph (34), a path from a first vertex to a second vertex, the first vertex corresponding to the measured positions of the vehicles (4, 6), and the second vertex corresponding to the second vehicle (6) being at least partially located within the region (12); and, using the identified path, determining the first and second routes.
    Type: Grant
    Filed: July 7, 2014
    Date of Patent: July 4, 2017
    Assignee: BAE SYSTEMS plc
    Inventors: Richard Edward Simpson, Arthur George Richards
  • Patent number: 9620024
    Abstract: A system and method are provided for integrating live flight following information provided as Trusted Automatic Dependent Surveillance-Broadcast (ADS-B) data with stored planned flight and other information, and for, in part, comparatively analyzing the data/information to generate automated alerts to one or more end-users when an aircraft is determined to deviate from a planned flight route by a predetermined degree, as specified by adjustable set parameters. Broadcast ADS-B data transmitted by participating aircraft is collected and communicated via a secure, trusted and dependable worldwide network for analysis in a centralized location. The analysis involves, in part, comparing the ADS-B data to other information provided to, or collected by, the centralized location from multiple sources regarding planned routes of flight for participating aircraft and other available information relevant to aircraft operations in particular geographic locations.
    Type: Grant
    Filed: May 13, 2015
    Date of Patent: April 11, 2017
    Assignee: Rockwell Collins, Inc.
    Inventors: Adam Mottram, Brian Creswell, Rolf R. Stefani, James Gary Cooper, Jr.
  • Patent number: 9590728
    Abstract: A mobile device includes an inertial navigation system (INS) to measure inertial quantities associated with movement of the device, and estimate a kinematic state associated with the movement based on the measured inertial quantities. The device includes a light receiver to record light beams originating from lights at respective image positions in a sequence of images. The device photogrammetrically determines its position relative to the originating lights based on predetermined real-world positions and corresponding image positions of the lights. The device corrects the estimated kinematic state based on the photogrammetrically determined position, to produce a corrected estimated kinematic state.
    Type: Grant
    Filed: September 29, 2012
    Date of Patent: March 7, 2017
    Assignee: Intel Corporation
    Inventors: Richard D. Roberts, Xue Yang
  • Patent number: 9511880
    Abstract: Embodiments of a flight deck display system deployed onboard a rotary wing aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a controller operably coupled to a cockpit display device. The controller is configured to: (i) generate a Primary Flight Display (PFD) on the cockpit display device including a vertical speed indicator; (ii) establish a first vertical speed alert threshold; (iii) compare the first vertical speed alert threshold to a current vertical speed of the rotary wing aircraft; and (iv) if the current vertical speed of the rotary wing aircraft exceeds the first vertical speed alert threshold, produce a first vertical speed alert on the PFD by altering the appearance of the vertical speed indicator in a first predetermined manner.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: December 6, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Gang He, Jason F. Harvey
  • Patent number: 9418564
    Abstract: This method for determining an obstacle avoidance guidance law for an aircraft is implemented by a system for determining said guidance law. The aircraft comprises a collision avoidance system adapted to detect a collision risk with the obstacle and said determination system. This method comprises determining one or more set points from among flight path angle and speed set points, at least one set point depending on at least one vertical speed limit value, at least one set point comprising a vertical component in a vertical direction, each limit value being provided by the collision avoidance system following the detection of a collision risk with the obstacle; and computing the avoidance guidance law as a function of the determined set points. During the determination step, at least one determined set point comprises a longitudinal component in a longitudinal direction perpendicular to the vertical direction.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: August 16, 2016
    Assignee: THALES
    Inventors: Matthieu Claybrough, François Colonna, Marc Riedinger
  • Patent number: 9399525
    Abstract: Methods, systems, and computer readable media are disclosed for troubleshooting and repairing an aircraft system failure during abnormal situations of an aircraft's operation. One aspect of a method for implementing the subject matter described herein includes at least one interactive interface configured for troubleshooting and repairing an aircraft system failure. The method also includes displaying at least one or more graphic object representing at least one or more aircraft system and configured for receiving interaction from a user, displaying at least one or more energy flow icon representing the direction of circulation of an energy flow, and displaying at least one or more macro action icon configured for performing an automated action sequence configured for troubleshooting and repairing the system failure.
