Abstract: A system, method, and computer program product are provided for monitoring for high energy landing approaches and advising a flight crew of an aircraft. Specific aircraft energy is predicted at a touchdown zone of a runway. The predicted specific energy is compared with predetermined threshold specific energy. An alert is generated when the predicted specific energy is at least the predetermined threshold specific energy. The present invention improves flight crew awareness of an impending problem with a landing approach, such as a high energy approach, provides an advisory when probability of an unsuccessful approach is significant, and allows a margin from stable approach criteria while avoiding increased aural and visual clutter in the flight deck.

Abstract: Method and system for automatically displaying, visually and/or audibly and/or by an audible alarm signal, relevant weather data for an identified aircraft pilot, when each of a selected subset of measured or estimated aviation situation parameters, corresponding to a given aviation situation, has a value lying in a selected range. Each range for a particular pilot may be a default range, may be entered by the pilot and/or may be automatically determined from experience and may be subsequently edited by the pilot to change a range and to add or delete parameters describing a situation for which a display should be provided. The pilot can also verbally activate an audible display or visual display of selected information by verbal entry of a first command or a second command, respectively, that specifies the information required.

Abstract: Apparatus and methods for enhancing the accuracy of height above ground measurements in which the registration error between successive images taken of the terrain over which an aircraft is flying is minimized, the earlier image having first been transformed according to measurements of the aircraft linear and angular velocities, the focal length and attitude of the image sensor, and an initial, coarse height estimate. By an iterative process, a more accurate height estimate is obtained.

Abstract: A method for flying in a degraded visual environment comprising the steps of collecting environmental data, processing the data and fusing the data together into a combined input output. The output is fed into a head down display, head mounted or heads up display and, preferably to a fly-by-wire vertical take-off and landing capable vehicle wherein the fly-by-wire system makes automatic adjustments to the helicopter.

Abstract: A graphical display of a vertical speed indicator showing “fly-to” and “no-fly” commands on the periphery of a vertical speed indicator during TCAS traffic or resolution advisory conditions.

Abstract: A flight control system includes a primary flight display having a hover display which facilitates operations in DVE conditions. The hover display includes a radar altitude display, heading drift symbology and lateral drift symbology which assists pilots in the detection of drift, which is common in DVE situations and to provide the pilot with a salient cue pertinent to the approach to hover and landing.

Abstract: Systems, 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: A method and apparatus is disclosed for displaying a dynamic parameter of an aircraft, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing to said scale in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.

Abstract: A monitoring instrument that represents the state of n parameters is disclosed, where n is an integer greater than two. The monitoring instrument includes n axes having a common origination point. Each axis is configured to indicate one of the n parameters. The instrument also includes a polygon having n vertices, wherein each vertex is disposed along one of the n axes at a location indicating the state of the parameter indicated by said axis.

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.

Abstract: There is provided a method for displaying aircraft positions, which is capable of effectively avoiding the occurrence of near miss or collision. The method displays the terrain of an air space under air traffic control apparently in three dimensions on a display screen, displays aircraft marks at positions on the display screen so as to correspond to the three-dimensional positions of the respective aircraft, and displays a warning mark when a distance between two aircraft is shorter than a threshold value, wherein the warning mark comprises a triangle having three apexes, which comprise the aircraft marks, and a position that is apart from the aircraft mark of one of the aircraft along a vertical line extending perpendicular to the one aircraft toward a ground surface of the terrain by a distance corresponding to an altitude difference between both aircrafts on the display screen.

Abstract: A display system for a vehicle is provided. The display system includes a display configured to render a representation of an intended vehicle path. At least one relative speed indicator is rendered upon the display. The at least one relative speed indicator is configured to move along the representation of the intended vehicle path, in an area of the display that is peripheral to a focus area of the display, in response to a difference between an actual value of a speed-based parameter and a preferred value of a speed-based parameter of the vehicle.

Abstract: A method for displaying flight information includes displaying a first characteristic sign illustrating a speed vector of an aircraft. The method also includes determining a first longitudinal margin of maneuver of the aircraft as a load factor, and displaying a second characteristic sign such that a position of the second characteristic sign relative to the first characteristic sign illustrates the first longitudinal margin of maneuver.

