Altitude Patents (Class 340/970)
  • Publication number: 20040239529
    Abstract: A free flight obstacle avoidance system (OAS) is a commanded obstacle resolution feedback system. The system employs insertion of hybridized elements to the existing designs of Adaptive Ground Collision Avoidance Systems and Midair Collision Avoidance Systems along with a newly design module, the obstacle avoidance dispatcher and resolver, to provide a coherent obstacle resolution. The system is capable of filtering data produced by the hybrid ground collision avoidance module and the hybrid air collision avoidance module, inserting evaluating solution status and command directives before routing avoidance data to hybrid modules for validation. The dispatcher and resolver module determines the final obstacle resolution to generate avoidance control guidance and appropriate warnings clearly indicated obstacle situation and obstacle avoidance maneuvers to the flight crew.
    Type: Application
    Filed: May 27, 2003
    Publication date: December 2, 2004
    Inventor: My Tran
  • Patent number: 6819266
    Abstract: An aircraft system for reducing the airspeed of an aircraft as it passes through a preselected altitude includes an automatic throttle system including a computer, a device for inputting a preselected altitude and a preselected airspeed into the computer. An altimeter provides the current altitude of the aircraft and an aircraft instrument provides the current air speed and the vertical speed of the aircraft. The computer in response to the current altitude and vertical speed of the aircraft generates a signal to retard the throttles when the current altitude, the current air speed of the aircraft is equal to 2 times the vertical speed plus a preselected altitude.
    Type: Grant
    Filed: October 7, 2002
    Date of Patent: November 16, 2004
    Assignee: Safe Flight Instrument Corporation
    Inventor: Randall A. Greene
  • Patent number: 6810322
    Abstract: An improved method for correlating between targets in an air traffic control system. A methods or systems according to the invention compare selected components of a first target report to the components of a second target report, produce a confidence level on each component comparison, and determine whether to declare the targets similar based on the confidence level on each component compared. The first and second target reports may include ADS-B target reports and TIS target reports. The individual components of the reports may be range, bearing, track angle, and relative altitude. The methods or systems may use a fuzzy logic probability model to produce a continuous confidence level on each component comparison.
    Type: Grant
    Filed: February 10, 2003
    Date of Patent: October 26, 2004
    Assignee: Garmin AT, Inc.
    Inventor: Chih Lai
  • Publication number: 20040186635
    Abstract: A method for detecting an inaccurate barometric pressure adjustment setting on a barometric altimeter is described. The method includes receiving a barometric corrected altitude from the altimeter, receiving an altitude from a global positioning satellite (GPS) system, comparing the barometric corrected altitude with the altitude received from the GPS system, actuating an alarm if the altitudes differ by an amount larger than a threshold value, the threshold value being dependent upon one or more of the received altitudes.
    Type: Application
    Filed: March 21, 2003
    Publication date: September 23, 2004
    Inventor: Mark T. Manfred
  • Patent number: 6785594
    Abstract: The ground proximity warning system and method provide a number of alerts based upon a substantially reduced list of input parameters relative to a conventional ground proximity warning system and method. The ground proximity warning system and method generally constructs alert envelopes and generates alerts if the upcoming terrain or other obstacles pierce the alert envelopes. The ground proximity warning system and method can also generate alerts if the aircraft has an excessive descent rate at a relatively low altitude and if the aircraft descends immediately following takeoff in a similar fashion to Mode 1 and Mode 3 alerts. Further, the ground proximity warning system and method can provide altitude call outs at predefined altitudes above a target runway and can provide alerts if the aircraft appears to be landing short of a runway.
    Type: Grant
    Filed: March 24, 2000
    Date of Patent: August 31, 2004
    Assignee: Honeywell International Inc.
    Inventors: C. Don Bateman, Steven C. Johnson
  • Publication number: 20040160341
    Abstract: A display control device, having a processor structured for receiving terrain elevation information and samples of current position and altitude above ground data; and one or more algorithms resident on the processor for generating, as a function of the current position and altitude above ground data, one or more display control signals for causing a display device to display, in a monochromatic scale graduated as a function of terrain elevation relative to mean sea level, a strategic portion of the terrain elevation information extending between a minimum elevation of the strategic portion of the terrain elevation information and a pre-selected strategic altitude threshold less than the altitude above ground data.
