Abstract: A relative navigation system comprising of a pair of Global Navigation Satellite System (GNSS) and Inertial Navigation System (INS) units that communicate to provide updated position, velocity and attitude information from a master to a rover. The rover unit produces a carrier based solution that enables the system to reduce the uncorrelated low latency position error between the master and the rover units to less than 50 cm.

Abstract: A lighting device, capable of identifying and marking traffic areas of airports, comprises at least one semiconductor lamp and an electronic control circuit, which is connectable to an electrical AC supply network with constant current feed. For controlling the operation of the semiconductor lamp, the control circuit has a rectifier, which is connectable without a transformer to the electrical AC supply network. It further has an internal power supply, which is connected to the rectifier, for supplying the semiconductor lamp with an electric direct current. Furthermore, the voltage supply device (3) having electronic power factor correction means, by means of which voltage and current can be kept in phase in all operating states of the lighting device (1). It furthermore re-adjusts the input voltage from the electrical AC supply network to allow the current predefined on the AC supply network to flow in the event of a small power demand of the electronic control circuit.

Abstract: An aeronautical safety device which seeks to improve landing and take-off operations of aircraft, having a simple device which, by means of light means and push buttons or actuators indicating the instructions received, allow reflecting the instructions received from the control tower on a panel or in any other enabled point or by the senior cabin crew members themselves. The device has a casing on which at least two display indicators are arranged. One of them would serve for indicating that permission for takeoff or landing has been received, while the other light indicator would exclusively serve to indicate that the cabin is secure. The display indicators indicating that the instruction to initiate takeoff or landing has been received can range from light indicators to simple hinged flaps.

Abstract: A method and apparatus for displaying an energy state of an aircraft. The energy state of the aircraft is identified by a processor unit based on a speed of the aircraft and an altitude of the aircraft. An indication of the energy state is displayed by the processor unit.

Abstract: A method, apparatus, and computer program product for displaying information about runways. A runway for an aircraft is identified when the aircraft is within a selected distance of the runway. A number of graphical indicators are displayed on a display in a flight deck. The number of graphical indicators corresponds to a number of features of the runway present in a field of view for an eye reference point in the flight deck.

Abstract: Another embodiment of the disclosure relates to an altitude system for an aircraft. The aircraft radar system includes a processor configured to determine an altitude of the aircraft using runway position information, and an angle to the runway associated with a radar beam to the runway. The angle to the runway is being determined using a pointing angle of the antenna adjusted with an angular offset. The angular offset is determined from phase processing.

Abstract: An infrared laser landing marker system provides a capability to mark a boundary line of varying lengths with near infrared lasers, e.g., of the order 8xx nm. This system can be either directly operated or remotely operated via satellite communications and is compatible with currently fielded night vision goggles. Two modules, placed at either end of boundary, self align to each other and then proceed to mark a boundary edge of a landing zone with an infrared laser line.

Abstract: A lighting device, capable of identifying and marking traffic areas of airports, comprises at least one semiconductor lamp and an electronic control circuit, which is connectable to an electrical AC supply network with constant current feed. For controlling the operation of the semiconductor lamp, the control circuit has a rectifier, which is connectable without a transformer to the electrical AC supply network. It further has an internal power supply, which is connected to the rectifier, for supplying the semiconductor lamp with an electric direct current. Furthermore, the voltage supply device (3) having electronic power factor correction means, by means of which voltage and current can be kept in phase in all operating states of the lighting device (1). It furthermore re-adjusts the input voltage from the electrical AC supply network to allow the current predefined on the AC supply network to flow in the event of a small power demand of the electronic control circuit.

Abstract: A precision approach path indicator system (PAPI) including multiple LHA indicators and power sources. Each LHA indicator comprises several assembly modules, with each module made up of several red and white LEDs, several collimating lens, one optical combiner, and one projection lens set. From a side view of the module, the red LEDs are placed on top of white LEDs, with a collimating lens in front of each LED. The optical combiner is in front of both the red and white LEDs, slightly above the white LEDs in vertical placement. The optical combiner has a reflective coating on the bottom surface, and a red light filter coating on the projection surface. The combined beam of light is projected out through a projection lens at front of the assembly module.

Abstract: A visual display system is provided, and includes a visual display element configured to display a visual display with three-dimensional, conformal background information at a first perspective; and a processor coupled to the visual display. The processor can be configured to evaluate flight path information and to adjust the visual display into a second perspective if the flight path information cannot be accurately displayed at the first perspective relative to the background.

Abstract: In a method for aiding aircraft landing using a GPS and an MLS within the context of a computed axial approach, the method uses coordinates of an azimuth antenna and/or of an elevation antenna as a reference point for the computation of a position of the aircraft in a reference frame centered on the landing runway. This position of the aircraft is thereafter used to determine an angle of azimuth between a longitudinal axis of the landing runway and the aircraft.