    Type: Grant
    Filed: February 3, 2014
    Date of Patent: July 26, 2016
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Mael Mesguen, François Buron, Thibaut Poux
  • Patent number: 9324238
    Abstract: The use of dynamic collision avoidance parameters in connection with automatic dependent surveillance, broadcast, as well as for other purposes in systems and methods may assist collision avoidance and/or advisory systems in properly identifying intruders for reporting to pilots. For example, a method can include monitoring for a triggering event with respect to at least one of geographic coordinates and a flight path of an aircraft. The method can also include detecting the triggering event. The method can further include altering at least one characteristic of at least one of a traffic alerting system and an advisory system based on detecting the triggering event.
    Type: Grant
    Filed: May 17, 2011
    Date of Patent: April 26, 2016
    Assignee: Aviation Communication & Surveillance Systems LLC
    Inventors: Gregory T. Stayton, Charles C. Manberg
  • Patent number: 9261883
    Abstract: Systems and methods that alert the pilot of the unusual negative pitch attitude. Additionally, the system can bias a “sink rate” envelope toward a more sensitive direction, such that the pilot can be alerted while (or before) a large sink rate is built up during an unusual negative pitch attitude condition.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: February 16, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Yasuo Ishihara, Steve Johnson, Gary Ostrom
  • Patent number: 9189962
    Abstract: Novel and non-trivial systems and methods for generating and providing alerts in a terrain awareness and warning system (“TAWS”) are disclosed. The systems could be comprised of a navigation system, an airport-related database, a terrain database, a terrain alert processor, and crew alerting system. A phase of flight and flight attitude parameter may be determined based on the location to the nearest airport or runway environment, and a terrain clearance altitude associated with the phase of flight and flight attitude parameter may be added to the highest elevation of a terrain cell over which the aircraft is projected to operate to determine a minimum operating altitude of the terrain cell. If the aircraft altitude is less than any value of minimum operating altitude along the projected flight path, an alert signal is generated.
    Type: Grant
    Filed: September 27, 2007
    Date of Patent: November 17, 2015
    Assignee: Rockwell Collins, Inc.
    Inventor: Patrick D. McCusker
  • Patent number: 9092976
    Abstract: Systems and methods for providing runway entry awareness and alerting. An exemplary system includes a processing device that determines pilot intent based on one of a manual runway selection, automatic runway selection, aircraft information received from one or more sensors or received clearance information; receives at least one of aircraft position or motion information; determines if a no access condition exists based on the received information, the stored airport information and the determined pilot intent; and generates at least one of a hold-short gate still image or animation, if the no access condition exists.
    Type: Grant
    Filed: September 14, 2012
    Date of Patent: July 28, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Ratan Khatwa, Chris Hamblin
  • Patent number: 9043055
    Abstract: A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition.
    Type: Grant
    Filed: December 19, 2012
    Date of Patent: May 26, 2015
    Assignee: GE Aviation Systems LLC
    Inventor: Frazer Leslie Pereira
  • Patent number: 9037321
    Abstract: A taxiway approach advisory system. The system may include a computer-readable memory containing runway information and a processor in data communication with the memory. The processor may include a component for ascertaining the altitude of an aircraft, a component for ascertaining the location of the aircraft, a component for accessing runway information from the memory and determining if the aircraft is within a pre-determined runway envelope based on the altitude and location, and a component for issuing an indication if the aircraft is not within the pre-determined runway envelope.
    Type: Grant
    Filed: July 25, 2006
    Date of Patent: May 19, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Kevin J Conner, Ratan Khatwa
  • Patent number: 9035802
    Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.
    Type: Grant
    Filed: December 22, 2010
    Date of Patent: May 19, 2015
    Assignee: Textron Innovations Inc.
    Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
  • Patent number: 9020681
    Abstract: A method of displaying navigation limits for a planned travel route of a vehicle is presented here. The method calculates estimated navigation limits for the vehicle using an onboard subsystem of the vehicle, where the estimated navigation limits represent self-assessed navigation accuracy of the vehicle relative to the planned travel route. Contracted navigation limits are acquired for the vehicle, where the contracted navigation limits represent specified navigation accuracy of the vehicle, relative to the planned travel route, as mandated by a third party navigation controller. A navigation display is rendered on an onboard display element such that it includes graphical representations of the planned travel route, at least one of the estimated navigation limits, and at least one of the contracted navigation limits.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: April 28, 2015
    Assignee: Honeywell International Inc.
