Phased Warnings For Same Flight Condition Patents (Class 340/964)
  • Patent number: 10082799
    Abstract: A method and device for assisting initiation of a flare maneuver of an aircraft during a landing. The device includes an acquisition unit for acquiring current values of flight parameters of the aircraft, including the current height of the aircraft with respect to the ground, a computation unit for computing a first reference height and a second reference height, corresponding to a height starting from which the aircraft attains a current start of flare height while maintaining its current descent conditions over a predetermined first duration and over a predetermined second duration respectively, and an acoustic emission unit for emitting at least two sound signals in the cockpit of the aircraft, namely a first sound signal when the current height of the aircraft attains the first reference height during the descent and a second sound signal when the current height of the aircraft attains the second reference height during descent.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: September 25, 2018
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Jerôme Bazile, Patrice Rouquette, Matthias Eberle, Philippe Perrin
  • Patent number: 9950681
    Abstract: The method for setting an internal usage scenario of a vehicle is presented, which includes obtaining, by a vehicle-mounted device, identity information of a user and feature information, where the user is a user who is using a vehicle in which the vehicle-mounted device is located, and the feature information is used to represent an internal first usage scenario of the vehicle; sending, by the vehicle-mounted device, the identity information of the user and the feature information to a network device; receiving, by the vehicle-mounted device, an internal usage scenario model of the vehicle sent by the network device, where the model is obtained by the network device based on the identity information of the user and the feature information; and adjusting, by the vehicle-mounted device, a parameter of the vehicle according to the model.
    Type: Grant
    Filed: September 2, 2016
    Date of Patent: April 24, 2018
    Assignee: HUAWEI TECHNOLOGIES CO., LTD.
    Inventor: Li Qian
  • Patent number: 9911342
    Abstract: An avionics wake turbulence awareness system and method for use in an aircraft includes an ADS-B receiver that is adapted to be positioned in an equipped aircraft and receives ADS-B transmissions from other aircraft. A control system is responsive to the ADS-B receiver and determines an identity for each of the other aircraft and determines a movement of each of the other aircraft relative to the equipped aircraft. The control system determines a flight path history of each of the other aircraft from their respective identities and movements relative to the equipped aircraft. An output device is responsive to the control system to provide guidance to a pilot of the equipped aircraft to avoid an encounter with a wake turbulence caution area that is defined by a flight path history of another aircraft.
    Type: Grant
    Filed: May 4, 2016
    Date of Patent: March 6, 2018
    Assignee: L3 Commmunications Avionics Systems, Inc.
    Inventor: Andrew J. Herder
  • 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: 8957790
    Abstract: A monitoring system is disclosed for use with a mobile platform being operated by an operator. The system may make use of a database for containing operational information and procedures relating to the operation of the mobile platform by the operator. A processor may also be used that communicates with the database and with at least one subsystem of the mobile platform for monitoring operational information concerning operation of the mobile platform against stored information contained in the database. The processor may determine if the operation of the mobile platform is proceeding in accordance with predetermined standards.
    Type: Grant
    Filed: January 6, 2009
    Date of Patent: February 17, 2015
    Assignee: The Boeing Company
    Inventors: Bradley D. Cornell, Michael E. Dey
  • Patent number: 8922396
    Abstract: Technologies are described herein for providing an automatic reminder function. The technologies are adapted to receive a definition of a reminder as an occurrence or are non-occurrence of an event and to receive operationally relevant data from a system data device. The technologies then determine whether the operationally relevant data indicates that the reminder is triggered by the occurrence or non-occurrence of the event. Responsive to determining whether the operationally relevant data indicates that the reminder is triggered by the occurrence or non-occurrence of the event, the technologies issue the reminder through instrumentation on an aircraft.
    Type: Grant
    Filed: November 25, 2009
    Date of Patent: December 30, 2014
    Assignee: The Boeing Company
    Inventors: Gordon Robert Andrew Sandell, Bradley David Cornell
  • Patent number: 8902085
    Abstract: An integrated audiovisual threat warning system configured to detect a threat, estimate a relative location of origin of the threat with respect to a host platform with which the system is associated, and to warn an occupant of the host platform of the threat. The system includes an audio processor configured to receive a warning tone, geo-spatial coordinate data from the host platform, and the estimated relative location of origin of the threat, and to process the warning tone based on the geo-spatial coordinate data and the direction information to generate a directional audio warning signal. The system also includes a plurality of speakers configured to audibly project the directional audio warning signal to audibly identify the estimated relative location of origin of the threat, and a display control unit configured to display the estimated relative location of origin of the threat overlaid on a map.
