Abstract: A method of increasing positional awareness of a pilot of an aircraft during a landing approach of the aircraft. First data from a navigational aid is received. The first data is analyzed to determine a first position of the aircraft at a predetermined time. Second data is received. The second data is independent of the first data. The second data is analyzed to determine a second position of the aircraft at the predetermined time. The first position of the aircraft and the second position of the aircraft are compared, and the pilot is alerted to a difference between the first position of the aircraft and the second position of the aircraft. The second data may be displayed in a form that is convenient for the pilot to view during landing.

Abstract: A critical point on a runway indicates a point at which an aircraft may experience a runway overrun if landing beyond the critical point. A path projection is extended from the aircraft at a descent slope angle to determine whether the aircraft will land beyond the critical point at the current descent slope. Timely alerts may be provided by accounting for the time required to announce a distance value, and the distance traveled during the announcement.

Abstract: The method provides for determining an approach mode which has been selected by the pilot of the aircraft from among a plurality of predetermined approach modes, for selecting a characteristic segment (6) of an arrival path which relates to the selected approach mode thus determined, for determining the orientation of the projection on the ground of the said characteristic segment (6) with respect to the center line of the said runway (5) and, depending on this orientation, for determining an anchoring point of the said final approach path, the orientation (?) in a horizontal plane of the said final approach path and the slope (?) of the said final approach path.

Abstract: A method and system for locating aircraft with respect to airport runways selecting as a function of aircraft state parameters one of a plurality of candidate runways that the aircraft on which it is installed is most likely to encounter, whether taxiing, preparing for take-off, or approaching to land.

Abstract: An avionics system and method is employed for alerting pilots of low premature descent during final landing approach. The method involves determining Final Approach Flight Safety Altitudes for a plurality of runways, identifying which runway an aircraft is likely to land on, and alerting the pilot if the aircraft altitude is lower than the final approach flight safety altitude. The method takes into account terrain information, airport and runway information, and aircraft reference data to make its determination. Particular embodiments reference the Final Approach Fix, one or more step down fix values, the Minimum Descent Altitude and the Missed Approach Point in calculating the Final Approach Flight Safety Altitudes. The system and method have particular utility with a Terrain Awareness and Warning System (“TAWS”) and display in an aircraft.

Abstract: A thin flat panel display for aircraft cockpits. These displays use a dual CPU/graphics generator system to produce simulated aircraft instrumentation displays which are color coded to indicate when one of the graphic generators has not correctly received data from the aircraft system bus. The displays use standard graphic generators and CPUs, and do not require additional software. The displays also allow the aircraft systems to be continuously tested while the aircraft is on the ground. Moreover, the inventive systems include input touch devices which access external memories to display necessary flight and landing information which allow the cockpit crew to expand in detail the external information for display on the flat panels.

Abstract: This invention, a Protected Primary Focal Node PFN is a Trusted Remote Activity Controller TRAC and mobile communication router platform that provides accountable remote and robotics control to transportation vehicles by interfacing with the vehicles E/E systems. It connects each vehicle either on the earth's surface or near the earth's surface with application specific intranets for air, sea and land travel, via either host commercial servers or agency providers through wireless communication gateways and then further interfaces these vehicles in a larger machine messaging matrix via wireless and IP protocols to further coordinate movement assess and manage equipment use and impact on the world resources, societies infrastructure and the environment. This filing focuses directly on PFN/TRAC System use to augment and upgrade public safety and security in the Airline Industry and restrict any unauthorized use of an aircraft.

Abstract: A method of guiding an aircraft in the final approach phase including imaging the ground using an imaging system onboard the aircraft to obtain an image, analyzing the image to detect an airport area, detecting an airport area and selecting a runway for landing, tracking the selected runway during the approach of the aircraft by visually tracking the selected runway in the image supplied by the imaging system, and tracking the runway when the aircraft is very close to the ground by analyzing the image supplied by the imaging system to determine the position of the aircraft relative to the runway.

