Abstract: A seismic communication system suitable to communicate information to an underground device is disclosed. A seismic source (preferably on or near the surface of the earth) generates a timed series of seismic shots. These shots are then detected by one or more seismic receivers underground. Depending on the timing of these seismic shots, and the communication protocol selected, various information may be communicated to the underground target. Such a system is particularly desirable when the underground device includes a perforating gun because the perforating gun may not only be remotely detonated without the drawbacks of previous methods, but the detonation of the perforating gun charges may also be detected, giving an indication whether substantially fewer than all of the explosive charges detonated. The seismic communication system may also be used, as a component within a multi-functional well seismic system, for seismic reservoir monitoring or seismic monitoring of well operations.

Abstract: Methods and apparatus are provided for indicating safe or potentially hazardous operating conditions of an aircraft in a required navigational performance (RNP) environment. The apparatus comprises a course deviation display field with first and second markers defining outer boundaries of the RNP width and a central marker indicating the desired course within the RNP width, an aircraft estimated position uncertainty (EPU) marker in the display field whose size corresponds to the EPU relative to the RNP and a current aircraft position marker coupled to the EPU marker and moving therewith as the aircraft position changes with respect to the RNP width. The display desirably changes color and/or flashes to alert a pilot to a potentially hazardous condition when an outer boundary of the EPU marker approaches to within a predetermined guard-band distance of or overlaps either of the first or second markers. An audible warning can be included.

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: 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.

Abstract: System, devices and methods are provided for automatic flight logs. One method includes receiving one or more location data points associated with a flight, automatically recording the one or more location data points in a flight log, and allowing access through a display user-interface to view and operate on the flight log. Receiving the one or more location data points includes obtaining the location data points from a global positioning system (GPS).

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.

Abstract: A navigation device for navigating a vehicle to a point comprises a GPS receiver for receiving GPS signals, a processor connected with the receiver for processing the GPS signals, navigation data created by the processor, and a display page. The navigation data includes ground speed, altitude, vertical speed and rate of turn information, and the display page presents this information in individual graphic, circular displays representative of an aircraft instrument panel.

Abstract: Methods for generating information for displaying terrain on an aircraft display system that significantly reduces the computation and data load for producing the terrain display. This is accomplished through the use of intelligent level of detail control that computes and displays terrain and dynamic on-terrain perspective projection lines and distance rings aligned with the aircraft heading for depth perception and relative altitude awareness. The terrain details are processed and displayed in a manner that shows all significant terrain features, e.g., peaks, towers, and the like, but through the use of nonlinear error bound geometric morphing, coupled with triangle binary tree based terrain mesh generation, the polygon count, and thus the computational load, are significantly reduced, while visual fidelity is maintained.

Abstract: The present invention provides a system and method for filing and closing of flight plans. With the present invention, a computing device is provided that includes a flight plan filing device that is capable of electronically transmitting a flight plan to an airport server. The flight plan filing device provides an electronic form, such as an electronic version of FAA Form 7233-1, which may receive input from a user, such as a pilot of an aircraft. The completed electronic form is then transmitted to an airport server which forwards the form to a regulatory agency server which assigns a transponder code to the flight plan and stores the flight plan in association with the transponder code. The airport server further monitors for transponder signals of aircraft within a predetermined distance of the airport. When the airport server receives a transponder signal, the airport server determines whether the aircraft has landed based on the altitude indicated in the transponder signal.

Abstract: Data structures and systems are provided for configuring avionic equipment with profile data. Profile data is defined, stored, and/or retrieved. The profile data is used to configure one or more display fields of the avionic equipment, display units of measure, identify flight plans, define map settings, set navigation fields, define communication transceiver spacing, define data/time setup, to configure one or more timers, alarms, and/or to configure other communication, navigation, or surveillance settings associated with avionic equipment. Furthermore, instances of the profile data are associated with unique identifiers for storage and retrieval purposes.

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: A method and apparatus for conducting proximity operations is disclosed. The method called inverser proximity operations includes maneuvering an active vehicle into general proximity to a target vehicle, transmitting from the target vehicle to the active vehicle data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle in accordance with the data to effect a desired proximity operation. Another method called distributed proximity operations includes maneuvering a carrier vehicle into general proximity to a target vehicle, releasing one or more active vehicles from the carrier vehicle, transmitting from the carrier vehicle to the active vehicle(s) data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle(s) in accordance with the data to effect a desired proximity operation.

