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 flight control system and method for controlling a circle-to-land (“CTL”) maneuver utilizes an airborne area navigator. The area navigator receives inputs on aircraft category, aircraft position and speed, airport navigation data and pilot supplied data. In response to this data, the area navigator calculates the necessary conditions for executing the CTL maneuver and outputs control commands to a flight director. The pilot then executes the CTL maneuver either manually using the information provided by the area navigator or by using the aircraft autopilot under the direction of the flight director.

Abstract: A self contained electronic system for manual or automatic control and navigation of fixed winged aircraft using electronic position sensing such as GPS, DGPS, WAAS, and the like, as the primary sensor and making use of known flight characteristics of the aircraft to determine aircraft attitude without any interaction with the aircraft, its controls, or the outside environment and without any moving mechanical devices other than switches, dials and connectors. The automatic and visual interface between the system and the pilot provides for simplified flight controls, and a new solution to the hazard of disorientation, and will reduce the time needed for a pilot to become proficient in VFR and instrument flying. A single instrument replaces many of the conventional instruments used for flight. Navigation data is provided in an easy to understand graphical format. The pilot is told explicitly where to move aircraft controls.

Abstract: An airport surface movement guidance and control system (SMGCS) involving detection, integrated processing and graphical display of the relevant, in particular the safety-relevant, positions and movements of aircraft, and optionally, vehicles, on airside (runway, taxiways, apron) and in the relevant airport airspace. At least one radar detects the positions and movements between airborne and parked positions of the aircraft. The relevant data are displayed after data concentration on the monitor of at least one controller station in graphical form and/or letter or number form. As a result, the operational management of the surface movement can be planned and executed from the at least one controller station by means of solely the SMGC system.

Abstract: An image sensor attached to an aircraft generates an image. The image includes a runway and other objects. The edges within the image are detected and Nav Data is used to predict the coordinates defining the runway. The predicted coordinates and the detected edges are correlated to determine the location of the runway within the image. The location of the runway within the image is then used to determine the lateral and vertical deviation of the aircraft relative to the runway.

Abstract: An imaging apparatus for aiding landing of aircraft in weather conditions obscuring a pilot's view of a runway. The apparatus comprises a plurality of LED assemblies which are disposed along the runway. Each LED assembly includes a plurality of LEDs, a receiver and a plurality of drivers responsive to the receiver for energizing the LEDs. The LEDs of each LED assembly are pulsed on by signals from a transmitter disposed adjacent an end of the runway. The transmitter also sends synchronization signals to a receiver located on board the approaching aircraft. The receiver on the aircraft is coupled to a processor which uses the synchronization signals to determine when the LEDs are energized and when they are not energized. The processor controls a CCD camera mounted on the aircraft so as to obtain an unobstructed view of the approaching runway. The processor controls the CCD camera such that the camera takes images (i.e., frames) while the LEDs are pulsed on and also while the LEDs are off.

Abstract: A wake turbulence avoidance light system is provided including an aircraft runway with a periphery including a pair of long parallel side edges and a pair of short end edges. Also included is a plurality of light assemblies mounted along at least one of the side edges of the runway in spaced relationship. A plurality of sensors are adapted for indicating a point on the runway at which a plane has departed. Finally, control circuitry is connected between the light assemblies and the sensors for indicating a location of the point by illuminating a light assembly adjacent thereto, as detected by the sensor.

Abstract: An alternate destination planner for searching a navigation database in an aircraft and identifying a plurality of alternate destinations at which the aircraft can land in the event of an emergency. For each identified alternate destination, the alternate destination planner calculates an estimated time of arrival (ETA) and an amount of fuel remaining upon arrival at the destination. The calculation of the ETA and the remaining fuel is based on user-modifiable parameters of aircraft speed, aircraft altitude, wind direction and speed, outside air temperature, and the type of routing the aircraft will follow from a diversion point to the alternate destination. The plurality of alternate destinations are displayed to a pilot of the aircraft according to the ETA to each alternate destination, with the closest alternate destination by time listed first. The plurality of alternate destinations are also displayed to the pilot on a map of the surrounding region that is provided to the pilot on a navigation display.

Abstract: An aircraft local-area augmentation system that employs a differential global positioning system (GPS) to assist aircraft (102) landing is disclosed. One or more GPS ground stations (120), each including at least two GPS receivers (122) and a datalink transmitter (126), calculate and transmit GPS correction data to an aircraft (102). An aircraft (102) employs a GPS receiver (106) for receiving ranging signals (112) from GPS satellites (108), and a datalink receiver (116) for receiving GPS correction data and other information from a GPS ground station (120). The aircraft (102) further includes a data processor (110) for determining a global position of the aircraft (102) as a function of the aircraft GPS pseudorange data and the GPS correction data. The system minimizes the introduction of non-common errors by the use of double-differencing calculations using multiple combinations of satellite (108) and GPS ground station receiver (122).

Abstract: A marker comprises a metal sheet bent to curve about an axis and forming, in sector perpendicular to said axis a hairpin turn and where there are median extents on each side, approximating in the sheet planar panels, defining an angle of 0.degree.-30.degree. to each other and having on their convex side, a retroreflectant layer.