    Type: Grant
    Filed: May 17, 2011
    Date of Patent: December 2, 2014
    Assignee: Raytheon Company
    Inventors: Michael S. Ray, Eric K. Moore, Todd A. Lovell, James A. Negro, Jason J. Braun
  • Patent number: 8744372
    Abstract: A system and method of transmitting data from an aircraft includes a PC card that acquires aircraft data and transmits the aircraft data over a radio frequency communications signal into the skin of the aircraft, which radiates the radio frequency communications signal to a location remote from the aircraft.
    Type: Grant
    Filed: September 5, 2007
    Date of Patent: June 3, 2014
    Assignee: Harris Corporation
    Inventors: James J. Ziarno, Shawn Gallagher
  • Patent number: 8706324
    Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.
    Type: Grant
    Filed: March 23, 2011
    Date of Patent: April 22, 2014
    Assignee: Dassault Aviation
    Inventors: Jérôme Barral, Salvador Lopez, Eric Gerard
  • Patent number: 8548727
    Abstract: Integrated surveillance systems and methods for processing multiple sensor inputs and determining a best route for avoiding multiple hazards. An example method performed on a first aircraft includes generating a plurality of routes for avoiding a previously determined alert from a first advisory system. Then, probability of success information is generated at other advisory systems for each of the plurality of routes. The best route of the plurality of routes is determined based on the generated probabilities and output to the flight crew or other aircraft. The probability of success information includes a previously defined uncertainty value. The uncertainty value corresponds to quality of data provided to or provided by the respective advisory system.
    Type: Grant
    Filed: November 25, 2008
    Date of Patent: October 1, 2013
    Assignee: Honeywell International Inc.
    Inventors: Donald C. Kauffman, Michael Christian Dorneich
  • Patent number: 8504224
    Abstract: The invention relates to a method and a device for monitoring risky atmospheric areas. The invention relates to an onboard device connected to meteorological measurement systems making it possible to calculate danger detection areas in front of the aircraft in order to detect potential areas of penetration of the aircraft into risky atmospheric areas. The areas of intersection between the detection areas and the risky meteorological areas are calculated according to the trajectory of the aircraft stored in the navigation system. The method makes it possible to generate alerts and force the display of the meteorological situation in front of the aircraft in case of danger.
    Type: Grant
    Filed: August 20, 2009
    Date of Patent: August 6, 2013
    Assignee: Thales
    Inventors: Nicolas Marty, Hugues Meunier, Philippe Salmon
  • Patent number: 8493240
    Abstract: An operational flight phase determination, indication and configuration system for an aircraft includes input/output circuitry for receiving an operational flight phase selector output signal, aircraft sensor signals, and on-board automation system output signals including configuration status information. A processor is coupled to the input/output circuitry. A flight phase data table is coupled to the processor. The flight phase data table includes a list of the defined operational flight phases for the aircraft. A flight phase transition rules set is coupled to the processor. The flight phase transition rules set includes flight rules for defining flight phase transitions. An aircraft system configuration data table is coupled to the processor. The aircraft system configuration data table includes a list of the defined configurations for each operational flight phase and the aircraft system configuration settings for each configuration. Program memory and working memory are coupled to the processor.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: July 23, 2013
    Assignee: Rockwell Collins, Inc.
    Inventor: Matthew J. Carrico
  • Patent number: 8380371
    Abstract: A method of producing a variable thrust cutback of an aircraft during aircraft departure is provided. The method includes the steps of storing expected sound exposure levels for an aircraft in memory, and storing a sound exposure level limit for a navigation flight in memory. The method also includes the steps of determining aircraft altitude and determining aircraft airspeed. The method further includes the steps of computing an engine thrust value that complies with the sound exposure level limit based on the altitude, airspeed and the sound exposure levels, and outputting the computed engine thrust value for use in controlling the aircraft during departure.