Abstract: Directed toward universal commercial-airliner application as an air/ground-lifesaving function, this cost-effective retrofitable system enables airliner-pilots to conveniently actuate an inconspicuous AIRCIA™/enable-switch,—thereby instantly disabling onboard flight-commands to render the airliner's guidance-system irretrievably placed into total reliance upon its existing autopilot-system in RF-communication with encrypted remote ground/air-intercept personnel. Acting to virtually confound any criminal-attempt by a hijacker to commandeer an airliner, the airliner thus becomes flown only as directed by an authorized remote/flight-control station in cooperation with the airliner's remotely-reprogrammed onboard avionics-system, automatically vectoring the airliner to land safely via the existing avionics/autopilot-system at a designated airport.

Abstract: Systems and methods are provided for integrated control, access, and presentation of flight information within the cockpit. Cockpit instrument systems and methods are provided which include a first cockpit instrument panel which has a first display proximately located to a first bezel. The first display is operable to present navigational data, communication data, and flight information data including airspeed, attitude, and altitude. The systems and methods further include a second cockpit instrument panel located adjacent to the first cockpit instrument panel. The second cockpit instrument panel has a second display proximately located to a second bezel. The second display is operable to present navigational data, communication data, and flight information data including detailed engine parameters.

Abstract: A system for tracking a fleet of vehicles, such as trucks or aircraft, includes a set of vehicle processing systems associated with each vehicle. Each vehicle processing system receives a travel route matrix from a remote server, and generates periodic vehicle position information which is compared with a propagating wave associated with different segments, or corridors, of the matrix. When the vehicle position is determined to lie outside the propagating wave and a geo-corridor at a particular point in time, alerts are sent to the server notifying the server of same. Corrective action can then be taken, such as remotely disabling the vehicle, or alerting a fleet manager.

Abstract: An apparatus and method for automatically displaying to a flight crew member a list of electronic charts appropriate for a set flight plan or alternatively displaying the appropriate chart in response to information input into an FMS.

Abstract: Systems and methods are provided for integrated control, access, and presentation of flight information within the cockpit. Cockpit instrument systems and methods are provided which include a first cockpit instrument panel which has a first display proximately located to a first bezel. The first display is operable to present navigational data, communication data, and flight information data including airspeed, attitude, and altitude. The systems and methods further include a second cockpit instrument panel located adjacent to the first cockpit instrument panel. The second cockpit instrument panel has a second display proximately located to a second bezel. The second display is operable to present navigational data, communication data, and flight information data including detailed engine parameters.

Abstract: A system and method for downlinking weather data, generated by existing weather and data sensors, to a ground station. The ground station utilizes data from multiple aircraft to form refined weather information, and uplinks the refined weather information to the aircraft. The refined weather information is stored at the aircraft and picture generating equipment, such as an existing onboard ground proximity terrain or weather radar picture and symbol generator, generates pictorial information depicting weather. The pictorial information is displayed, for example by an existing EFIS or weather radar display, in the form of polygons.

Abstract: A method of generating a synthetic pressure altitude is disclosed. The method includes providing a static air temperature to a data processing device. The method also includes providing a wind velocity, a ground velocity, and a geometric altitude to the data processing device. Further, the method includes performing a numerical integration based on the static air temperature, the wind velocity, the ground velocity, and the geometric altitude. The wind velocity and the ground velocity are used to estimate pressure gradients not included in a static air column model.

Abstract: A flight attendant actuated warning system for alerting a flight crew in a flight deck compartment of an aircraft of a potential hijacking or other troublesome situation includes a receiver unit on the flight deck and at least one portable transmitter unit with a flight attendant in the passenger cabin. In the event of trouble, the flight attendant can actuate the transmitter to transmit a preselected activation signal having a frequency that does not interfere with the avionics and navigational equipment of the aircraft. The signal is received by the receiver unit and activates an audible and visual alarm of the receiver unit to alert the flight crew. The signal may also actuate a radio in the receiver unit that transmits on a preselected frequency, a transponder to squawk a hijacking code, and a vibratory alarm of one or more portable receivers with flight attendants and/or a federal air marshal.