    Inventors: Petr Krupansky, Jiri Vasek, Pavel Kolcarek, Tomas Neuzil, John A. Wise
  • Patent number: 9014878
    Abstract: The present invention relates to a method for detecting the performance of the aircraft comprising: collecting data reflecting operation status of the aircraft; generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft; storing or transmitting the customized message; and detecting the performance of the aircraft based on the customized message.
    Type: Grant
    Filed: July 26, 2012
    Date of Patent: April 21, 2015
    Assignee: Air China Limited
    Inventors: Zhuping Gu, Jiaju Wu, Fengliang Zheng, Lei Huang, Minjie Tang
  • Patent number: 9008870
    Abstract: A terrain warning system includes an indicator to inform a pilot of a proposed degree of flight parameters for safely clearing terrain. An aural message may identify a vertical speed that may be used to safely traverse terrain to the pilot. A visual indicator on a display informs the pilot of a vertical speed or climb angle to traverse terrain. The display may be a vertical speed indicator also capable of displaying traffic advisories.
    Type: Grant
    Filed: March 14, 2003
    Date of Patent: April 14, 2015
    Assignee: Aviation Communication & Surveillance Systems LLC
    Inventors: James Peter Redmond, Richard Darrell Ridenour
  • Patent number: 9002542
    Abstract: A method for detecting piloting conflicts between the crew and the autopilot of an aircraft. According to the method, an automatic trajectory is programmed by checking whether the actual values of navigation parameters converge on said corresponding desired values within a predetermined convergence period; in the case where at least one of the actual values does not converge, within the convergence period, on the corresponding desired value, a predictive calculation is carried out, at consecutive future moments, of the value of at least one particular parameter selected amongst the navigation parameters; and in the case where the predicted value of the particular parameter is higher than a corresponding predefined threshold, an alarm is emitted for the crew of the aircraft to notify them about a piloting conflict being able to jeopardize the flight safety of the aircraft. A device for implementing the method. An aircraft including the device.
    Type: Grant
    Filed: June 4, 2009
    Date of Patent: April 7, 2015
    Assignee: Airbus Operations (SAS)
    Inventors: Frédéric Dehais, Charles Lesire, Catherine Tessier, Laure Christophe
  • Patent number: 8996204
    Abstract: Systems and methods for adjusting target approach speed for use in a “Too Fast” approach to landing condition. An exemplary system stores predefined maximum wind setting and a predefined reference speed and a pilot set bug speed value. A processing device sets a target speed equal to the bug speed, if the bug speed is less than the reference speed plus a value associated with a predefined maximum wind setting, and sets the target speed equal to the reference speed plus the max wind added value, if the manual bug speed is not less than the reference speed plus the max wind added value. An output device outputs an alert if the received aircraft speed is greater than the set target speed plus a predefined error value when the received aircraft location is within a threshold value of a touchdown point.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: March 31, 2015
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Steve Johnson
  • Patent number: 8983686
    Abstract: The invention relates to a device aboard an aircraft comprising output means configured to restore information relating to the aircraft status from aircraft systems, the device including a module providing interface between said output means and said aircraft systems, said module being configured to synthesize information from aircraft systems depending on predetermined behavior rules and to transmit said information thus synthesized to said output means.
    Type: Grant
    Filed: May 17, 2011
    Date of Patent: March 17, 2015
    Assignee: AIRBUS Operations S.A.S.
    Inventors: Alexandre Broquet, Yannick Deleris, Raphael Andre, Fabien Pascal
  • Patent number: 8977550
    Abstract: Part units of speech information are arranged in a predetermined order to generate a sentence unit of a speech information set. To each of a plurality of speech part units of the speech information, an attribute of “interrupt possible after reproduction” with which reproduction of priority interrupt information can be started after the speech part unit of the speech information is reproduced or another attribute of “interrupt impossible after reproduction” with which reproduction of the priority interrupt information cannot be started even after the speech part unit of the speech information is reproduced is set. When the priority interrupt information having a high priority rank than the speech information set being currently reproduced is inputted, if the attribute of the speech information being reproduced at the point in time is “interrupt impossible after reproduction,” then the priority interrupt information is reproduced after the speech information is reproduced.
    Type: Grant
    Filed: May 6, 2011
    Date of Patent: March 10, 2015
    Assignee: Honda Motor Co., Ltd.