Abstract: A flight information display for the flight deck of an aircraft showing a pictorial side view of the flight path or the area directly in front of the aircraft area having a selected distance of at least 0.5 nautical miles, comprising (a) a pictorial representation to scale of the profile of the highest elevations of a swath of terrain along said path or area, (b) an icon positioned on the left or right side of the display representing the aircraft, the altitude of which is to scale with the height of the terrain, and (c) an altitude reference scale; wherein the width of the swath is at least 0.1 nautical miles and no greater than the distance of the minimum accuracy of the means for determining the aircraft's location.

Abstract: A symbology system uses programmable software in a computerized system interacting with the altitude, attitude, air speed, and other flight indicators of an aircraft to create symbology in the pilot's display seen in the field of view of the pilot. The symbology represents a virtual geometric solid form, such as a vertical cylinder, always appearing perpendicular to the horizon and moving across the terrain with the aircraft in the center of the form. The pilot sees a front portion of a virtual series of horizontal circles or other shapes, spaced by a programmable distance, symbolizing the geometric solid form appearing to surround the aircraft. The geometric form references the world as-ground for use in recognizing the attitude of the aircraft-as-figure. On landing, the form appears to stop at the ground and the aircraft appears to descend within it. A virtual bank indicator line changes orientation to the geometric solid corresponding to the attitude change of the aircraft relative to the horizon.

Abstract: A system, comprising a data receiving arrangement to receive target data points from a data feed arrangement, each target data point including data corresponding to a location of a target aircraft and additional information on the target aircraft, a data analyzing arrangement to analyze the target data points and store each target data point in a target flight record, the target flight record corresponding to the target aircraft a data generation arrangement to generate a flight track for the target aircraft using the data stored in the target flight record and a data distribution arrangement to organize the flight track and the additional information into a displayable file and distribute the file to users of the system, wherein the displayable file is displayed on a single graphical user interface including the flight track and the additional information.

Abstract: A method and system is utilized to produce an output corresponding to a safety level, particularly in relation to an activity on a moving body. The method involving producing an output corresponding to the ability to perform an operation within a safe limit on a moving vessel. The method comprising the steps of acquiring real time data from instrumentation on the vessel indicative of first and second elements of vessel motion relevant to the safety of the operation. Processing the data relating to each element of motion. Scaling the data relating to each element to a common scale to provide first and second values relating to the respective elements of vessel motion. Determining which value is of greatest significance and providing a output indicative of the greatest value.

Abstract: Method and indicator for displaying information showing the airspeed tolerance margins for an aircraft. The indicator comprises a central processing unit which selects, from a plurality of longitudinal scales, the longitudinal scale representative of the current aerodynamic configuration of the aircraft and a display means which presents on a display screen the selected longitudinal scale, which is mobile in the longitudinal direction, and whose position on the display screen depends on the current angle of attack of the aircraft, shown by a characteristic marker in a fixed position on the display screen across the longitudinal scale, the latter scrolling up and down relative to the characteristic marker as a function of the current angle of attack of the aircraft.

Abstract: A display system for an aircraft includes a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft. The longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver. The display system also includes a display unit connected to the central unit. The display unit includes a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver.

Abstract: The vessel monitoring system of the present invention enables vessel owners to monitor their vessels when they are unable or unavailable to personally do so. The system of the present invention provides an efficient method for inspecting and repairing a designated vessel at periodic intervals and for reporting the results of such inspections and repairs to the vessel's owner in a timely manner for the owner's review and consideration.

Abstract: A programmable symbology is provided that defines a series of geometric forms in the visual field of a pilot. The symbology includes a virtual representation of a predicted flight path of the aircraft and a virtual representation of a projected contact point with an external object, including the ground. The symbology also provides a virtual representation of a predicted flight path of the aircraft that is projected onto the ground below the projected flight path as a ground path predictor. The symbology further provides a critical slowing air speed indicator.