    Type: Application
    Filed: February 18, 2003
    Publication date: August 19, 2004
    Applicant: Honeywell International, Inc.
    Inventors: Thea L. Feyereisen, Christopher J. Misiak
  • Patent number: 6744373
    Abstract: Disclosed is a portable gas alarm device easy to be fabricated as a small-sized one handy to carry and high in convenience for use. The portable gas alarm device comprises a gas alarm device body having a casing flat in whole and a fitting member provided on the casing to fit it to the human body. The gas alarm device body has a control circuit board extending to the direction of the flat plane of the casing, a display mechanism is arranged in a central area on the front surface side of the control circuit board, a gas sensor and an alarm buzzer are arranged on the right and left sides of the display mechanism, and a battery fitting chamber is provided on the back surface side of the circuit board. A vibration generator for alarm may be provided in the gas alarm device body. The fitting member may be one suitable for use in fitting the gas alarm device body to a person's wrist or a person's wear.
    Type: Grant
    Filed: March 25, 2002
    Date of Patent: June 1, 2004
    Assignee: Riken Keiki Co., Ltd.
    Inventors: Junichi Koyano, Shuji Tajima, Yoshiharu Ao, Masahide Kitamura
  • Patent number: 6737988
    Abstract: An integrated cabin pressure control system valve that uses a dual, redundant channel electronic control unit for both control of the valve and to supply alarm, indication, and control signals to the aircraft's avionics system. Each channel in the electronic control unit includes an instrumentation and control circuit that uses multiple, dissimilar sensors and signals for warnings, indications, and controls. This configuration reduces the likelihood for a common mode failure that could result in a postulated gradual decompression without indication event.
    Type: Grant
    Filed: February 21, 2002
    Date of Patent: May 18, 2004
    Assignee: Honeywell International, Inc.
    Inventors: Darrell W. Horner, Joaquin P. Rabon, Andrew D. Bunn
  • Patent number: 6710723
    Abstract: A terrain-awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.
    Type: Grant
    Filed: September 17, 2001
    Date of Patent: March 23, 2004
    Assignee: Honeywell International Inc.
    Inventors: Hans R. Muller, Kevin J. Conner, Steven C. Johnson
  • Patent number: 6711478
    Abstract: A system and method for determining the vertical integrity of an altitude component of an aircraft navigational signal through the use of a receiver-autonomous vertical integrity monitoring (RAVIM) algorithm. The system and methods also provide timely warning to vehicle operators if the integrity of the signal is unacceptable or unknown. The system and methods are capable of determining the vertical integrity of an incoming signal without relying upon data embedded within the incoming signal itself. In addition, the system and methods of the present invention provide vertical integrity to vehicle operators in instances, such as when the specific aircraft navigational signal is not operating, when the specific aircraft navigational signal is not available in a particular region, or when an aircraft is operating outside the geographic area covered by the specific aircraft navigational signal system.
    Type: Grant
    Filed: December 10, 2001
    Date of Patent: March 23, 2004
    Assignee: Garmin AT, Inc.
    Inventor: Robert C. Hilb
  • Patent number: 6707394
    Abstract: The present invention provides several apparatus, methods, and computer program products for generating a terrain clearance floor envelope for use in a ground proximity warning system. In one embodiment, the present invention includes a processor that defines a terrain clearance floor envelope having at least two boundaries. In this embodiment, the processor defines at least one of the boundaries based on a runway position quality factor, an altitude data quality factor, and an aircraft position quality factor. Using these factors, the processor of the present invention can more precisely define the boundaries of the envelope about the selected runway. Further, the processor of the present invention does not unnecessarily increase the region between the envelope and runway where no ground proximity alarms are generated.
    Type: Grant
    Filed: February 1, 2000
    Date of Patent: March 16, 2004
    Assignee: Honeywell, Inc.
