Abstract: A system and method are configured to provide a cost-effective runway monitoring tool that may be used by airports to aid in accident avoidance and investigation by generating and analyzing image data corresponding to runway areas and surfaces.

Abstract: An airport map display system provides situational awareness to a pilot of an airport's runways, taxiways, and other features relative to the pilot's aircraft. Data representative of an airport map is translated and communicated between aircraft systems using a data interchange method that facilitates efficient throughput of information used to represent an airport map. In addition, data representative of taxi routes, modified taxi routes, and current position of the aircraft at the airport are also translated and communicated using a compact data interchange method. Airport map data is scaled so that it is compatible with display systems previously incompatible with displaying some airport maps. Aircraft equipped with raster displays are manipulated to display map symbology by redefining existing vector group labels. For retrofit applications, the airport map display system is activated when a preexisting input (e.g., an “ARPT” button) is activated when a taxi-related page is active.

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 head up display system that incorporates conformal and non-conformal views and associated symbology to provide highly informative and intuitive guidance with respect to all aspects of operating an aircraft or other vehicle in a controlled geographical area, by utilizing calculated views from the pilot seat, aircraft speed, and relevant ground operation information.

Abstract: In an aircraft flight information display system, a viewing surface of the display presents an observer with a view of the flight space forward of the aircraft. The viewing surface includes a section displaying a translucent plane of flight of the aircraft along its lateral axis having as an upper bound a line transverse to the lateral axis. The portion of the flight space upward of the plane of flight of the aircraft is displayed as a second section of the flight space above the line. Information of the features of terrain in the flight space, flight parameters of the aircraft and TCAS information is processed to form images of the terrain and traffic in relation to the translucent plane of flight of the aircraft. Terrain and traffic features are rendered in different colors according to their location with respect to the plane of flight. A series of ring-like indicia are displayed in the translucent plane to indicate the distance ranges in the plane of flight of the aircraft.

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: An aircraft including an approach and landing system, including a navigation unit for providing navigation information, a weather radar unit for providing radar information, a processor which receives navigation information from the navigation unit and information from the weather radar unit, the processor unit providing an output representing information concerning the aircraft in accordance with the provided navigation information and radar information, a memory for storing information representing a scene, the processor unit correlating the stored scene information with the output representing information concerning the aircraft to provide a mapped scene, a display unit for displaying the output of said processor and the mapped scene, and a steppable frequency oscillator for providing a signal which is stepped in frequency to the weather radar unit, thereby providing an increased range resolution.

Abstract: The present invention relates to a device for aiding the piloting of an aircraft, especially a rotary-wing aircraft, in particular a helicopter. According to the invention, said device (1) comprises first means (2) for determining, on the one hand, the slope and the heading of a preset path of the aircraft and, on the other hand, the slope and the heading of a flight path which the aircraft can take in order to join up with the preset path, and second means (3) for presenting, on a display screen (5), simultaneously a first characteristic sign (S1), whose position on the display screen (5) is representative of the slope and of the heading of the preset path and a second characteristic sign (S2), whose position on the display screen (5) is representative of the slope and of the heading of the flight path.

Abstract: Process and device using a flight management system (FMS) for aiding aerial navigation. To facilitate the task of the pilot, the FMS carries out a dialogue with the pilot via a data display and input console (MCDU), which displays a list of tasks to be executed in the form of a succession of selectable and activatable main zones. Each zone corresponds to a task, executed via the console, and when the task has been executed (validation key actuated by the pilot), the list of tasks is redisplayed, with the zones for which tasks have been executed and validated appearing in a different color from other zones. The zones preferably appear in duplicate when there is a co-pilot, so that it is easy to see which tasks have been performed and by which pilot, and which tasks remain to be performed.

Abstract: An aircraft including an approach and landing system, including a navigation unit for providing navigation information, a weather radar unit for providing radar information, a processor which receives navigation information from the navigation unit and information from the weather radar unit, the processor unit providing an output representing information concerning the aircraft in accordance with the provided navigation information and radar information, a memory for storing information representing a scene, the processor unit correlating the stored scene information with the output representing information concerning the aircraft to provide a mapped scene, a display unit for displaying the output of said processor and the mapped scene, and a steppable frequency oscillator for providing a signal which is stepped in frequency to the weather radar unit, thereby providing an increased range resolution.