    Type: Grant
    Filed: December 11, 2007
    Date of Patent: February 19, 2013
    Assignee: General Electric Company
    Inventor: Michael K. DeJonge
  • Patent number: 8319667
    Abstract: A system and method of conveying missed approach procedures to a pilot are provided. The system and method include rendering a graphic representation of at least one leg of the missed approach procedure on a display. A determination is made as to whether the aircraft is at least substantially flying the at least one leg of the missed approach procedure. At least one visual characteristic of the rendered graphic is selectively varied based on the determination of whether the aircraft is at least substantially flying the at least one leg of the missed approach procedure.
    Type: Grant
    Filed: March 11, 2008
    Date of Patent: November 27, 2012
    Assignee: Honeywell International Inc.
    Inventors: Roger W. Burgin, Blake Wilson, Sandy Wyatt
  • Patent number: 8306677
    Abstract: The invention relates to a method for automatic detection of turbulence by a second aircraft, by information exchange between the second aircraft and at least a first aircraft. The first aircraft has means for transmitting information and the second aircraft has means for receiving the information transmitted by the first aircraft. The method includes the identification of information about turbulence liable to be encountered by the second aircraft, by analyzing the information received from the first aircraft. An alarm is activated on the basis of the turbulence information.
    Type: Grant
    Filed: November 19, 2007
    Date of Patent: November 6, 2012
    Inventors: Guy Deker, Jérôme Sacle, François Coulmeau
  • Patent number: 8294596
    Abstract: Disclosed is to an aircraft radiofrequency communication system. The system includes at least one at least one radiofrequency transceiver device that is configured to transmit and receive data according to a VDL mode 3 standard and to receive status information that relates to at least one radio link of the radiofrequency transceiver device and includes the status concerning the possibility of transmitting on a particular, selected frequency. In one embodiment, a man/machine interface unit is configured to display configuration information and at least a portion of the status information. In an alternative embodiment, at least one radiofrequency transceiver device is configured to further determine status information that represents a possibility of using the radiofrequency transceiver device in transmission.
    Type: Grant
    Filed: October 24, 2005
    Date of Patent: October 23, 2012
    Assignee: Airbus Operations SAS
    Inventors: Isabelle Lavielle, Michel Le Toullec
  • Patent number: 8280622
    Abstract: A system indicating to a pilot that an aircraft has passed the limit-point of success of a standard vertical avoidance maneuver is disclosed. To determine the limit-point, the system monitors a penetration of a model of the terrain being flown over into a first protection volume linked to the aircraft and configured so as to model a standard vertical avoidance maneuver path executed without delay. To determine disengagement azimuth sectors, the system monitors the penetrations of the model of the terrain being flown over into a second protection volume with large azimuth aperture, linked to the aircraft and configured so as to contain the limit-point protection volume and, for the various azimuths covered, paths of a composite maneuver beginning with change-of-heading maneuvers with which to reach the azimuth concerned and continuing with the standard terrain vertical avoidance maneuver.
    Type: Grant
    Filed: October 31, 2006
    Date of Patent: October 2, 2012
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty
  • Patent number: 8217807
    Abstract: An operational flight phase determination and indication system for an aircraft includes input/output circuitry for receiving an operational flight phase selector output signal and aircraft sensor signals. A processor is coupled to the input/output circuitry. A flight phase data table is coupled to the processor. The flight phase data table includes a list of the defined operational flight phases for the aircraft. A flight phase transition rules set is coupled to the processor. The flight phase transition rules set includes flight rules for defining flight phase transitions. Program memory and working memory are coupled to the processor. The processor uses input from the input/output circuitry, the flight phase data table, the flight phase transition rules set, the program memory and the working memory to provide an operational mode signal indicating the operational mode of the aircraft.
    Type: Grant
    Filed: July 16, 2009
    Date of Patent: July 10, 2012
    Assignee: Rockwell Collins, Inc.