    Inventors: Yasuo Ishihara, Scott Gremmert, Steven C. Johnson
  • Patent number: 6704634
    Abstract: A method and system for braking aircraft landing gear wheels after initialization of landing gear retraction. The system includes monitors, controlling components, measurement components, a fault recording memory, fault annunciation components, wheel braking system and brakes. The monitors monitor speed of the landing gear wheels and landing gear position. The control component generates braking instructions based on the monitored speed of the wheels and position of the landing gear.
    Type: Grant
    Filed: November 6, 2002
    Date of Patent: March 9, 2004
    Assignee: The Boeing Company
    Inventors: John J. Gowan, Scott D. Maxwell, Tu-Luc H. Nguyen, Beth L. Sundquist
  • Patent number: 6686851
    Abstract: A device for enhancing altitude awareness in an avionics display is disclosed. The device includes an altitude indicator that displays a current altitude on the avionics display. A scrolling display of altitude levels is displayed with the altitude indicator on the avionics display. The scrolling display includes a plurality of scaled numbers that represent predetermined intervals of altitude levels surrounding the current altitude. The scrolling display also includes a non-numeric graphic construct that is displayed adjacent the plurality of scaled numbers. The graphic construct has first and second substantially mirror-image portions that are positioned on first and second opposing sides of the plurality of scaled numbers. A controller causes the altitude indicator to display the current altitude on the avionics display.
    Type: Grant
    Filed: August 25, 2000
    Date of Patent: February 3, 2004
    Assignee: Rockwell Collins
    Inventors: Thomas M. Gordon, Timothy J. Etherington
  • Patent number: 6653947
    Abstract: A display system having a display screen for graphical display of data, a graphics processor for receiving data from at least a terrain data base and data from a weather radar and for converting the received data into a single data stream to provide an input data stream to the display screen. The single display displays the weather data on one portion of the display screen and displays the terrain data on a second portion of the display screen. The weather data is displayed as a two-dimensional graphic and the terrain data is displayed as a three-dimensional graphic, thus providing a user with the necessary flight information while keeping processing resources to a reasonable level. The terrain data is displayed as an out the window display graphic, and the weather data and the terrain data displays are scaled such that the displays are dimensionally juxtaposed to allow rapid recognition of the data by a user of the display system.
    Type: Grant
    Filed: February 20, 2002
    Date of Patent: November 25, 2003
    Assignee: Honeywell International Inc.
    Inventors: David B. Dwyer, Gang He
  • Publication number: 20030206120
    Abstract: The present invention provides several apparatus, methods, and computer program products for generating a terrain clearance floor envelope for use in a ground proximity warning system. In one embodiment, the present invention includes a processor that defines a terrain clearance floor envelope having at least two boundaries. In this embodiment, the processor defines at least one of the boundaries based on a runway position quality factor, an altitude data quality factor, and an aircraft position quality factor. Using these factors, the processor of the present invention can more precisely define the boundaries of the envelope about the selected runway. Further, the processor of the present invention does not unnecessarily increase the region between the envelope and runway where no ground proximity alarms are generated.
    Type: Application
    Filed: February 1, 2000
    Publication date: November 6, 2003
    Inventors: Yasuo Ishihara, Scott Gremmert, Steven C Johnson
  • Patent number: 6640165
    Abstract: A method of determining an altitude of a flying object. A Blanchard altitude of a flying object is computed. A non-Blanchard reference altitude and a trajectory of the flying object are measured and input to a Kalman filter. In the Kalman filter, the non-Blanchard reference altitude and the trajectory are processed to derive a radius of jet stream curvature. A gradient wind correction factor is then computed as a function of the radius of jet stream curvature. The Blanchard altitude is then corrected in response to the gradient wind correction factor.
    Type: Grant
    Filed: November 26, 2002
    Date of Patent: October 28, 2003
    Assignee: Northrop Grumman Corporation
    Inventors: Kirk W. Hayward, Larry G. Stephenson
  • Publication number: 20030193409
    Abstract: A system for monitoring an aircraft receives navigation signals and deriving a position vector therefrom and also receives an input representative of altitude of the aircraft above ground level. The system samples the position vector at a selected sample rate and outputs a succession of samples of the position vector, the sample rate depending on whether the altitude of the aircraft above ground level is less than a predetermined value. Data packets that contain respective samples of the position vector are transmitted to a ground-based receiving station. The ground-based receiving station may calculate secondary data.