Abstract: A mechanical computer used in tandem with a GPS to approach, enter and fly the traffic pattern of any uncontrolled airport. Pilots must navigate to a relatively small area or approach point before entering the traffic pattern of an uncontrolled airport. While airports are programmed into GPS units, the approach points are not. The computer works in tandem with an onboard GPS unit programmed for navigation direct to the airport of intended landing and employs triangulation to navigate to an approach point from which a proper traffic pattern entry can be made.

Abstract: A method is disclosed for assuming and maintaining secure remote control of and aircraft in the event of an attack upon, or incapacity of the pilot of the aircraft.

Abstract: A flight guidance system providing perspective flight guidance symbology using positioning and terrain information provides increased pilot situational awareness of an aircraft. The guidance system uses a positioning system and a detailed mapping system to provide a perspective display for use in an aircraft. A Perspective Flight Guidance (PFG) symbology set is thereby displayed on a pilot display. The PFG symbology set includes broken line symbols representing an open tunnel and providing flow field data, a half-bracket symbol to indicate that the aircraft is no longer in the open tunnel represented by the broken line symbols and a quickened flight path vector (QFPV) symbol to provide the pilot with predictive flight path information.

Abstract: An aircraft FMS/guidance system which provides for automated and immediate calculation of a preferred flight path and full heading, pitch-and-roll guidance along that path for paths of random origins, such as during late-occurring missed approaches and circling-to-land maneuvers.

Abstract: The present invention provides systems, apparatus and methods for entering data into a flight plan entry field which facilitates the display and editing of aircraft flight-plan data. In one embodiment, the present invention provides a method for entering multiple waypoint and procedure identifiers at once within a single a flight plan entry field. In another embodiment, the present invention provides for the partial entry of any waypoint or procedure identifiers, and thereafter relating the identifiers with an aircraft's flight management system to anticipate the complete text entry for display. In yet another embodiment, the present invention discloses a method to automatically provide the aircraft operator with selectable prioritized arrival and approach routing identifiers by a single manual selection. In another embodiment, the present invention is a method for providing the aircraft operator with selectable alternate patterns to a new runway.

Abstract: Deriving inertial-aided deviations for autoland systems during GPS signal interruptions involving an inertial reference system and a GPS landing system can include converting position coordinates of an aircraft from the inertial reference system to runway, lateral, and vertical coordinates. After this conversion, the method calibrates runway distance and lateral distance based on the converted position coordinates from the inertial reference system using runway distance and lateral distance from the GPS landing system with a third-order calibration filter when the aircraft is below a first height above terrain and calibrates vertical distance based on the converted position coordinates from the inertial reference system using vertical distance from the GPS landing system with a second-order calibration filter when the aircraft is below the first height above terrain.

Abstract: Process for designing flight controllers, in which first for the rigid airplane and then for the elastic airplane the damping and the phase delay for each excitation frequency is determined, and the flight controller is adapted in such a manner that the structural responses to each excitation frequency for both the rigid airplane and the elastic airplane in the open control circuit outside two design fields, applicable to the elastic airplane, are laid around the instability points in the data field comprising damping and phase delay, whereby for the design of the elastic airplane between the phase delays of −270 degrees and −495 degrees, a damping exceeding −6 dB is allowed.

Abstract: An aviation navigational system and method for predicting glide range for an aircraft for specific airports and other potential emergency landing locations in proximity to the aircraft. Information is presented to the pilot by complementing a conventional moving map display with symbols centered on each landing location. GPS altitude, airport elevation, and the aircraft's glide ratio are factored into an equation to determine glide range for each airport within proximity to the aircraft. A circular symbol representing the glide range boundary is displayed around each airport. Each circular symbol represents a sectional view of an imaginary inverted cone, having the apex thereof centered on a given landing location. The size and shape of the cone is based on the gliding performance of the aircraft and the altitude differential between the aircraft and the target landing location. As the altitude differential increases the radius of the circle increases.

Abstract: Aircraft piloting system, at least for piloting the aircraft during a non precision approach with a view to a landing.