    Inventor: Matthew J. Carrico
  • Patent number: 8115655
    Abstract: The invention relates to a method and a system for monitoring the temperature of an aircraft, in which at least one camera connected to a first processing unit, for imaging detection of at least one region of the substantially upwardly-pointing outer surface of the aircraft, detects an images once, several times, or at regular intervals and transmits this to the first processing unit, wherein the light spectrum which may be detected by the camera lies substantially in the infrared range and the first processing unit determines the temperatures of substantially all the pictorially detected locations or has these determined by a downstream signal-processing device, in each case compares the temperature for individual locations with a predetermined maximum design temperature for the relevant location, and if the maximum design temperature is exceeded, generates a warning signal.
    Type: Grant
    Filed: December 19, 2008
    Date of Patent: February 14, 2012
    Assignee: Airbus Operations GmbH
    Inventors: Christian Pautsch, Wolfgang Wohlers
  • Patent number: 7957853
    Abstract: A method, system and computer program product to detect and indicating TFR zone violations, potential TFR zone violations or TFR zones in vicinity of an aircraft and indicating measures to avoid or exit a TFR zone are provided. TFR zone information and an aircraft's position information are received. The aircraft's position information is processed to determine the aircraft's current heading. A TFR zone violation is determined based on the aircraft's current position. A potential TFR violation is determined based on whether the aircraft's current heading intersects a TFR zone. The presence of a TFR zone in the vicinity of the aircraft is determined based on the aircraft's current position and heading. Indicators of a TFR violation, potential TFR violation, no TFR violation or TFR zones in the vicinity are provided. If a TFR violation, or possible TFR violation or TFR zone in the vicinity are found, measures are indicated to exit the TFR zone or change the aircraft's current heading to avoid the TFR zone.
    Type: Grant
    Filed: June 13, 2006
    Date of Patent: June 7, 2011
    Assignee: The MITRE Corporation
    Inventors: Todd Michael Stock, James Daniel Nickum, Doyle Travis Peed, Frank J. Ruscil, Jr., Jonathan L. Schwartz
  • Patent number: 7756637
    Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: July 13, 2010
    Assignee: The Boeing Company
    Inventors: Patrick Ralf Wipplinger, Richard William Ellerbrock
  • Patent number: 7724155
    Abstract: An avionics display is disclosed. A synthetic rendering of terrain is created using stored terrain data. A horizon line is overlaid upon the synthetic rendering of terrain. The horizon line represents zero degrees pitch attitude in a direction of travel of an aircraft in which the avionics display is installed. The horizon line is configured to move in response to attitude-changing movement of the aircraft. An attitude cue is overlaid upon the synthetic rendering of terrain and depicted on first and second sides of the horizon line such that the synthetic rendering of terrain remains substantially visible. The attitude cue has a first appearance on the first side of the horizon line and a second appearance on the second side of the horizon line. The first appearance is visually contrasted from the second appearance.
    Type: Grant
    Filed: September 7, 2006
    Date of Patent: May 25, 2010
    Assignee: Rockwell Collins, Inc.
    Inventors: Eric N. Anderson, John C. Frank, Craig D. Pettit, Sarah Barber, Matthew Carrico
  • Publication number: 20100057276
    Abstract: The invention relates to a method and a device for monitoring risky atmospheric areas. The invention relates to an onboard device connected to meteorological measurement systems making it possible to calculate danger detection areas in front of the aircraft in order to detect potential areas of penetration of the aircraft into risky atmospheric areas. The areas of intersection between the detection areas and the risky meteorological areas are calculated according to the trajectory of the aircraft stored in the navigation system. The method makes it possible to generate alerts and force the display of the meteorological situation in front of the aircraft in case of danger.
    Type: Application
    Filed: August 20, 2009
    Publication date: March 4, 2010
    Applicant: Thales
    Inventors: Nicolas Marty, Hugues Meunier, Philippe Salmon
  • Patent number: 7589641
    Abstract: A wind power installation includes a pylon and a machine housing mounted thereon. The pylon accommodates the rotor of the wind power installation and the generator for producing energy. Wind power installations can be provided with signaling devices so that the attention of air traffic is drawn to the existence of the wind power installation as a large structure. The flight lighting arrangement produces a light which is visible over a long distance, preferably a flashing light. A cover arranged with the flight lighting arrangement can substantially prevent the light from the flight lighting arrangement from being visible, from the ground, in a region around the wind power installation.