    Type: Application
    Filed: May 8, 2003
    Publication date: October 16, 2003
    Inventor: Kelly C. Crank
  • Publication number: 20030184450
    Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.
    Type: Application
    Filed: March 28, 2003
    Publication date: October 2, 2003
    Inventors: Hans R. Muller, Kevin J. Conner, Steven C. Johnson
  • Patent number: 6622066
    Abstract: An apparatus, method and computer program product for suppressing an alert generated by a terrain awareness system rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft.
    Type: Grant
    Filed: January 23, 2002
    Date of Patent: September 16, 2003
    Inventors: Yasuo Ishihara, Steven C. Johnson, Kevin J Conner
  • Publication number: 20030156046
    Abstract: A display system having a display screen for graphical display of data, a graphics processor for receiving data from at least a terrain data base and data from a weather radar and for converting the received data into a single data stream to provide an input data stream to the display screen. The single display displays the weather data on one portion of the display screen and displays the terrain data on a second portion of the display screen. The weather data is displayed as a two-dimensional graphic and the terrain data is displayed as a three-dimensional graphic, thus providing a user with the necessary flight information while keeping processing resources to a reasonable level. The terrain data is displayed as an out the window display graphic, and the weather data and the terrain data displays are scaled such that the displays are dimensionally juxtaposed to allow rapid recognition of the data by a user of the display system.
    Type: Application
    Filed: February 20, 2002
    Publication date: August 21, 2003
    Inventors: David B. Dwyer, Gang He
  • Patent number: 6606034
    Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.
    Type: Grant
    Filed: July 31, 1995
    Date of Patent: August 12, 2003
    Assignee: Honeywell International Inc.
    Inventors: Hans R. Muller, Kevin J. Conner, Steven C. Johnson
  • Patent number: 6593858
    Abstract: Methods and apparatus are provided for generating a vertical situational image of a vehicle. The apparatus for generating a vertical situational image of the vehicle is comprised of an input device configured to receive flight plan data of the vehicle and a situational display configured to produce the vertical situational image from the flight plan data. The apparatus for generating a vertical situational image of the vehicle is further comprised of a processing device that is configured to receive the flight plan data from the input device, generate a first segment having a first slope in a first viewable range of the vertical situational image from the flight plan data and determine the first segment in a second viewable range of the vertical situational image.
    Type: Grant
    Filed: September 12, 2001
    Date of Patent: July 15, 2003
    Assignee: Honeywell International Inc.
    Inventor: Hisham M. Qureshi
  • Patent number: 6583733
    Abstract: An apparatus, method and computer program product has a first terrain awareness mode and a second terrain awareness mode selectable by the pilot.
    Type: Grant
    Filed: May 25, 2001
    Date of Patent: June 24, 2003
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Kevin Conner
  • Patent number: 6577931
    Abstract: A terrain avoidance system, method and computer program product for reducing nuisance alarms. The system includes a geometric altitude component, first and second vertical safety margin generators, and an alert component.
    Type: Grant
    Filed: July 27, 2001
    Date of Patent: June 10, 2003
    Assignee: Honeywell International Inc.
    Inventors: Kevin J Conner, Yasuo Ishihara, Steve C. Johnson
  • Patent number: 6567756
    Abstract: A portable pressure measuring apparatus detects a designated altitude by sensing an outside atmospheric pressure. An A/D converter generates pressure data corresponding to the outside pressure. Pressure data corresponding to a designated altitude is stored in a memory, and the pressure data generated by the A/D converter is compared with the stored pressure data. The designated altitude may be set to any value through a manually-operated input switch and converted into pressure data. Alternatively, the designated altitude may be set as the altitude at which the apparatus is positioned by converting pressure data generated by the A/D converter at that altitude into a corresponding altitude.