Abstract: The method provides for determining an approach mode which has been selected by the pilot of the aircraft from among a plurality of predetermined approach modes, for selecting a characteristic segment (6) of an arrival path which relates to the selected approach mode thus determined, for determining the orientation of the projection on the ground of the said characteristic segment (6) with respect to the center line of the said runway (5) and, depending on this orientation, for determining an anchoring point of the said final approach path, the orientation (&agr;) in a horizontal plane of the said final approach path and the slope (&bgr;) of the said final approach path.

Abstract: A critical point on a runway indicates a point at which an aircraft may experience a runway overrun if landing beyond the critical point. A path projection is extended from the aircraft at a descent slope angle to determine whether the aircraft will land beyond the critical point at the current descent slope. Timely alerts may be provided by accounting for the time required to announce a distance value, and the distance traveled during the announcement.

Abstract: A method, system, and computer program product for using airport information based on the flying environment are provided. When a helicopter is determined to be approaching a runway, ground proximity warning envelopes are automatically reduced to prevent unwanted, or nuisance, terrain alerts. On the other hand, when a helicopter is flown near a runway without intent to land or when a helicopter is taking off, ground proximity warning envelopes may remain unchanged. As a result, nuisance alerts are reduced when a helicopter is approaching a runway for landing and ground proximity warnings may remain in effect to maximize protection when a helicopter is flying near a runway without an intent to land or is taking off from a runway.

Abstract: A dialog method for dialog between an operator of an aircraft and at least one system of the aircraft including the steps of displaying on a display at least one window including a plurality of responsive objects respectively associated with one of multiple functions of the at least one system of the aircraft, moving a cursor on the display so as to designate a responsive object such that when the cursor is on the responsive object, a main object marker appears and designates the responsive object, and discretely displacing an auxiliary object marker on the display, responsive object by responsive object, so as to designate a responsive object without affecting control of the main object marker.

Abstract: An arrangement for generating control commands for controlling the slats and landing flaps of an aircraft includes two manually operable command input levers which are arranged directly side-by-side or as a “rod-within-rod” and are connected respectively by two linkages to two rotatable sensor disks that respectively cooperate with two sets of signal emitters that are electrically connected respectively to two control computers. The two levers and two linkages are coupled to form a single command transducer having two coupled parallel command transmission paths. Based on the signals of the signal emitters, the control computers generate actuating signals that are provided to actuators for adjusting the positions of the slats and landing flaps.

Abstract: An airport feature display system for aircraft provides visual guidance cues and awareness to track the specified taxi path on a HUD. The guidance cues include symbology representative of the position of selected airport features such as runway and taxiway edges, taxi routes, and airport signage. Data representative of the airport features is communicated between aircraft systems using a data interchange method that facilitates efficient throughput of the large quantities of data required to represent the airport features.

Abstract: A method for coordinating numerous vehicles within a common maneuver is characterized by receiving, at a moving vehicle, state and projected maneuver information of other vehicles participating in the maneuver via a broadcast link and utilizing the information to control the trajectory of the moving vehicle based on predicted paths of all participating vehicles for future times for which the maneuver is to be conducted. For simple maneuvers, such as flight-deck based self-spacing of aircraft in a runway approach, the method allows each participating vehicle to virtually perform the coordinated maneuver by predictive simulation using current state data to determine if corrective measures need be undertaken, or, if the predicted maneuver shows that it would complete as planned, maintaining its current trajectory. This affords vehicle operators the freedom to perform other duties, as the operators are alerted only when a change in state is necessitated.

Abstract: A method, avionics apparatus and computer program for determining a terminal flight path, including access to aircraft position information provided by a Global Positioning System (GPS) receiver. The method apparatus and computer program determine an Intended Touchdown Point (ITP), which is the desired landing location on an intended runway; determine a Current Touchdown Point (CTP), which is where the aircraft will land given its current glidepath and is a function of the current trajectory, configuration and engine thrust; determine a correspondence of the CTP and ITP and generate an output signal as a function of the correspondence, which is displayed on a cockpit display device, annunciated on a cockpit speaker, or both.