Abstract: An air vehicle landing/takeoff area mapping system includes a plurality of transmitters located in the landing/takeoff area with each transmitter propagating a signal having a signal frequency indicative of the transmitter location. A receiver is located on the air vehicle and is capable of scanning the landing/takeoff area. The receiver processes a received transmitter signal to produce an output based on the received transmitter signal frequency. Control logic processes a sequence of receiver outputs to produce an image of the landing/takeoff area on a display device located within the air vehicle to assist a pilot during landings and takeoffs of the air vehicle under either clear or inclement weather conditions and/or either day time or night time visibility.

Abstract: A device for assisting the piloting of a vehicle by instruments. Various indications are displayed on an aircraft head-up view finder including a horizontal line graduated in terms of heading, a perpendicular line graduated in terms of atitude, an aircraft symbol representing the direction of the longitudinal axis of the aircraft above the horizontal line and a velocity vector symbol representing the tracking slope followed by the aircraft with respect to the ground. These are determined with respect to the tracking and atitude scales. The guidance window whose position is references with respect to the same axis is also displayed. The pilot must control the aircraft as to bring the velocity vector into the guidance window and keep it there. The window is placed on the screen at a position which is computed by the computer and which corresponds to the direction of a point of the desired path of the aircraft, this point being at a predetermined distance ahead of the aircraft.

Abstract: A flight control system user interface apparatus and a control data display method thereof are provided to reduce a workload on a controller and to increase the safety of flight. A main-control terminal on a man-machine interface apparatus for use in a flight control system has an aircraft position display area 102, an aircraft order display area 102, a simple strip display area 104, an aircraft data display area 104, and a control pilot data link communication display area. These areas are arranged in such a way that they are controlled by one input unit.

Abstract: An aircraft display system positions a synthetic runway which is properly aligned with a target runway even during crosswind approaches. The relative position of the target runway is computed in a manner which reduces the accumulated error associated with previous systems. The lateral deviation rate of the aircraft relative to the extended centerline of the target runway is computed from data provided by various aircraft navigation and sensor systems. A track error angle representative of the difference between the extended centerline of the runway and the ground track of the aircraft is computed from the lateral deviation rate and ground speed. Runway bearing relative to ground track is computed from the track error angle and lateral deviation angle. Compensating runway bearing relative to ground track with drift angle yields a runway bearing relative to aircraft heading which is useful for positioning a synthetic runway on a display.

Abstract: A device for the substitution of an artificial image shown to an aircraft pilot by the corresponding real image includes a device for the simulation of human vision; criteria for the exploitation of the simulated image; compare to a device for comparing to compare the simulated image with the criteria of exploitation; a device for attenuating the artificial image, the artificial image being attenuated when the simulated image meets a given number of exploitation criteria.

Abstract: System for deriving an information, warning or alarm signal on board an aircraft in the event of an anomaly during take-off.According to the invention, the system comprises:means (4) for calculating the position D.sub.stop on the runway where the aircraft must stop if the pilot decides to interrupt the take-off procedure immediately, that is to say representative of the stopping distance of the aircraft during the acceleration phase of the latter at take-off; means (5) for comparing D.sub.stop to the length of runway L available so as to determine whether an interruption of the take-off is still possible.

Abstract: A system and method for detecting and viewing aircraft hazardous incidents such as flying aircraft and meteorological phenomena which includes microbursts, thunderstorms, tornadoes, and the wake turbulence of aircraft. The aircraft hazardous incidents are positionally and horizontally displayed to the pilot on a display, that is located in the aircraft cockpit, in relation to the flight path of the aircraft. The timely displaying of any of the aircraft hazardous incidents permits the pilot to take evasive action to avoid a potentially dangerous incident.

Abstract: The method for receiving and transmitting optical data and control information to and from remotely located receivers and transmitters in an optical location system. Wherein, the locator system tracks and locates the position of a main object having an attached transceiver. This transceiver has stored in memory selected identifying information about the object to which the transceiver is attached. The selected identifying information was received by the transceiver over it's 1-wire interface from a touch memory.