    Type: Grant
    Filed: June 15, 2000
    Date of Patent: May 20, 2003
    Assignee: Seiko Instruments Inc.
    Inventor: Tomoharu Tsuji
  • Patent number: 6552669
    Abstract: A method and apparatus for automatically providing advisories to pilots in a monitored airspace comprises monitoring weather conditions and air traffic in an airspace and then generating and broadcasting advisories over a radio channel in response to relevant air traffic conditions. Advisory lengths are sized based on the volume of communications on the common traffic advisory frequency. An airspace model, made up of a multitude of constantly updated records, is used to keep track of important flight information and weather conditions. A monitoring CPU, accessing the airspace model, creates the advisory messages based upon hazard criteria, guidelines, airport procedures and other relevant air traffic data.
    Type: Grant
    Filed: January 15, 2002
    Date of Patent: April 22, 2003
    Assignee: Potomac Aviation Technology Corporation
    Inventors: Gary B. Simon, David J. Wartofsky
  • Patent number: 6542810
    Abstract: An improved method for correlating between targets in an air traffic control system. A methods or systems according to the invention compare selected components of a first target report to the components of a second target report, produce a confidence level on each component comparison, and determine whether to declare the targets similar based on the confidence level on each component compared. The first and second target reports may include ADS-B target reports and TIS target reports. The individual components of the reports may be range, bearing, track angle, and relative altitude. The methods or systems may use a fuzzy logic probability model to produce a continuous confidence level on each component comparison.
    Type: Grant
    Filed: June 4, 2001
    Date of Patent: April 1, 2003
    Assignee: United Parcel Service of America, Inc.
    Inventor: Chih Lai
  • Patent number: 6538581
    Abstract: Includes means for monitoring the position and behavior of air traffic in the vicinity of the aircraft and generating a warning or avoidance signal for air traffic predicted to be on a collision course. The apparatus also includes means for monitoring the position and behavior of the aircraft relative to terrain in the vicinity of the aircraft flight path to generate a warning or avoidance signal for terrain features predicted to provide a collision threat. Means are provided for receiving the traffic warning signals and terrain warning signals comparing the signals and generating a combined warning or advisory signal which indicates an action for the aircraft which avoids both air traffic and terrain collisions.
    Type: Grant
    Filed: August 26, 1999
    Date of Patent: March 25, 2003
    Assignee: BAE Systems PLC
    Inventor: Mark Cowie
  • Patent number: 6525674
    Abstract: A conditional TAWS algorithm, system and method for providing advanced warnings of potential hazard situations which could result from changes in heading and vertical speed.
    Type: Grant
    Filed: August 8, 2001
    Date of Patent: February 25, 2003
    Assignee: Rockwell Collins, Inc.
    Inventors: Wallace E. Kelly, Serdar Uckun
  • Patent number: 6507289
    Abstract: In a ground proximity warning system for an aircraft, a signal representing clearance of the aircraft from the underlying terrain is produced from a sea level related altitude signal and a terrain database in addition to the radio altitude signal of the aircraft's radio altimeter. An indication of reasonableness of the aircraft radio altitude signal is formed jointly responsive to the aircraft radio altitude signal and the terrain clearance signal.
    Type: Grant
    Filed: October 5, 2000
    Date of Patent: January 14, 2003
    Assignee: Honeywell International Inc.
    Inventors: Steven C. Johnson, Glen A. Burlingame
  • Patent number: 6502015
    Abstract: A Terrain Following Apparatus for a vehicle such as an aircraft includes means (1) for effecting autonomous following of terrain by the vehicle, a control device (2), operable by a person operating the vehicle, to engage and disengage the means (1), a Terrain Referenced Navigation system (3) operable to provide navigation data for the vehicle, and validation means (4) for validating the integrity of the navigation data to provide when the integrity of the navigation data is validated for engagement of the autonomous Terrain Following means (1) by the device (2) and when the integrity of the navigation data is invalidated, for preventing operation of the means (1) when the control device (2) is operated.