    Inventor: Tokujiro Kizaki
  • Patent number: 8970399
    Abstract: Methods, systems, and computer-readable storage media provide for selective Notice to Airmen (NOTAM) notifications to be made to the crew of an aircraft according to the relevance of the NOTAM to a selected phase of flight of the aircraft. According to embodiments described herein, NOTAMs are received and parsed for subject and status codes. The subject and status codes are used with the selected phase of flight to determine a relevance code each NOTAM according to a set of relevance rules. The relevance rules provide a level of relevance of the NOTAM to the phase of flight and trigger a type of notification according to that level of relevance.
    Type: Grant
    Filed: August 30, 2010
    Date of Patent: March 3, 2015
    Assignee: The Boeing Company
    Inventors: Nico Zimmer, Keyvan Bayram
  • Patent number: 8965629
    Abstract: A method and system are disclosed herein for confirming a potentially unintended command given to a vehicle. The method includes, but is not limited to, receiving a command from an operator configured to cause actuation of a vehicle system. The method further includes, but is not limited to, detecting a condition of the vehicle. The method further includes, but is not limited to, determining, with a processor, that the command is inconsistent with the condition. The method still further includes, but is not limited to alerting the operator that the command is inconsistent with the condition.
    Type: Grant
    Filed: June 12, 2012
    Date of Patent: February 24, 2015
    Assignee: GM Global Technology Operations LLC
    Inventors: Rami I. Debouk, Barbara J. Czerny
  • Patent number: 8958930
    Abstract: Method for dynamically limiting the inclinations of monoblock flight control surfaces (FCS) in an aircraft. Dynamic limitation of the FCS is activated if a stall susceptibility condition is detected in the current aircraft environment. The real-time calibrated airspeed of the aircraft, real-time angle of attack (AOA) of the aircraft, and real-time sideslip angle (AOS) of the aircraft are obtained. The aircraft parameters may be obtained via estimation if the measured values are deemed unsuitable. The real-time local AOA and AOS of the FCS are calculated based on the obtained aircraft parameters. The inclination of each of the FCS relative to the critical values is dynamically limited according to the calculated real-time local AOA and AOS of the FCS. The aircraft may be an unmanned aerial vehicle (UAV) and/or a V-tail aircraft. The stall susceptibility condition may include icy conditions.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: February 17, 2015
    Assignee: Elbit Systems Ltd.
    Inventor: Dan Malta
  • Patent number: 8948950
    Abstract: In a drive control apparatus (1) of a hybrid vehicle, a provisional target engine power calculator (17D) of a controller (17) compares provisional target engine power which is calculated from a target drive power and a target charge/discharge power with a target engine power lower limit value and, when the provisional target engine power is smaller than the target engine power lower limit value, sets the target engine power lower limit value to the provisional target engine power.
    Type: Grant
    Filed: February 21, 2011
    Date of Patent: February 3, 2015
    Assignee: Suzuki Motor Corporation
    Inventors: Masakazu Saito, Yoshiki Ito, Masaaki Tagawa, Hitoshi Ohkuma, Yukihiro Hosoe
  • Patent number: 8942882
    Abstract: 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: Grant
    Filed: June 12, 2007
    Date of Patent: January 27, 2015
    Assignee: The Boeing Company
    Inventors: Kevin Swearingen, Kirby J. Keller
  • Patent number: 8942831
    Abstract: 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: Grant
    Filed: August 9, 2010
    Date of Patent: January 27, 2015
    Assignee: EI Electronics LLC
    Inventors: Karl A. Davlin, Adel George Tannous, Alan R. Loudermilk
  • Patent number: 8928497
    Abstract: A method monitors at least one avionic system connected to a communication medium that includes at least one active communication switch component. The method includes determining a state of the switch component and evaluating an indicator of a state of the communication medium from the state of the switch component and from a predetermined modeling of communication flows of the communication medium. The method also includes selecting and activating an alarm according to the evaluated state of the communication medium and according to a predetermined modeling of consequences of the evaluated state of the communication medium on a function of the at least one avionic system. A corresponding device and a method for determining conditions for alarm activation are also disclosed.
    Type: Grant
    Filed: May 13, 2008
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations S.A.S.