Abstract: Flight plan information is provided in the form of a series of waypoints having attributes which preferably include, among others, latitude, longitude, altitude constraint, and waypoint identifier. A flight path, defined by this information is modeled, and the flight plan model is checked against terrain information to locate any instances in which a potentially unsafe flight altitude exists. In flight, the flight path model is updated using aircraft position so that the path from the aircraft position to the next waypoint is reflected in the model. In the event that a potentially unsafe flight altitude is detected, an alert may be issued to the flight crew. The crew may then amend the flight plan or take other appropriate action.

Abstract: An integrated display for displaying navigation and communication information from a plurality of sources on a single screen provides an overall picture of selected information. A graphical representation of the relationship between predetermined types of selected information is also provided. Visual representations of various components provide information and identify active components and data paths. A warning indication alerts to specific conditions and alternate modes of display operation are provided in response to specific component failures.

Abstract: Flight control indicator for an aircraft, in particular a transport airplane, intended to supply the thrust generated by at least one engine of the aircraft.

Abstract: Attitude, ground velocity, and acceleration inputs from an aircraft Inertial Navigation System (INS) and/or a Global Positioning System (GPS) instrument on board the aircraft, are used to estimate wind velocity relative to the aircraft and/or the ground in three dimensions. A wind velocity in the third dimension is assumed to be zero. In an exemplary embodiment, one or more of a) atmospheric density, b) speed of sound, C) air temperature, d) thrust of the aircraft, e) aerodynamic force coefficients of the aircraft, and f) mass of the aircraft, are used in conjunction with the inputs from the INS/GPS instrument(s) to estimate the wind velocity. Air temperature can be used, for example, together with an ambient air pressure and/or a known altitude of the aircraft to indicate an atmospheric density.

Abstract: A system for managing an aircraft maintenance program for an aircraft operated by an operator includes means for extracting maintenance tasks for the aircraft from at least one aircraft maintenance document, means for sorting the maintenance tasks into initial maintenance task groups having common control points, and means for guiding the airline operator to organize the maintenance tasks and initial maintenance task groups into a plurality of maintenance task groups.

Abstract: An airborne collision avoidance system includes a receiver stage constructed and arranged to detect (a) at a first radio frequency, first interrogation signals, and first collision resolution advisory (RA) signals transmitted from other nearby aircraft, and (b) at a second radio frequency, first acquisition signals including position information with respect to the nearby aircraft, and first reply signals from the nearby aircraft. A transmitter stage is constructed to produce (a) at the first radio frequency, second interrogation signals and second collision RA signals, and (b) at the second radio frequency, second acquisition signals including position information with respect to the given aircraft, and second reply signals from the given aircraft in response to the first interrogation signals. Tracking and collision avoidance information derived by a system processor from the detected first acquisition and first RA signals is shown on a cockpit display.

Abstract: The present invention provides airline mechanics with an electronic maintenance terminal (MT) that displays real time central maintenance computer (CMC) data screens. The invention provides the mechanic with the ability to access fault isolation manual (FIM) troubleshooting procedures via an internal software hot link between the CMC fault code and the FIM procedure. The FIM data is a subset of the electronic portable maintenance aid (PMA) data. In addition to faults the present invention also links flight deck effect (FDE) EICAS messages to FIM troubleshooting procedures.

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: Electronics for a shock-hardened device, in particular a data recorder, incorporating non-volatile memory. The device has the functional elements: a signal conditioning circuit, an oscillator, an analog-to-digital converter (ADC), a field programmable gate array (FPGA), a trigger, and a non-volatile memory incorporating both electrically erasable programmable read only memory (EEPROM) and fast static random access memory (SRAM). As a recorder, the electronics enable efficient and reliable data recording in extreme shock environments, e.g., those involving dynamic testing of weapons such as target penetrating bombs or dual-stage warheads. It also provides for data retention upon loss or shutdown of power to the unit and yields high MTBF (mean time between failure) figures in more benign environments.

Abstract: A telemeter for telemetry of diagnostic messages from a mobile asset to a remote station comprises a processor coupled to the output of one or more condition sensors. The processor converts the output of the condition sensors to a diagnostic message, and provides the diagnostic message at a processor output. A transmitter is coupled to the processor output. The transmitter is adapted to transmit the diagnostic messages in the Industrial, Scientific, Medical (ISM) frequency band. An exemplary embodiment of a telemetry system of the invention comprises a telemeter adapted to transmit diagnostic messages in the ISM frequency band, and a remote station including a receiver for receiving the diagnostic messages in the ISM band.