    Type: Grant
    Filed: December 14, 2000
    Date of Patent: December 31, 2002
    Assignee: BAE Systems plc
    Inventors: Tom M Brookes, Laurence Day
  • Patent number: 6502020
    Abstract: An ongoing driving habit monitoring system used by insurance companies to more accurately determine the driving habits of their policyholders or authorized drivers to more accurately determine their risk of loss. The system uses a monitoring device located in the insured party's motor vehicle. Each monitoring device is coupled to a GPS receiver, that provides physical location information, and to a wireless modem capable of connecting to a wireless communication network. The system also includes a central computer connected to a wide area network that is able to continuously or intermittently receive movement information from the monitoring device as it travels in a specific region covered by the wireless communication network. The central computer uses a driving monitoring software program and several ancillary databases containing roadway information for a region, route information, and traffic pattern information.
    Type: Grant
    Filed: January 17, 2002
    Date of Patent: December 31, 2002
    Inventor: Brook W. Lang
  • Patent number: 6484071
    Abstract: A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.
    Type: Grant
    Filed: February 1, 2000
    Date of Patent: November 19, 2002
    Assignee: Honeywell International, Inc.
    Inventors: Kevin J Conner, Steven C. Johnson
  • Patent number: 6480120
    Abstract: A working memory contains a local altimetric map defining an altitude envelope of the terrain in the vicinity of the aircraft. A vertical limit path of the aircraft is established, on the basis of status indications and selected flight parameters, in the vertical surface containing the axis of its path. A first comparison is undertaken between this vertical limit path and the corresponding part of the altitude envelope, so as to determine a hazard of a vertical collision with the ground, and an alarm can be established according to the result of this first comparison. A lateral limit path of the aircraft on one side of the vertical of the flight path is also established on the basis of the status indications and selected parameters. A second comparison is made between this lateral limit path and the corresponding part of the altitude envelope.
    Type: Grant
    Filed: April 14, 1997
    Date of Patent: November 12, 2002
    Assignee: Dassault Electronique
    Inventor: Hugues Meunier
  • Patent number: 6462480
    Abstract: A process for diagnosing the proper operation of direction indicator lights of a motor vehicle includes the steps of temporally and alternately shifting the end of illumination of the right and left change of direction indicator lamps of the vehicle, measuring the current passing through a power circuit of the direction indicator lamps during the temporal shift, comparing the measured value with a reference value, and deducing therefrom whether at least one of the lamps is inoperative and in this case informing the driver thereof. A device for diagnosing the proper operation of the direction indicator lights of a motor vehicle is also provided.
    Type: Grant
    Filed: March 28, 2001
    Date of Patent: October 8, 2002
    Assignee: Siemens VDO Automotive S.A.S
    Inventor: Jean-Marc Tornare
  • Patent number: 6452510
    Abstract: A cabin pressure altitude monitor and warning system provides a warning when a detected cabin pressure altitude has reached a predetermined level. The system is preferably embodied in a portable, pager-sized device that can be carried or worn by an individual. A microprocessor calculates the pressure altitude from signals generated by a calibrated pressure transducer and a temperature sensor that compensates for temperature variations in the signals generated by the pressure transducer. The microprocessor is programmed to generate a warning or alarm if a cabin pressure altitude exceeding a predetermined threshold is detected. Preferably, the microprocessor generates two different types of warning or alarm outputs, a first early warning or alert when a first pressure altitude is exceeded, and a second more serious alarm condition when either a second, higher pressure altitude is exceeded, or when the first pressure altitude has been exceeded for a predetermined period of time.
    Type: Grant
    Filed: March 8, 2001
    Date of Patent: September 17, 2002
    Assignee: National Aeronautics & Space Administration
    Inventor: Jan A. Zysko
  • Patent number: 6452511
    Abstract: A conditional TAWS algorithm system and method for providing advanced warnings of potential CFIT situation which could result from predictable errant course changes.
    Type: Grant
    Filed: August 8, 2001
    Date of Patent: September 17, 2002
    Assignee: Rockwell Collins, Inc.