Abstract: A system is directed at automatically detecting events that are extremely important for a civil airline, and which have conventionally been grasped by means of radio intercepts by experts in air traffic control, such as TAKEOFF, LANDING, GO-AROUND, DIVERT after entry into an approach area, REJECT-TAKEOFF, arrival at an arbitrarily set altitude, entry into HOLDING, and release from HOLDING of civil aircraft; for a data source, response waves from a conventional ATC mode S transponder are received when these are transmitted by aircraft for the purpose of receiving air control, and data comprised therein is extracted and used; a computer comprises a simplified initialization function, allowing detection conditions to be set simply by selecting related parameter values from a list for each event to be detected, so as to readily adapt to the specific operations of each airport and airline company.

Abstract: The device (1) comprises a means (2) for determining at least the current speed vO of the vehicle, a means (3) for determining a value acc corresponding to a deceleration of said vehicle, a calculation means (4) for calculating the distance df to be traveled on the ground by the vehicle in order to reach a particular speed vf by using the expression df=(vO2=vf2)/(2 acc), and a means of presentation (7) for presenting this distance df to a driver of the vehicle.

Abstract: A method, avionics apparatus and computer program for determining a terminal flight path, including access to aircraft position information provided by a Global Positioning System (GPS) receiver. The method apparatus and computer program determine an Intended Touchdown Point (ITP), which is the desired landing location on an intended runway; determine a Current Touchdown Point (CTP), which is where the aircraft will land given its current glidepath and is a function of the current trajectory, configuration and engine thrust; determine a correspondence of the CTP and ITP and generate an output signal as a function of the correspondence, which is displayed on a cockpit display device, annunciated on a cockpit speaker, or both.

Abstract: A method for locating aircraft with respect to airport runways and taxiways, generating and annunciating situational awareness advisories as a function of aircraft state parameters relative to a determination of the aircraft location.

Abstract: The present invention is structured such that, as for travelling on the ground, there is provided a braking mechanism capable of braking wheels by the use of a single brake pedal or a braking mechanism capable of braking the wheels by flare out operation of a control stick, while automatic control of traveling direction is performed in flight using a yaw damper. In addition, a larger braking force is automatically generated, without manual operations by a pilot, for landing gear mounted on the side of an airframe toward which direction of an aircraft is to be changed as compared with the braking force applied to landing gear on the other side.

Abstract: An interactive flight map is provided to a passenger, through which information on the areas overflown can be accessed and utilized. A map of the portion of the flight path near the airplane, where the map has one or more identifiers, is displayed to a passenger. Selection of an identifier from the passenger may be received, and in response information associated with the selected identifier is displayed to the passenger. The identifiers may be icons, text or other unique identifying symbols, associated with points of interest, map locations, tourist facilities, or other particular locations or facilities. The map may be scrolled to view other areas of the ground. In response to the selection of a particular identifier by a passenger, information may be displayed to the passenger in a variety of formats, such as HTML or video.

Abstract: A method of guiding an aircraft in the final approach phase including imaging the ground using an imaging system on board the aircraft to obtain an image, analyzing the image to detect an airport area, detecting an airport area and selecting a runway for landing, tracking the selected runway during the approach of the aircraft by visually tracking the selected runway in the image supplied by the imaging system, and tracking the runway when the aircraft is very close to the ground by analyzing the image supplied by the imaging system to determine the position of the aircraft relative to the runway.

Abstract: A system for automatically controlling lift augmentation devices of an aircraft, during a phase of take-off by the aircraft, includes a controllable actuator that shifts the lift-augmentation devices, and a control unit for generating control demands to control the actuator to bring the lift-augmentation devices into a defined position. The control unit further includes a detector that detects actual take-off by the air craft and, if appropriate, signals such detection to the control unit. At start of the take-off phase, the lift-augmentation device are brought into a first position, in which they are deployed. The control unit generates, at least when the detector signals the actual take-off, a control demand making it possible to bring the lift-augmentation devices into a second position, in which the lift-augmentation devices are retracted by comparison with the first position.