Abstract: A method for generating a power setting parameter table. The method includes the steps of generating an index from a plurality of first and second inputs and determining a power setting parameter corresponding to each index and second input. The first inputs may include flight speed and temperature values and the second inputs may include altitude values.

Abstract: The invention relates to the field of methods for managing a man-machine interface in an at least partially airborne mapping system.

Abstract: A system allowing for an integrated flight loads balancing process at one or more time instances of a flight maneuver of an aircraft includes a processor and a plurality of resources. Additionally, the system includes a resource integration program that is executable by the processor. Upon execution by the processor, the resource integration program operates to integrate the plurality of resources so that the integrated resources are accessible to the system while balancing the flight loads at the one or more time instances.

Abstract: The wind turbulence prediction system according to the present invention provides a measurement system, which is capable of measuring three-dimensional wind turbulence, exhibits limited aerodynamic and structural effects when mounted on an aircraft, is capable of measurement even in cases in which the velocity is equal to or less than 20 to 30 m/s, at which velocity a Pitot tube is incapable of measurement, and even in cases where the air flow direction differs greatly from the axis of aircraft body, and does not produce an error resulting from disruption of the air flow by the aircraft body itself. The wind turbulence prediction system of the present invention adopts a system that measures the speed of remote three-dimensional air flow by mounting a laser wind speed indicator utilizing the Doppler effect on an aircraft, irradiating laser light while scanning same in a cone shape, and then receiving scattered light from wind turbulence regions forward of an aircraft body in flight.

Abstract: A spatial data search method, system and apparatus for identifying particular data of significance around a reference vector through the spatial data. The method involves determining a reference vector within a spatial region for which spatial data exists, loading a portion of the spatial data including the data around the reference vector into a memory buffer, and searching the spatial data in a prioritized order. The method, system and apparatus have particular utility in searching geographic data for a terrain awareness and warning system (“TAWS”) and display in an aircraft. Embodiments of the present invention provide advantages over existing sequential and radial search methods, significantly reducing the processing and calculations required and providing faster alerts to pilots.

Abstract: A method and system for autoflight information display. A method in accordance with one embodiment of the invention includes determining if an automatic aircraft controller is controlling an aircraft function based at least in part on a target aircraft speed. If so, the method further includes displaying alphanumeric information corresponding to the operation of the automatic aircraft controller at a first location of a display medium. If not, the method further includes displaying the alphanumeric information at a second location of the display medium different than the first location. The first location can be aligned with a display of the aircraft speed, and the second location can be aligned with a display of the aircraft altitude. In another embodiment of the invention, engine control information can be integrated with a display of aircraft autopilot and/or autothrottle information.

Abstract: A system and method provides a retrievable record of the flight performance of the aircraft and includes a ground data link unit that obtains flight performance data representative of aircraft flight performance during flight of the aircraft. A spread spectrum transceiver is coupled to a data store and operative to download flight performance data that has been accumulated and stored by the data store over a spread spectrum communication signal. A ground base spread spectrum transceiver receives the spread spectrum communication signal from the aircraft and demodulates the signal to obtain flight performance data. A wireless unit is operative with the ground data link unit. This wireless unit could be for inventory control of products during in-flight servicing of passengers.

Abstract: A device and method to provide backup electrical power to a vehicle data acquisition and recording system. The device operates to control its charging state, discharge state, and interval of discharge to ensure reliable operation of the recording system. The method delineates the process by which continuous electrical power can be supplied to the recording system.

Abstract: A method and system for acquiring and recording on-board data relative to the movement of a vehicle, whereby a sequence of images of a control panel of the vehicle is acquired by a video camera installed in a cockpit of the vehicle, and is then recorded in a storage device; at the same time, a position of the vehicle is determined by means of a satellite locating device, and the position assumed by the vehicle at the time the image is acquired is related to each image stored in the storage device.

Abstract: A method of preventing un-commanded power surging of an aircraft engine includes two steps of detecting whether the Weight-On-Wheels signal is on and detecting whether the Low-Power-Lever-Angle-Discrete signal is on, which indicate whether the aircraft is on the ground and whether the throttle lever is positioned for a low power range. If both results are positive, a further step is performed for comparing a measured engine power or thrust level with a predetermined threshold and a final step reduces the fuel supply or shuts down the engine, if the measured engine power level is greater than the predetermined threshold.