    Inventors: Wallace E. Kelly, Serdar Uckun
  • Patent number: 6445310
    Abstract: The present invention provides apparatus, methods, and computer program products that monitor the altitude of an aircraft with respect to a selected runway. If the attitude of the aircraft is below a minimum glideslope with respect to the selected runway, the apparatus, methods, and computer program products of the present invention alert the flight crew, such that the altitude of the aircraft can be increased. This, in turn, increases time for reaction to abrupt changes in elevation near the selected runway. Specifically, the apparatus, methods, and computer program products of the present invention define a runway field clearance floor envelope about the selected runway that represents different preselected altitudes above the selected runway at respective distances from the selected runway. The apparatus, method, and computer program products of the present invention compare the altitude of the aircraft with respect to the selected runway to the runway field clearance floor envelope.
    Type: Grant
    Filed: February 1, 2000
    Date of Patent: September 3, 2002
    Assignee: Honeywell International, Inc.
    Inventors: C. Don Bateman, Steven C. Johnson, Scott Gremmert, Yasuo Ishihara
  • Patent number: 6437707
    Abstract: The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second component that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach).
    Type: Grant
    Filed: July 23, 2001
    Date of Patent: August 20, 2002
    Assignee: Honeywell International, Inc.
    Inventor: Steven C. Johnson
  • Publication number: 20020097169
    Abstract: The present invention includes a system, method and computer program product for reducing nuisance warnings during low altitude flight conditions and in the presence of low position uncertainty. The system includes a first component that determines whether the aircraft is in a low altitude flight condition and a second component that determines the position, positional uncertainty, and the heading. The system also includes a third component that attenuates and refines the look-ahead envelope in accord with the determined condition of flight and positional uncertainty.
    Type: Application
    Filed: July 27, 2001
    Publication date: July 25, 2002
    Inventors: Steve C. Johnson, Yasuo Ishihara, Kevin J. Conner
  • Publication number: 20020089433
    Abstract: The present invention provides apparatus, methods, and computer program products that monitor the altitude of an aircraft with respect to a selected runway. If the altitude of the aircraft is below a minimum glideslope with respect to the selected runway, the apparatus, methods, and computer program products of the present invention alert the flight crew, such that the altitude of the aircraft can be increased. This, in turn, increases time for reaction to abrupt changes in elevation near the selected runway. Specifically, the apparatus, methods, and computer program products of the present invention define a runway field clearance floor envelope about the selected runway that represents different preselected altitudes above the selected runway at respective distances from the selected runway. The apparatus, method, and computer program products of the present invention compare the altitude of the aircraft with respect to the selected runway to the runway field clearance floor envelope.
    Type: Application
    Filed: February 1, 2000
    Publication date: July 11, 2002
    Inventors: C. Don Bateman, Steven C. Johnson, Scott Gremmert, Yasuo Ishihara
  • Publication number: 20020077731
    Abstract: A system and method for determining the vertical integrity of an altitude component of an aircraft navigational signal through the use of a receiver-autonomous vertical integrity monitoring (RAVIM) algorithm. The system and methods also provide timely warning to vehicle operators if the integrity of the signal is unacceptable or unknown. The system and methods are capable of determining the vertical integrity of an incoming signal without relying upon data embedded within the incoming signal itself. In addition, the system and methods of the present invention provide vertical integrity to vehicle operators in instances, such as when the specific aircraft navigational signal is not operating, when the specific aircraft navigational signal is not available in a particular region, or when an aircraft is operating outside the geographic area covered by the specific aircraft navigational signal system.
    Type: Application
    Filed: December 10, 2001
    Publication date: June 20, 2002
    Applicant: United Parcel Service of America, Inc.
    Inventor: Robert C. Hilb
  • Patent number: 6397142
    Abstract: A method and system for conducting local neighborhood searches among three or more aircraft routes to cure any irregularity in one of the aircraft routes, in which states of Binary Operations are stored, time and space feasibility tables are created from the stored states, and Tertiary Operations responsive to data stored in the feasibility tables are performed on the three or more entities to effect a repair.
    Type: Grant
    Filed: April 11, 2001
    Date of Patent: May 28, 2002
    Assignee: CALEB Technologies Corp.