Abstract: A method for automating a landing maneuver for an aircraft, comprising the steps of generating an approach profile comprising an initial approach fix (IAF), a flight path, a landing decision point, a balked landing route, a pre-landing point, and a landing point, engaging an automated approach system to access the approach profile, receiving periodic position data of the aircraft, comparing the position data to the approach profile to compute a plurality of deviations each time the position data is received, outputting the plurality of deviations to a display, converting the plurality of deviations into a plurality of control commands, and maneuvering the aircraft in response to the control commands along the flight path.

Abstract: A method and system for determining a desired altitude for an aircraft during descent toward a runway is provided. The method and system utilize latitude and longitude data provided by a global positioning system (GPS) as well as coordinate data concerning the location of a touchdown point. Elevation data concerning the elevation above mean sea level of the touchdown zone of a runway on which the aircraft is to land is utilized in the exemplary embodiment. The method and system of the invention determine a desired altitude for the aircraft without regard to the actual altitude of the aircraft. Instead, the data utilized provide a pilot with recommended altitude data that can be used to maintain a course of approach to the runway at a prescribed angle.

Abstract: A global landing system (GLS) for retrofitting an aircraft having ILS systems, as well as autopilot or flight control computers. The GLS using horizontal and vertical guidance control points (GCPs) which are co-extensive with glideslope and localizer antenna locations, and correction lever arms representing the separation of such GCPs with on-board GPS antennas. A method of measuring such lever arm with an additional GPS receiver is also included.

Abstract: An aircraft guidance system uses radar imaging to verify airport and runway location and provide navigation updates. The system is applicable to flight operations in low visibility conditions.

Abstract: Methods and systems for programming the automatic guidance unit of an aerial delivery system. The operator selects on a hand-held unit the desired flight parameters such as the latitude, longitude and altitude of the desired landing site, as well as the desired landing heading and default heading. A microprocessor converts this data into digital data that is stored on a removable EEPROM memory key. This key is then removed from the hand-held unit and at any convenient time, inserted into a mating female receptacle in the automatic guidance unit of the aerial delivery system. The programmed information originally entered in the hand-held unit is then transferred into the guidance unit of the aerial delivery system.

Abstract: A taxi planning system for aircraft provides an intuitive user interface for entering and selecting taxi plans quickly and easily. The system includes predefined reduced selection menus that prompt the pilot with feasible taxi choices. Predefined standard routes allow the pilot to select a taxi route with a minimum of keystrokes and in a minimum of time. A display screen communicates the selection menus and standard routes to the pilot who makes a selection with as little as one keystroke. A database comprising a linked list structure facilitates a flexible system that is able to represent a wide variety of airport runways, taxiways, gates, ramps, and other airport structures. The selected taxi route is communicated to other aircraft systems such as head-down displays, head-up displays, flight management computers, communication systems, and the like.

Abstract: An airport map display system for an aircraft displays the airport paved surfaces and structures to a pilot or crew member. The system displays runways, taxiways, connectors, ramps, gates, and buildings. Hold and yield points may also be displayed. A compact set of specific data points and associated pavement width values is used to store unique data for each airport.

Abstract: The present invention is directed to novel methods for depicting glide range on moving map displays and on perspective-view primary flight displays. These methods involve processing data gathered from various aircraft sensors and, using a variety of electronic databases, generating intuitive symbols that aid the pilot.

Abstract: An approach suppressed TAWS system and method for suppressing nuisance alarms based upon a determination that an aircraft is properly aligned for landing based upon location within a safe zone defined by a glideslope component and a localizer component.

Abstract: The present method and apparatus consists of storing past values of estimated IRU error and using these past values to update the coasting filter when switching from GPS to inertial mode. Through the storage of past IRU error estimates, it is possible to avoid misdirected guidance from an erroneous GPS signal. The MMR and ground station can require up to 6 seconds to identify a failed GLS signal.

Abstract: The present method and apparatus consists of storing past values of estimated IRU error and using these past values to update the coasting filter when switching from GPS to inertial mode. Through the storage of past IRU error estimates, it is possible to avoid misdirected guidance from an erroneous GPS signal. The MMR and ground station can require up to 6 seconds to identify a failed GLS signal.