Abstract: A system and/or method is/are provided which reduces the likelihood of air vehicles being utilized by terrorists as weapons. In certain embodiments, when it is determined that the air vehicle is about to hit a designated structure (e.g., high-rise office building or apartment building, national monument, and/or government building), a controller automatically takes control of the air vehicle away from the pilot(s) and causes an automatic computerized pilot (auto-pilot) to take over control of the air vehicle and causes it to land at a selected airport and/or runway.

Abstract: Apparatuses and methods for displaying autoflight information and controlling autoflight systems. In one embodiment, a flight deck for an aircraft having an autoflight system includes at least one pilot seat, at least one window positioned forward of the pilot seat, and a forward instrument panel positioned forward of the pilot seat. In one aspect of this embodiment, the forward window provides a forward field of view out of the aircraft for a pilot seated in the pilot seat. In another aspect of this embodiment, the flight deck further includes a display device configured to provide information related to one or more autoflight modes. The display device can be positioned at least approximately between the forward instrument panel and the forward window to provide the pilot with autoflight information at least proximate to the forward field of view. In a further aspect of this embodiment, the display device can be configured to provide information related to one or more target flight parameters.

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: A system, method and device for selecting and displaying navigational information is presented which displays navigational procedures and/or options, allows for selecting and deselecting the procedures and/or options, and allows for generating a predetermined set of navigational procedures and/or options based upon the previous selection of navigational procedures and/or options. The system, method and device provide a more efficient and intuitive method for planning and programming a navigational path with special emphasis on facilitating the planning and programming of a phase of arrival for the flight path of an aircraft.

Abstract: An avionics system for providing information to pilots provides a communications bus, allowing each instrument in communication with the bus to access information from a plurality of sensors. Software based instrumentation and the ability to remove and insert computation units in communication with the bus provide the ability to change instrumentation. Interchangeable display units provide additional redundancy in the event of display unit failure.

Abstract: An alerting and/or notification system for operator(s) of a vehicle about conditions that affect the operation of the vehicle. The system collects information from one or more hazard warning systems, groups the warnings into different alert categories, and resolves conflicts between two or more hazard warnings within the same alert category to set a priority level. The prioritized alerts are presented to the operator, and associated detailed information also made available, in the form of graphical and/or textual messages on a display. Using two- or three-dimensional surround sound techniques, directional verbal and tonal aural cues also inform the operator(s) about the presence of threats and/or conditions. Visual displays and/or directional aural commands may be issued to dictate an evasive maneuver direction, if desired.

Abstract: A method and apparatus for rapidly displaying air traffic control (ATC) information on an ATC display provides a two-dimensional (2D) scene graph and associated 2D scene graph display commands in conjunction with a thee-dimensional graphic card. In other embodiments, any desktop application software can make use of a 2D scene graph and associated 2D scene graph display commands in order to rapidly render a 2D display.

Abstract: The present invention is a power lever tactile cueing system for providing tactile alerts to pilots as operational limits of an aircraft are approached. The cueing system generates a tactile cue comprising a variable dive rate and a variable friction force on a power lever of an aircraft. The cueing system provides spring-like tactile cues when power commands reach a predetermined operating limit, without the use of mechanical springs. The cueing system trims down the power lever position and provides the additional friction force based upon aircraft and engine state. The cueing system remains activated until the aircraft is again operated within its operational limits. The pilot may override the cueing system in certain situations.

Abstract: Systems and methods are provided for integrating cockpit controls and data associated with the controls into a single interface having a bezel surrounding a single display. Furthermore in one embodiment, a system includes two bezels having individual and duplicate controls affixed thereon, where each bezel surrounds a display operable to present data related to the controls. Moreover, the bezels are proximate to one another. Additionally in one embodiment, a system, having an audio control panel interposed between two bezels, is provided.

Abstract: A meteorological information system useable by aircraft pilots and others. A receiver-calculator unit receives raw meteorological data and site-specific physical data from a ground-based weather station having a signal transmitter for broadcasting signals conveying data about weather conditions at the station. The transmitted raw data signals are received by the receiver-calculator unit in the aircraft. The receiver-calculator unit may feature an input with which the operator inputs information about the physical character, such as the heading, of the runway of interest. The receiver-calculator unit processes both received raw weather data and received site-specific physical data, and/or operator-input data, to derive additional meteorological information. The raw and derived weather conditions information is displayed by the unit to be available to the aircraft pilot during landing or take-off maneuvers.