    Inventors: Jean-Michel Camus, Jerome Grieu, Fabien Cases, Christine Gris, Patrick Ringeard
  • Patent number: 8924047
    Abstract: 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: Grant
    Filed: March 7, 2013
    Date of Patent: December 30, 2014
    Assignee: Thales
    Inventors: Emmanuel Dewas, Vincent Savarit, Francois Coulmeau
  • Patent number: 8909393
    Abstract: Methods of predicting a speed brake fault in an aircraft having a speed brake system including multiple control surfaces, a handle for setting the position of the multiple control surfaces, and at least one control surface position sensor, the methods include receiving a position signal from the at least one position sensor, determining a variation in the position signal and predicting a fault in the speed brake system.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: December 9, 2014
    Assignee: GE Aviation Systems Limited
    Inventors: Christopher Joseph Catt, Julia Ann Howard
  • Patent number: 8897934
    Abstract: Described is a method of protecting an aircraft in approach by signalling against risks of collision with a terrain in steep-sided environments in order to avoid unwanted warnings emanating from clearance sensors of the on-board TAWS (Terrain Awareness and Warning System) while protecting the aircraft when the aircraft fails to observe a published procedure which includes a landing procedure and a take-off procedure. The method, in some embodiments, includes modifying characteristics of at least one of the clearance sensors according to the position deviation of the aircraft relative to a published RNP (Required Navigation Performance) trajectory.
    Type: Grant
    Filed: November 11, 2008
    Date of Patent: November 25, 2014
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty, Aurélie Sallier
  • Patent number: 8897935
    Abstract: This disclosure relates to a system for preventing collisions with a terrain. The system includes a detecting means for detecting risks of collision with the terrain after a predetermined forecasting delay. The system further includes a determining means for determining, based on a trajectory followed by the aircraft, a possible limit point for success of the vertical terrain avoidance maneuver. The system further includes indication means for giving indications on azimuth clearance sections, around the direction in which the aircraft is moving, suitable for success of the vertical terrain avoidance maneuver. The system further includes means for estimating a free-travel distance in each azimuth clearance sector on a straight distancing trajectory with constant gradient and over a distance correspond to more than one minute of flight, the free-travel distance being free of potential conflicts with the terrain.
    Type: Grant
    Filed: August 29, 2007
    Date of Patent: November 25, 2014
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty, Julia Percier
  • Patent number: 8886402
    Abstract: Methods and apparatus are provided for an actively variable shock absorbing system for actively controlling the load response characteristics of a shock absorbing strut. In one embodiment the shock absorbing system comprises a controllable valve adapted for actively varying a load response characteristic of the shock absorbing strut. The shock absorbing system further comprises an electronic control system comprising an input for receiving a signal from a sensor, an algorithm adapted to determine an optimal position for the controllable valve in view of the sensor signal, and an output for sending a control signal to the controllable valve to place the valve in the optimal position.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: November 11, 2014
    Assignee: Armorworks Enterprises LLC
    Inventor: Ken-An Lou
  • Patent number: 8880339
    Abstract: A schematic display for presenting vertical navigation (VNAV) data is disclosed. A planned route such as a flight plan is divided into a series of VNAV legs, and only a VNAV schematic that corresponds to the active VNAV leg is displayed. The VNAV schematic in accordance with the present disclosure is a profile-view schematic for the active VNAV leg, providing a visual representation indicating the locations of the upcoming Top of Climb (TOC) or Top of Descent (TOD). Additional VNAV data may also be presented to provide content context. Since the schematic display in accordance with the present disclosure only displays VNAV data relevant to the active VNAV leg at a given time, the complexities associated with displaying the VNAV schematic is reduced, making the VNAV data easy to read and understand.
    Type: Grant
    Filed: August 21, 2012
    Date of Patent: November 4, 2014
    Assignee: Rockwell Collins Inc.
    Inventors: Seth A. Cooper, David A. Gribble, David L. Leedom, Geoffrey A. Shapiro, Daniel E. Russell, James E. Winfield
  • Patent number: 8868256
    Abstract: A method and system for navigating an unmanned aerial vehicle (UAV) for aerial refueling is described. A system processor in the UAV receives navigation data from a tanker aircraft and calculates a plurality of relative navigation solutions with respect to the tanker aircraft. The system processor compares the plurality of relative navigation solutions to identify any inconsistent solutions. The inconsistent solutions are discarded and the system processor navigates the UAV in position for refueling using the remaining relative navigation solutions.
    Type: Grant
    Filed: May 15, 2006
    Date of Patent: October 21, 2014
    Assignee: Honeywell International Inc.