Abstract: A system is provided for managing the inbound flow of aircraft to an airfield by ensuring that aircraft are sequenced before departure into an arrival stream. Sequencing uses operational data obtained from airlines and then provides a methodology for sharing this data with the air traffic control (ATC) agency. The outcome is a daily arrival schedule providing a predetermined operational arrival time for each aircraft movement. The operational data used by the system relates to airline punctuality, taxi times at departure airfields and actual flight times predicted on a flight-by-flight basis by airline flight planning systems. This information is combined to effect a predictive arrival time at a desired navigational fix. When used in conjunction with an optimised sequencing process for the final arrival time, the system then creates a Tactical Arrival Time (TAT) for an individual flight. Airlines share proportionally in a measure of departures from requested TATs, such measures being optionally weighted.

Abstract: An embedded terrain awareness warning system for aircraft being flown by a pilot includes a signal processing component, a protection component and a pilot vehicle interface. A method for providing an embedded terrain awareness warning system for aircraft being flown by a pilot includes providing a signal processing component, a protection component and a pilot vehicle interface. The signal processing component communicates with three-dimensional digital terrain elevation data and is able to take input data from aircraft sensors, aircraft computers or navigation systems and determine aircraft position and velocity. The protection component is in communication with the signal processing unit such that the protection component is able to determine if a potential controlled flight into terrain exists and is able to predict a recovery flight path to avoid terrain.

Abstract: A sensor detects skewed adjacent movable component. The sensor may be used to detect harmful skews of aircraft control surfaces, such as slats or flaps on aircraft wings, which may be caused by an actuator disconnection from the surface it drives. Harmful skew, which is a relative asymmetrical motion of control surfaces beyond a predetermined limit, is detected by the sensor, but the relatively smaller harmless skew caused by normal flight is ignored. The sensor comprises first and second arms connected to a common base that may be attached to a first control surface. A constraining means such as a mechanical fuse holds the arms together while a separating means such as a spring exerts a separating force on the arms when the fuse breaks. A switching means is integral to the two arms. A striker pin on a second control surface strikes the first or second sensor arm when the relative motion between the control surfaces exceeds a certain predetermined limit.

Abstract: A system and method for issuing an aircraft drift advisory. In one embodiment, the system includes a head or eye tracker to monitor the rotational position of the pilot's line of sight with respect to the aircraft axis. The pilot's line of sight is compared to the direction of the aircraft. If the absolute value of the difference is greater than or equal to a predetermined angle, corresponding to the foveal cone of vision, the incremental aircraft drift distance is computed and used to update the cumulative aircraft drift distance. The cumulative aircraft drift distance is compared to the predetermined advisory criterion, which may be a constant, a uniform function of altitude or a function of altitude that is tied to a digital terrain map. When the cumulative aircraft drift distance equals or exceeds the advisory criterion, the pilot is given a drift advisory that the aircraft has drifted so as to prompt the pilot to adjust his line of sight to the direction of the drift.

Abstract: The present invention provides several apparatus, methods, and computer program products for determining a corrected distance between an aircraft and selected runway, such that the corrected distance may be used for ground proximity warning calculations. Specifically, the present invention includes a processor that receives data related to the coordinates of the aircraft and a selected runway. Based on these coordinate values, the processor determines a coordinate distance between the aircraft and selected runway. The processor also compares the altitude of the aircraft to a predetermined glideslope constructed about the runway. Specifically, the processor calculates a distance value that corresponds to the altitude of the aircraft above the runway along the predetermined glideslope. The processor compares the coordinate distance and the calculated distance values and selects either the coordinate distance or the calculated distance value as the corrected distance between the aircraft and the selected runway.

Abstract: The present invention stores data of the nearest airport where an airplane can take off and land as well as database of an ETOPS-applied time related to this airplane beforehand. When a flight route is set, this ETOPS-applied time is read out. An area having a radius r calculated on the basis of the ETOPS-applied time is defined to be a flight-permitted area. With this, if a desired route entered by the operator is outside this area, an operating port calculates a flight route that can be contained in the flight-permitted area throughout the total flight.