Abstract: A device for aiding the visual spotting of a second aircraft in flight by the pilot of a first aircraft looking at the sky through the canopy may include an approximately vertical display device and a first device that displays on the display device a representation of the canopy. A communication device receives position information relating to the second aircraft from an outside source. Using the received position information, a second device displays on the display device a symbol representative of the second aircraft such that the position of the symbol in relation to the displayed representation of the canopy corresponds to the position of the second aircraft in relation to the aircraft's canopy as seen through the pilot's field of view.

Abstract: The present invention provides a solid-state rotational rate sensor device formed by a thin-film for generating an electrical voltage output proportional to the rate of rotational motion. The precision thin-film piezoelectric elements are configured and arranged on a semi-rigid structure to detect rotation (such as pitch, roll, and yaw) while rejecting spurious noise created by vibration, thermal gradients, and electro-magnetic interference.

Abstract: The invention provides a primary flight display instrument in which a symbol—such as a small star or triangle—indicates the bearing to the current waypoint in the flight navigation plan. The display may also show a bearing indication symbol showing a follow-on waypoint in the flight plan. These symbols are preferably located on the horizon line of the primary flight display (or the attitude indicator) providing bearing to the current waypoint in the flight plan and/or to the following waypoint. An image processing unit generates the display, including earth ground and horizon, in a view substantially conformal with a VMC view from the aircraft.

Abstract: A method and system for transmitting engine control data to or from the engine control unit of an engine. The system includes a local communication unit capable of establishing a wireless communication link with a remote communication unit and a link for transferring data between the local communication unit and the engine control unit. In operation, a wireless communication link is established between the local communication unit and the remote communication unit. Engine control data is transferred between the local communication unit and the engine control unit and transmitted between the local communication unit and the remote communication unit via the wireless communication link.

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: Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.

Abstract: Systems and methods are provided for integrated control, access, and customizable presentation of navigation related, flight information data on a multifunction display (MFD) within a cockpit. The MFD includes a bezel having controls located thereon which are adapted for controlling display formats, communication devices, navigational devices, and equipment sensors. A display is located adjacent to the bezel. The display is adapted to include at least one display region having navigation related data. At least one of the controls is operable to variably select a display format for the at least one display region.

Abstract: Systems and methods are provided for customized displays and customized presentations of cockpit data. Configurable soft keys or controls located in close proximity to a cockpit display are provided. Each key is configured to perform a desired display function or other function. Labels are displayed adjacent to each of the soft keys to identify each of the soft keys. A display is operable to provide multiple views, each view within the display is adapted to be overlaid with additional cockpit data if so configured. Furthermore, each view is capable of being presented from one or more selectable perspectives as desired.

Abstract: The marine vessel monitoring system of the present invention enables marine vessel owners to monitor their vessels when they are unable or unavailable to personally do so. The system of the present invention provides an efficient method for inspecting and repairing a designated marine vessel at periodic intervals and for reporting the results of such inspections and repairs to the vessel's owner in a timely manner for the owner's review and consideration.

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: 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: 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: The present invention includes a display for viewing information, where a number of lines on the display has a variable line resolution scale. Each of the number of lines corresponds to a value of information, such as angle degrees relative to the horizon line of the sky in the context of avionics, for example. In addition, the present invention may include a value indicator positioned within the number of lines on the display such that the value indicator designates a value of information. Each distance between each of the number of lines may vary, so that the line resolution of the number of lines near the value indicator, for example, is greater than the line resolution further removed from the value indicator. By varying the line resolution using a distortion function, values of information on the display may be more precisely read.

Abstract: An electronic cockpit vision system for a vision system to enable maintenance of control, in continued flight and landing, of an aircraft and its systems when the cockpit has become invaded with dense and continuous smoke. The system includes an electronic signal converter, a scanner, a windshield video camera, cockpit video camera, and smoke over-goggles equipped with two eye level electronic video display devices. The signal converter feeds its output into a video display equipped smoke qualified over-goggle, resulting in the display upon a virtual screen of information essential to emergency flight and landing. The virtual screen displays the information in appropriate depth perception for ease of comprehension.