    Inventor: James D. Waid
  • Patent number: 8862289
    Abstract: A power electronic control circuitry device comprises the following intercommunicating distinct hardware physical entities: a digital microcontroller unit (UNMC) for managing the operation of the device, hardened to withstand the effects of radiations in space; a digital fast regulation unit (UNRR) for controlling priority and real-time processes, hardened to withstand the effects of radiations in space; a digital communication unit (UNC) for communications external to the device, hardened to withstand the effects of radiations in space; a digital tracing and debugging unit (UNTD) for detecting errors in the design of the device; and a digital non-volatile memory (MRN) for storing information representative of the initial configuration of the device, hardened to withstand the effects of radiations in space.
    Type: Grant
    Filed: July 27, 2011
    Date of Patent: October 14, 2014
    Assignee: Thales
    Inventors: Marc Fossion, Marc Durvaux
  • Patent number: 8855906
    Abstract: An aircraft traffic alert system that minimizes false alarms and unnecessary alerts by automatically adjusting the sensitivity of the system based on proximity to an airport. The system also can use information from a flight management system (FMS) or GPS navigation system (GNS) to only adjust the sensitivity near a destination airport and to suppress potential alerts for possible collisions with other aircraft that will be moot based on planned course changes of the subject aircraft. The system also can suppress alerts related to another aircraft when the other aircraft is landing on a parallel runway to the runway on which the subject aircraft is landing. The system may use multiple sensitivity levels based on different airspace classes, each class being associated with a different sensitivity level.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: October 7, 2014
    Assignee: Avidyne Corporation
    Inventors: Daniel J. Schwinn, Edward A. Lester, Dean E. Ryan
  • Patent number: 8838293
    Abstract: The invention relates to a flight management system for aircraft which makes it possible to carry out tests of the results of the calculations of the main functions for formulating the flight plans and trajectories of the aircraft making it possible to anticipate errors in this formulation, to present them to the crew as a function of criticality criteria, to store them so as to be communicated and processed by the maintenance teams.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: September 16, 2014
    Assignee: Thales
    Inventors: Manuel Gutierrez-Castaneda, Guy Deker
  • Patent number: 8830090
    Abstract: Systems and methods are disclosed for displaying the current trends (i.e., turning or going straight) or the future positions of vehicles of interest on a traffic display unit. The position, orientation and geometry of the displayed symbology is a function of parametric information broadcast by the vehicles of interest and processed by a computer system that controls the traffic display unit. In particular examples disclosed herein, the traffic display unit is a navigation display on an aircraft or a traffic display unit at a traffic controller's station. However, the methods disclosed herein have application to vehicular traffic other than aircraft, such as boats or ships.
    Type: Grant
    Filed: July 8, 2011
    Date of Patent: September 9, 2014
    Assignee: The Boeing Company
    Inventor: Syed Tahir Shafaat
  • Patent number: 8825235
    Abstract: An aircraft hover system for enabling an aircraft to hover at a target spatial location represented by GPS location coordinates. The hover system includes a display screen rendering a display including live video feed of the terrain below the airborne aircraft, a first mark overlaying the video feed, the first mark representing the current position of the aircraft relative to the terrain, and a perimeter surrounding the first mark, the portion of the terrain within the perimeter being substantially magnified compared to that of the terrain outside of the perimeter. The hover system is configured such that, as the aircraft approaches the target spatial location, the distance between the first mark and a second mark on the display gradually decreases until and finally the first and second marks coincide; the second mark representing the target spatial location.
    Type: Grant
    Filed: August 29, 2013
    Date of Patent: September 2, 2014
    Assignee: Sandel Avionics, Inc.
    Inventor: Gerald J. Block
  • Patent number: 8825238
    Abstract: A system is provided for monitoring an energy height of an aircraft during landing. The system includes a database including landing distance data; a processing unit configured to receive the landing distance data from the database and to calculate a landing distance of the aircraft based on a velocity and a height of the aircraft, the processing unit further configured to provide display signals based on the landing distance; and a visual display coupled to the processing unit and configured to provide a visual image based on the display signals.
    Type: Grant
    Filed: July 22, 2008
    Date of Patent: September 2, 2014
    Assignee: Honeywell International Inc.
    Inventors: Dave Peptione, Blake Wilson, Roger W. Burgin
  • Patent number: 8825234
    Abstract: A method and apparatus for managing a touch screen system. Data generated by an acceleration detector about acceleration of the touch screen system is received. The acceleration detector is located within the touch screen system. An action is initiated by an input manager when the acceleration of the touch screen system reduces usability of the touch screen system.