    Type: Grant
    Filed: June 4, 2003
    Date of Patent: September 15, 2009
    Inventor: Aloys Wobben
  • Patent number: 7525448
    Abstract: An aircraft optical display system for implementing an enhanced vision system based on weather conditions is described. The display system includes a plurality of imaging sensors configured to receive imaging input data and generate image data, where each imaging sensor is associated with one or more weather conditions. The system further includes a weather conditions input device configured to receive current weather condition information and a weather dependent imaging system configured to receive the current weather conditions information and to select one or more of the plurality of imaging sensors to provide imaging input data in accordance with the current weather conditions information.
    Type: Grant
    Filed: September 28, 2006
    Date of Patent: April 28, 2009
    Assignee: Rockwell Collins, Inc.
    Inventors: John G. Wilson, Kenneth A. Zimmerman, Dean A. Schwab, Michael J. Oldham, Robert E. Stockwell
  • Patent number: 7355522
    Abstract: A warning system for a wind power installation of a wind farm. In one embodiment, the warning system comprises a visibility measuring device. In one embodiment, the warning system comprises a controller configured to synchronize flashing lights on the wind power installation with flashing lights on another wind power installation of the wind farm.
    Type: Grant
    Filed: March 14, 2005
    Date of Patent: April 8, 2008
    Inventor: Aloys Wobben
  • Patent number: 7330780
    Abstract: This invention relates to a safety system for aircraft, wherein prohibited airspaces which aircraft may not enter are marked on a digitally stored image of the airspace, wherein the aircraft is provided with an automatic control device that automatically steers the aircraft on to an alternative route, which is situated outside the prohibited airspace, when the probability that the aircraft will enter the prohibited airspace exceeds a predetermined threshold value.
    Type: Grant
    Filed: April 16, 2003
    Date of Patent: February 12, 2008
    Assignee: Diehl Avionik Systeme GmbH
    Inventors: Harro Von Viebahn, Jens Schiefele
  • Patent number: 7295134
    Abstract: An aircraft terrain avoidance method and device may employ a collision warning section that transmits a caution signal when the aircraft risks colliding with the terrain at the end of a first predetermined period of time. A warning signal is transmitted when the aircraft risks colliding with the terrain at the end of a second predetermined period of time, which is shorter than the first predetermined period of time. A piloting system causes the aircraft to automatically climb with a first gradient corresponding to a predetermined value upon the transmission of the caution signal. An automatic pilot is engaged automatically, if currently disengaged, to force the aircraft to climb with a second gradient, corresponding to the maximum gradient possible in the current flight conditions of the aircraft, upon the transmission of the warning signal.
    Type: Grant
    Filed: September 17, 2004
    Date of Patent: November 13, 2007
    Assignee: Airbus France
    Inventors: Christophe Jourdan, Vincent Foucart
  • Patent number: 7132928
    Abstract: A threat detection system interface that provides translates threat diction information into a tactile signal for a user to indicate the direction and distance of an identified threat relative to an object. The threat detection system interface having applications for use with military vehicles, and in particular military aircraft, but also having application in connection with flight training simulators, computer and/or video games.
    Type: Grant
    Filed: November 12, 2003
    Date of Patent: November 7, 2006
    Inventor: Nicholas V. Perricone
  • Patent number: 7088264
    Abstract: A method and system compares combinations of vehicle or aircraft state variables against known combinations of potentially dangerous states. Alarms and error messages are selectively generated based on such comparisons. In one embodiment, pairs of aircraft state variables are selected and compared to known undesirable pairs of state combinations that indicate an error or a condition that a crew should monitor closely. The combinations and error messages are provided by the database. The comparisons are conducted on a periodic basis monitoring real time states of the parameters collected from various sensors and commands. Experts considering a matrix that provides an exhaustive pairwise comparison of potentially important state variables initially identify undesirable state combinations. Error messages and identification of potential alarms are generated based on both knowledge of actual accidents, and on use of expert knowledge to predict potentially dangerous states.
    Type: Grant
    Filed: March 14, 2002
    Date of Patent: August 8, 2006
    Assignee: Honeywell International Inc.