Abstract: The invention relates to a process for the display on a screen on board an aircraft of flying aid symbols. On the basis of information supplied by an inertial system and ground beacons processed by an on board computer, the process consists of displaying on an on board screen (EV) symbols more particularly representing the wings of the aircraft (A1, A2), the model of the aircraft (CP), its speed (V), the tendency to acceleration and deceleration (AD1, AD2), a flight path prediction (PT), the artificial horizon (H), the roll angle (.phi.), the sideslip (AL) and the total energy (ET1, ET2). It also consists of displaying the flight path to be followed in perspective (P1, P2, S3, S4, S5) and in projection (S'1 to S'5) on the plane of the runway. Any flight path segment during passage, as well as the segment following the latter are displayed in parallelepipedic form (P1, P2) in perspective.

Abstract: Automatically reconfiguring an electronic landing display that includes a flight path vector (FPV) symbol and a rising runway symbol combined with a digital altitude value that merge at low aircraft altitudes is disclosed. During approach, when the aircraft descends below a predetermined minimum altitude, e.g., 200 feet, the FPV symbol is removed. When the aircraft is on the ground and during takeoff, the rising runway symbol is removed. Removing one or the other of the merging symbols prevents the symbols from overlapping. Thus, the potential for pilot error due to one of the merging symbols occluding the other is avoided.

Abstract: A flight director command indicator for a cathode ray tube display has a single cue positioned in roll, pitch and translation by combining roll attitude and pitch attitude command signals. It includes cooperating indicia for providing visual commands to bring the aircraft to a predetermined flight path of attitude to satisfy the flight director command.

Abstract: An aircraft takeoff monitor having distance traveled sensors for measuring the distance traveled after the initiation of the takeoff roll. These sensors are interfaced with an onboard computer to provide the computer with information on the actual distance traveled by the aircraft since the takeoff run was initiated. The computer is programmable to receive predetermined input signals, including runway length, real-time inputs, and the initiation time, with the computer constantly generating a predicted ground distance that should be traveled since the initiation of the takeoff run. The computer is further programmed to compare the actual ground distance traveled to the predicted ground distance which should have been traveled and provide a display signal representative of this comparison on an onboard display instrument.

Abstract: An apparatus for generating computed images on an electronically controlled display surface is provided with an improved intensity shading generator. The shading generator operates by assigning each scan line of a raster display a fixed intensity between first and second points. The sweep position is monitored and each succeeding scan line between an initial position and a break point position of the image is monitored. The sweep intensity is incremented for each sweep line until the break point is reached, at which time new values for intensity are generated. The shading generator of this invention greatly reduces the bandwidth required to generate accurately placed intensity gradients perpendicular to the horizon in a displayed image system.

Abstract: A system of enhancing a limited field of view (LFOV) aircraft simulator, having less than a full 360.times.360 degree continuous field of view, such that while a primary object is tracking within the field of view it is fully reproduced as an aircraft, target, runway, etc. and once it migrates outside of this area, or if another primary object is located outside of this area, the object is represented and tracked as a light spot. Once the primary object migrates within the limited field of view, the light spot will be extinguished and replaced by the fully reproduced object. The relative distance of the primary object to the simulated cockpit is illustrated by varying the magnitude of the light spot.

Abstract: A glide slope indicator system in which light from an incoming aircraft's landing light is shaped by spherical/cylindrical lens combination into a line image which strikes a linear photodiode array. By determining which photodiode in the array the center of the line image strikes, the glide slope angle can be determined. An appropriate signal is communicated to the pilot via a pair of indicator lights mounted on the runway depending upon whether the aircraft is above, below or on the desired glide slope angle.

Abstract: A method and apparatus for determining the time remaining for maximum control action to be taken in order to achieve a desired objective (i.e., the chronodrasic interval) is disclosed. The method and apparatus continuously determines the amount of a parameter (e.g., runway distance) required to achieve a desired objective (e.g., stopping an aircraft before reaching the end of a runway on landing or accelerating an aircraft so that it reaches rotation speed before reaching the end of a runway on takeoff) if maximum control action is applied. The method and apparatus also continuously determines the total amount of the parameter remaining. The chronodrasic interval is then determined by deducting the amount of the parameter required to achieve the desired objective if maximum control action is taken from the total amount of the parameter remaining; and, dividing the result by a preselected (e.g., present or maximum) rate of change of the parameter.