Abstract: An aircraft landing determination apparatus and method for determining landing status of an aircraft by tracking arriving aircrafts and providing a unique runway assignment therefor. The aircraft landing determination apparatus includes a target processor, a track administrator, and a track reporter. The target processor culls multiple target tracks from a target data transmission provided by a target sensor. The track administrator receives the target tracks, selects at least one arrival track therefrom, and allocates a unique runway assignment to each arrival track. The track reporter receives the arrival track and runway assignment, prepares a track report thereabout, and transmits the track report to a position monitoring apparatus.

Abstract: An improved system is provided suitable for use in landing an aircraft (for example, helicopter, RPV, VTOL) on shipboard comprising a support, base, platform or housing, reciprocal from remote a landing area on the deck of a ship to a position proximate the landing area, the housing carrying an upwardly directed light sensor comprising a lens system and a pair of band-pass filters, one filter before the lens system of the sensor and one after the lens system, the filters each passing the identical wavelength of light at its center but which each need not have the same band width as the other, a pulse detector in close proximity to the upwardly directed light sensor, and means for securing the aircraft to the support, housing, base or platform.

Abstract: A control system includes at least one guiding device including a long range guiding water jet generator having a plurality of first nozzles each projecting a jet of water upwardly and a first illumination apparatus projecting a plurality of beams of light upwardly each in concert with the jet of water projected from each of the first nozzles so as to guide the flight vehicle along a predetermined direction when the flight vehicle is located at a longer distance relative to the guiding device and a short range guiding water jet generator having a plurality of second nozzles each projecting a jet of water upwardly and a second illumination apparatus projecting a plurality of beams of light upwardly each in concert with the jet of water projected from each of the second nozzles so as to guide the flight vehicle along the predetermined direction when the flight vehicle is located at a shorter distance relative to the guiding device.

Abstract: An aircraft navigational facilitation system (20) and method of use thereof operates in conjunction with conventional apparatus which provides aircraft current situational information. The system includes a memory (22) for storing runway and landing information for each of a plurality runways. An input device, such as a keyboard (24), is provided for selecting a destination runway. The system further includes a video display device (28) which simulates the view from a cockpit of the aircraft, with the view including the destination runway. The video display device is driven by a processor (26) which uses the current situational information and the runway information for periodically generating display signals for the video display device. The display signals cause the video display to provide an updated and scaled simulated three dimensional view of a perimeter of the destination runway from a perspective of the cockpit of the aircraft.

Abstract: Guide elements along paths and turns of a network emit guide signals for guiding vehicles along the paths and through the turns. Control elements, located at points in the network at which the locomotion of approaching vehicles may need to be controlled, emit control signals, such as "stop" and "start" signals. The signals are preferably various modulated and unmodulated sine waves having frequencies programmable by a system supervisor that sends itineraries to vehicles prescribing their respective travel routes, each itinerary containing at least a set of identifiers uniquely corresponding to the signals emitted along the paths and turns in a travel route. The order of the set indicates the order of paths and turns to be taken while travelling a route. A system interface, hosted by each vehicle, acquires itineraries pertaining to its host vehicle and provides path/turn information to a vehicle driver--a person or an apparatus.

Abstract: An improved system is provided suitable for use in landing an aircraft (for example, helicopter, RPV, VTOL) on shipboard comprising a support, base, platform or housing, reciprocal from remote a landing area on the deck of a ship to a position proximate the landing area, the housing carrying an upwardly directed light sensor comprising a lens system and a pair of band-pass filters, one filter before the lens system of the sensor and one after the lens system, the filters each passing the identical wavelength of light at its center but which each need not have the same band width as the other, a pulse detector in close proximity to the upwardly directed light sensor, and means for securing the aircraft to the support, housing, base or platform.

Abstract: An active, electro-optical display system for use on fixed-wing, land-based airport runways, is disclosed for remotely guiding a pilot during visual approach and landing of an aircraft. Conventional Microwave Landing System (MLS) ground-transmitted data is air-derived on board the aircraft and data-linked to a ground receiver to produce a continuous digital data signal indicative of aircraft slant range, elevation and azimuth relative to the desired landing position. The resulting data signal is electrically coupled to a signal processor governed in accordance with control guidance laws to produce three discrete signals indicative of the magnitude and direction of the descent rate error, the flight path acceleration, and the lateral drift rate of the aircraft relative to the intended landing area.

Abstract: A remotely-controlled lighting system for austere landing zone lighting includes a plurality of light units each having dual electroluminescent light panels, a plurality of remote controllers each having an electrical receiver, and a separate electrical transmitter. The light panel units and remote controllers, attached electrically, may also be attached physically and placed along the sides of a landing zone, while the separate transmitter is located at a remote, covert place, such as a foxhole. The transmitter and receivers of the remote controllers are capable of being preset to respectively transmit and receive a first sequence of coded pulses for turning "on" the light panel units and a second sequence of coded pulses different from the first sequence for turning "off" the light units.

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.