    Inventor: Victor Andrew Riley
  • Patent number: 7009531
    Abstract: A system and a method for providing a continuous, semi-continuous and/or repetitive aural signal to an aircraft pilot indicative of a difference between a set value and an actual value for one or more flight characteristics of the aircraft.
    Type: Grant
    Filed: July 15, 2002
    Date of Patent: March 7, 2006
    Inventor: Ram Pattisapu
  • Patent number: 6980103
    Abstract: An airline distress system is provided for an airplane. The airplane includes a pilot cockpit and a transponder for transmitting signals to an air traffic controller. The airline distress system includes an auxiliary transponder (10) that transmits auxiliary signals to the air traffic controller. The auxiliary transponder is preferably disposed outside of the pilot cockpit and inaccessible to airplane crew and passengers. In one embodiment, a sensor (16) is operatively coupled with the cockpit door, and a switch (20) communicates with the sensor (16) and the auxiliary transponder (10). The auxiliary transponder (10) is configured to be automatically activated by the switch (20) according to a signal from the sensor that the cockpit door has been opened.
    Type: Grant
    Filed: September 20, 2002
    Date of Patent: December 27, 2005
    Inventor: Norman Understein
  • Patent number: 6919808
    Abstract: The device (1) comprises a means (2) comprising at least one means of sensory recognition (3, 4), for pre-flight automatic characterization of the pilot who is located at a control station in the cockpit by establishing a reference profile, a means (5) comprising at least one means of sensory recognition (6, 7), for real-time automatic characterization, throughout the flight, of the person located at the control station, by establishing an actual profile, a means (8) for comparing in real time the actual profile with the reference profile, and for transmitting a dissimilarity signal, when they are different, and a means (9) for sending an alert signal to an air traffic control station (10), when a dissimilarity signal is transmitted.
    Type: Grant
    Filed: March 7, 2003
    Date of Patent: July 19, 2005
    Assignee: Eurocopter
    Inventor: Jean-Yves Longere
  • Patent number: 6917860
    Abstract: A method for transmitting environmental conditions information, which includes receiving at least some environmental conditions information, scaling the received information such that a scaled environmental conditions value is determined for a particular vehicle, receiving an environmental conditions threshold value, comparing the scaled value to the received threshold value, determining whether the scaled value is greater than the received threshold value, and transmitting, if the scaled value is greater than the received threshold value, at least some of the information.
    Type: Grant
    Filed: April 4, 2003
    Date of Patent: July 12, 2005
    Assignee: Aerotech Research (USA), Inc.
    Inventors: Paul Aaron Robinson, Roland L. Bowles
  • Patent number: 6867710
    Abstract: The object of the invention is to improve a flight warning light arrangement of wind power installations and in particular to make the operation thereof as effect as possible. Disclosed is a flight warning light arrangement for a wind power installation, comprising at least one light means which is mounted on the wind power installation, wherein there is provided a device for detecting the brightness value, for example a twilight switch which detects the level of daytime brightness in the area around the wind power installation, and the device for detecting the brightness value is connected to a switching device which evaluates the measured data and switches on the flight warning light arrangement when the brightness value falls below a given value.
    Type: Grant
    Filed: May 8, 2001
    Date of Patent: March 15, 2005
    Inventor: Aloys Wobben
  • Publication number: 20040044445
    Abstract: An airborne computer is linked to a ground-based or satellite-based supplier of weather data that is geographically referenced. The computer retrieves the weather data on a regular cycle but does not display the data. The computer also has access to the aircraft's state, i.e., position, altitude, speed, and intended route. Algorithms within the computer combine the present and estimated future positions of the aircraft with the weather data, and create an alert to the crew if a threat is detected. When a threat is detected, the weather display is activated to draw the attention of the crew to the threat.
    Type: Application
    Filed: August 30, 2002
    Publication date: March 4, 2004
    Inventor: David Burdon
  • Patent number: 6633239
    Abstract: A warning indication system and method of using the same in conjunction with a cargo door of an aircraft. The cargo door is positionable in an opened position; a closed position; a closed and latched position; and a closed, latched, and locked position. The method includes outputting first and second closed signals when the cargo door is in the closed position; outputting first and second latched signals when the cargo door is in the closed and latched position; and outputting first and second locked signals when the cargo door is in the closed, latched, and locked position. All of the signals are then analyzed to positively determine the position of the cargo door, while minimizing the probability of false indications. Various warnings are generated in response to the combination of signals received. The apparatus employs a dual logic system and redundant sensors to provide differing warnings dependent on the phase of flight.