    Type: Grant
    Filed: October 15, 2012
    Date of Patent: September 2, 2014
    Assignee: The Boeing Company
    Inventors: Jeffrey L. Williams, Susan Anne Foster, Jason W. Clark, Samantha Ann Schwartz, Aaron Daniel Pilcher
  • Patent number: 8818577
    Abstract: A device includes means for generating and applying to an aircraft protecting orders avoiding a flight with an excessive descent rate. More specifically, the device includes components configured to perform a series of operations including measuring the current vertical speed and the current height of the aircraft and comparing these flight parameters with a safety envelope defining couples of vertical speed and height that are indicative of an excessive descent rate. If the current vertical speed and height are located in the safety envelope, a protection is triggered by generating protecting orders to remove the aircraft from the safety envelope and applying those protecting orders to control surfaces of the aircraft.
    Type: Grant
    Filed: February 9, 2011
    Date of Patent: August 26, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Pascale Louise, Emmanuel Cortet, Erwin Grandperret
  • Patent number: 8803706
    Abstract: A system having a first motion sensor configured to sense movement of an object on a first side of a portal, the object including an RFID tag, a first RFID reader being activated by the first motion sensor when the first motion sensor senses movement of the object, the first RFID reader reading the RFID tag, a second motion sensor configured to sense movement of the object on a second side of the portal and a second RFID reader being activated by the second motion sensor when the second motion sensor senses movement of the object, the second RFID reader reading the RFID tag, wherein, when one of the first and second motion sensors sense movement of the object, the other one of the first and second motion sensors is deactivated for a predetermined period of time.
    Type: Grant
    Filed: July 12, 2013
    Date of Patent: August 12, 2014
    Assignee: AT&T Intellectual Property I, L.P.
    Inventor: Raymond B. Morin
  • Patent number: 8798819
    Abstract: A monitor on-board an aircraft which uses radio altitude measurements as the basic observable altitude during runway approach. The basic concept utilizes the aircraft's navigation system, which includes means to store and retrieve radio altitude thresholds as a function of the distance along the desired path from the runway thresholds. These threshold functions are determined in advance based on a radio altitude reference which is defined as the expected radio altimeter measurement that would be made if the airplane were exactly on the desired reference path. Vertical containment monitoring is achieved by comparing the radio altitude measurement to computed thresholds for both too high and too low. During the approach, an annunciation message can be generated if the radio altitude measurement is above or below the threshold limits.
    Type: Grant
    Filed: June 18, 2013
    Date of Patent: August 5, 2014
    Assignee: The Boeing Company
    Inventor: Timothy Allen Murphy
  • Patent number: 8798815
    Abstract: A system and method display general terrain clearance awareness, whether the aircraft is off route, on airway, off procedure, or on procedure, so altitude thresholds are not violated and EGPWS alerts are avoided, while reducing clutter in displaying the information. Altitude, location, and rate of change in altitude are considered in determining whether the aircraft will exceed the threshold altitude. A flight path or an area to be entered is highlighted when the threshold altitude will be violated by the aircraft with the current flight path. The threshold altitude may be a minimum or maximum allowed altitude, or the terrain.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: August 5, 2014
    Assignee: Honeywell International Inc.
    Inventors: Roger W. Burgin, Dave Pepitone, Jerry Ball, Pramod Kumar Malviya
  • Patent number: 8798844
    Abstract: A method and apparatus diagnoses a correct operation of a phase or star point isolation relay in an electric power steering system of the kind including a motor drive circuit and at least one phase isolation relay which connects a part of the drive circuit to a phase of the motor. The relay is opened during shutdown to isolate the motor phase from the part of the drive circuit and is normally closed during operation of the motor to connect the phase to the part of the drive circuit.
    Type: Grant
    Filed: August 3, 2011
    Date of Patent: August 5, 2014
    Assignee: TRW Limited
    Inventors: Philip Owen Browne, Adrian Szabo
  • Patent number: 8774989
    Abstract: A method and apparatus for displaying an energy state of an aircraft. The energy state of the aircraft is identified by a processor unit based on a speed of the aircraft and an altitude of the aircraft. An indication of the energy state is displayed by the processor unit.
    Type: Grant
    Filed: February 28, 2013
    Date of Patent: July 8, 2014
    Assignee: The Boeing Company
    Inventors: Larry Wayne Bush, Neil John Clark