    Inventor: Ira Louis Greenstein
  • Patent number: 6389354
    Abstract: Terrain navigation apparatus (1) for a stationary or moving vehicle (2) when the apparatus (1) is mounted thereon, including a system (3) for determining position, velocity, altitude and attitude incorporating at least six sensing means operable to provide signals indicative of a first measured height (5), a first velocity (7) and a first position (9) of the vehicle (2), scanning means (11) operable to scan terrain (13) around the vehicle (2) and measure a range (15) from the vehicle (2) thereto, first combining means (17) for combining signals indicative of the first measured height, the range and the first position (5, 15, 9) of the vehicle (2), together with error estimates (19) associated therewith, and for outputting results of said combining process, error-estimating means (21) for receiving as input signals results of said combining process and for providing said error estimates(19), such that the error-estimating means (21) and first combining means (17) operatively interact to effect terrain navigati
    Type: Grant
    Filed: August 1, 2000
    Date of Patent: May 14, 2002
    Assignee: BAE Systems plc
    Inventors: Andrew C Hicks, Ian W Scaysbrook, John R Fountain
  • Patent number: 6380870
    Abstract: The present invention provides several apparatus, methods, and computer program products for determining a look ahead distance value for use in a ground proximity warning system. Specifically, the present invention provides apparatus, methods, and computer program products that generate a candidate look ahead distance value that provides a constant reaction time for varying aircraft speeds. The apparatus of the present invention includes a processor that generates the constant reaction time look ahead distance by multiplying a desired reaction time by the speed of the aircraft. This constant reaction time look ahead distance value is compared by the processor to other candidate look ahead distance values that have variable reaction times for varying aircraft speeds. If the aircraft is traveling at a relatively high speed, the processor of the present invention selects the constant reaction time look ahead distance value for use in the ground proximity warning system.
    Type: Grant
    Filed: February 1, 2000
    Date of Patent: April 30, 2002
    Assignee: Honeywell International, Inc.
    Inventors: Kevin J Conner, Steven C. Johnson
  • Patent number: 6380869
    Abstract: A method and apparatus for automatically providing advisories to pilots in a monitored airspace comprises monitoring weather conditions and air traffic in an airspace and then generating and broadcasting advisories over a radio channel in response to relevant air traffic conditions. Advisory lengths are sized based on the volume of communications on the common traffic advisory frequency. An airspace model, made up of a multitude of constantly updated records, is used to keep track of important flight information and weather conditions. A monitoring CPU, accessing the airspace model, creates the advisory messages based upon hazard criteria, guidelines, airport procedures and other relevant air traffic data.
    Type: Grant
    Filed: May 19, 1999
    Date of Patent: April 30, 2002
    Assignee: Potomac Aviation Technology Corporation
    Inventors: Gary B. Simon, David Wartofsky
  • Publication number: 20020030610
    Abstract: An apparatus, method and computer program product has a first terrain awareness mode and a second terrain awareness mode selectable by the pilot.
    Type: Application
    Filed: May 25, 2001
    Publication date: March 14, 2002
    Inventors: Yasuo Ishihara, Kevin Conner
  • Publication number: 20020021230
    Abstract: The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second component that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach).
    Type: Application
    Filed: July 23, 2001
    Publication date: February 21, 2002
    Inventor: Steven C. Johnson
  • Patent number: 6347263
    Abstract: An aircraft terrain warning generator is provided having a terrain and obstacle warning envelope having a lower boundary formed according to the lesser of the current aircraft flight path angle and the obtainable climb gradient.
    Type: Grant
    Filed: October 15, 1999
    Date of Patent: February 12, 2002
    Assignee: AlliedSignal Inc.
    Inventors: Steven C. Johnson, Howard Glover
  • Publication number: 20010047230
    Abstract: An apparatus, system, method and computer program product to verify proper operation of an aircraft altimetry system. Aural and visual alerts may optionally be provided when a fault in the altimetry is detected.
    Type: Application
    Filed: February 2, 2001
    Publication date: November 29, 2001
    Inventors: Scott Gremmert, Steven C. Johnson, Glen Burlingame