    Type: Grant
    Filed: July 17, 2001
    Date of Patent: October 14, 2003
    Assignee: The Boeing Company
    Inventors: Leo W. Plude, Todd B. Brouwer, Mark E. Brighton, Donald E. Ham
  • Patent number: 6397128
    Abstract: A flight data recording system (50) including a flight data recorder (FDR (12) with an integrated flight data acquisition unit (FDAU) (16). The FDR (12) has first and second interface ports for communicating with one or more external aircraft instrumentation subsystems. The system includes an digital communication bus (52) coupled to one of the interface ports and arranged to provide a communications pathway between the FDR (12) and the external aircraft instrumentation subsystems. A portable maintenance access terminal (70) is coupled to the system via a local area network bus (60).
    Type: Grant
    Filed: December 30, 1998
    Date of Patent: May 28, 2002
    Assignee: Honeywell International Inc.
    Inventor: John C. Todd
  • Publication number: 20010035831
    Abstract: A display system for an airplane or other vehicle is disclosed. A rear projection LCD is used to allow for a maximum amount of screen area to be used in displaying operator pertinent data.
    Type: Application
    Filed: May 22, 2001
    Publication date: November 1, 2001
    Applicant: Sandel Avionics
    Inventor: Gerald J. Block
  • Patent number: 6201482
    Abstract: In a method of detecting a collision risk and preventing air collisions, it is proposed that probabilities should be calculated for the likely presence of one's own aircraft in predetermined sectors at a number of selected times (probabilities of presence) and these probabilities for one's own aircraft and those for other objects should be used to calculate the probabilities of one's own aircraft and at least one of the other objects being present simultaneously in a given sector (probabilities of collision) for the predetermined sectors and selected times.
    Type: Grant
    Filed: January 11, 1999
    Date of Patent: March 13, 2001
    Assignee: VDO Luftfahrtgeraete Werk GmbH
    Inventors: Jens Schiefele, Richard Schulze, Harro von Viebahn
  • Patent number: 6002348
    Abstract: An airborne power line detector and warning system includes a low frequency radio and antenna for detecting an AC signal of about 50 to 60 hertz. The system also includes a subsystem for producing a unique audio signal such as a series of clicks for warning a pilot that he is flying close to one or more power lines. In addition, the system includes a mute feature for muting the audio signal and replacing it with a visual signal. Finally, the system includes a gain sensor for replacing the audio signal at any time that the helicopter reduces its distance to a power line. An airborne power line detection and warning system which includes a second system or back up system is also disclosed. That system includes a GPS receiver and GIS data base to position a helicopter with respect to a power line grid and sound an alarm when the helicopter approaches a power line.
    Type: Grant
    Filed: September 18, 1998
    Date of Patent: December 14, 1999
    Assignee: Safe Flight Instrument Corporation
    Inventors: Leonard M. Greene, Randall A. Greene
  • Patent number: 5986582
    Abstract: A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.
    Type: Grant
    Filed: June 24, 1998
    Date of Patent: November 16, 1999
    Assignee: Safe Flight Instrument Corporation
    Inventors: Leonard M. Greene, Randall A. Greene
  • Patent number: 5864307
    Abstract: A terrain advisory system for an aircraft (A) comprises a processor (11) which compares terrain information, accessed from a memory (13) according to data from a navigation system (12), with dynamic flight parameters from a monitor (14) for the aircraft. The processor (11) also generates a trajectory signal and a pull-up signal to indicate, on a display (15), current aircraft trajectory relative to a line constructed from notional pull-up trajectories for the aircraft which avoid a predetermined clearance height without exceeding a predetermined acceleration acting on the aircraft during a pull-up maneuver.
    Type: Grant
    Filed: January 19, 1997
    Date of Patent: January 26, 1999
    Assignee: GEC Marconi Limited
    Inventor: Anthony John M. Henley