Abstract: Flight information is displayed using visual indications that resemble real world visual cues. For example, left and right side attitude displays extend vertically along each side of the windshield and a yaw display extends along a lower edge of the windshield. The attitude displays employ reference indications and outermost indications which track the position of the actual horizon. The yaw display employs outermost indications spaced from a reference indication a distance proportional to the rate of turn. Indexing of indications between the references and the outermost indications provides the appearance of movement representing climb, descent and turns. The rate and direction of indexing may be proportional to the rate and direction of change.

Abstract: The pilot's awareness of the aircraft's state is enhanced by supplementing the flight modes area (FMA) in the upper region of the primary flight display (PFD) with additional annunciators. The FMA in the present invention displays, in the active lateral modes region, the name of the waypoint the aircraft is flying towards and, if the waypoint is part of a published procedure, the procedure name is displayed in this area. Moreover, if the controls of the aircraft are set for a specific target, then the target, along with the mode annunciators, are displayed in the active vertical modes region of the FMA. Furthermore, if the aircraft starts to deviate from the preselected altitude, the pilot is alerted of the uncoordinated condition by a CHECK ASEL annunciation which is displayed in the lower center region of the FMA, namely below the autopilot (AP) annunciator.

Abstract: A primary flight display with three-dimensional capability provides information in an intuitive format for enhanced situational awareness. The display also includes other navigational data such as airspeed, attitude, altitude, and heading. The display may also include three view slices, a pictorial autopilot status indicator, vertical and lateral deviation and deviation history, glide slope and localizer information, airport and runway information, past position history of the aircraft and other nearby aircraft. The display may depict potential threats to the aircraft such as terrain or other manmade obstacles, nearby aircraft, severe weather thus increasing situational awareness with respect thereto. In a preferred embodiment, the three dimensional tactical map is implemented as a frequency separated display.

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.

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: The present invention is directed to novel primary flight displays, moving map displays and engine parameter displays for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using an various electronic databases, generate intuitive symbols that aid the pilot. The present invention also uses various novel algorithms that use data gathered from inexpensive sensors to derive parameters normally requiring far more expensive sensors.

Abstract: A portable computer system allows a pilot to efficiently and effectively manage time-oriented and other flight-related tasks. The system preferably includes a microprocessor coupled to a display/input screen. The microprocessor, which includes or is coupled to a timer, preferably executes one or more application programs that are configured to receive information from and display information to the pilot. The application program is preferably hierarchically arranged and menu-driven for navigating among the various displays and thereby retrieving the desired information or initiating the desired functionality.

Abstract: Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.

Abstract: A graphical display apparatus (and methods) for motor vehicles. The apparatus has a display coupled to an interior portion of a motor vehicle, which faces a driver of the motor vehicle. The display is coupled to an output for identifying a velocity value of the motor vehicle. A first graphical display portion of the display for outputting a first current speed indication of the motor vehicle using a first convention is also included. The first display portion for the current speed indication is coupled to the output. A second graphical display portion of the display for outputting a second current speed indication of the motor vehicle using a second convention is included. The second display portion is coupled to the first display portion such that the first current speed indication in the first convention is aligned to the second current speed indication in the second convention.

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.

Abstract: A compact, lightweight, cost effective, self-contained standby electronic navigation system with high signal-to-noise ratio and good dynamic stability is provided. The system includes a first sensor module for providing a plurality of rotational rate signals, a second sensor module for providing a plurality of compensation signals, and a microcontroller module for processing the rotational rate signals and the compensation signals and sending the signals to a display for displaying attitude information, directional information, and turn coordinate information on a single screen simultaneously. In one embodiment, the first sensor module includes a plurality of rotational sensors made of piezoelectric elements. The piezoelectric elements are made from a single sheet of piezoelectric material so that the elements possess uniform characteristics, and are arranged to reduce systematic drift and random noise normally present in a rotational rate sensor. The sensors can be configured on a single multi-sensor chip.

Abstract: Process and device for aiding the piloting of an aircraft.

Abstract: An apparatus, method and computer program product for an integrated display presentation for tactical flight path management that simplifies instrument flight by replicating many of the cues basic to visual flight using spatial flow, integrating navigation information conformal symbology, and improving instrumentation using an enhanced “T” instrument display.

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.

Abstract: Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.