Abstract: A present novel and non-trivial system, module, and method for presenting messages to a pilot of an aircraft are disclosed. The system comprises a source for providing message data, a message generating (“MG”) processor, and a presentation system. Message data received from a message data source includes data fields for providing message location on a flight plan and one or more modes of presentation. After receiving the message data, an MG processor generates a message presentation data set corresponding to the message data; the message presentation data set represents a message object shown at the message location on a flight plan and at least one presentation mode. Then, a presentation system receives the message presentation data set and presents the information contained in such data set to one or more units of the presentation system including a visual display unit and/or an aural alert unit.

Abstract: A method of and system for determining the altitude of an aircraft can use a relative altitude estimate using information from an onboard radar. The altitude can be referenced to a runway for landing operations. The radar can produce relative altitude information from the range to the landing point and a precision estimation of the vertical angle to the landing point. The vertical angle estimate can be made with a phase processing antenna/radar system.

Abstract: An apparatus for aligning an aircraft with an area on the ground is provided. The apparatus includes an aircraft having an on-board landing system, the on-board landing system configured to record an image of an area on the ground. The apparatus also includes a location marker on the area of the ground, and a stored image showing at least a portion of the area of the recorded image. The on-board landing system is configured to obtain information from the location marker and use the information to align the recorded image with the stored image.

Abstract: An emergency flight plan useable for an aircraft provided with a navigation system wherein the flight plan includes a pointer matrix including a number of cells. Each cell of the matrix has a unique identification and each cell corresponds to a geographical area, and wherein each cell of the matrix includes an identification of a cell corresponding to a next waypoint in an emergency route.

Abstract: A system for detection of foreign objects on airport travel surfaces including a plurality of foreign object detector modules mounted on a corresponding plurality of existing aircraft travel surface lighting supports, the plurality of foreign object detector modules providing a corresponding plurality of detection outputs and a high speed detection output analyzer operative to receive at least one of the plurality of detection outputs and to provide a high speed output indication of foreign object presence.

Abstract: A distribution device for a glide guidance component, the distribution device including an array of antenna elements installed on a pylon. The distribution device includes: a first and a second input for receiving a CSB (carrier plus sideband) input signal and an SBO (sideband only) input signal respectively, a plurality of outputs connectable to the array and including a first and a second output for the first and second output signals, respectively; each of said output signals including a CSB component and an SBO component. The array of antenna elements is such as to irradiate an image-less type pattern and the distribution device is such that the outputs have an substantially equal amplitude value for each pair arranged symmetrically around a central point of the array and a phase difference which is identical for the two CSB and SBO components.

Abstract: An ultraviolet radiation emission unit includes a housing and an aperture located on the housing. A radiation source includes a light emitting diode configured to emit radiation having a wavelength within a range of about 240 nm and about 280 nm. A radiation reflector is disposed proximate to the radiation source and configured to direct the radiation emitted from the radiation source through the aperture in the housing.

Abstract: An ultraviolet radiation emission unit includes a housing and an aperture located on the housing. A radiation source includes a light emitting diode configured to emit radiation having a wavelength within a range of about 240 nm and about 280 nm. A radiation reflector is disposed proximate to the radiation source and configured to direct the radiation emitted from the radiation source through the aperture in the housing.

Abstract: This invention provides an improvement in the present instrument approach procedure used at airports having an ILS localizer without an accompanying UHF glide-slope. The field strength of the localizer, as measured at the airplane, is used as a basis for producing a glide-slope deviation signal. The shape of the resulting path may be adjusted by changing the input/output characteristic of a localizer receiver.

Abstract: A method, system, and apparatus, for providing audio feedback regarding the operation of an aircraft. In one aspect, microphones are placed next to sound sources, which could be components of the aircraft. Audio inputs are received from the microphone and analyzed based on a psycho-acoustic model to provide settings, such as level, pan, and equalization, to an automatic mixer. The automatic mixer mixes the sounds based on the settings and provides audio output to the pilot of the aircraft. The pilot can then use the audio output to more effectively monitor the operations of the aircraft components, which might otherwise be difficult or impossible to hear.

Abstract: The invention relates to devices for processing images making it possible to identify, to process and to select discrete light sources present in a video image composed of pixels. The aim is the presentation, in real time, to a user of a processed image allowing better recognition of light sources in a weakly contrasted image. In aeronautical use, this device affords a landing aid by allowing better recognition of runway lamps in conditions of degraded visibility, in particular in foggy weather. The invention relies on three major principles: 1) the main processing of images is performed only on a small number of pixels whose level is greater than a threshold; 2) a likelihood estimator evaluates the probability of existence of sources in the image; 3) the threshold is variable as a function of a certain number of parameters of the image.

Abstract: A runway lighting fixture of the type normally permanently installed at an aircraft installation such as an airport to provide visible light signals to an aircraft, the fixture having an internal, non-visible light source such as an infrared lamp capable of being activated to provide a non-visible light signal to an aircraft specially equipped to see such non-visible signals. An airport normally having arrays of permanent visibly-lighted fixtures can be equipped for long-term or permanent covert operations capability by installing covert, non-visibly-lighted fixtures in place of visibly-lighted fixtures. In a preferred form the covert fixtures are capable of being both visibly and non-visibly lighted to allow normal appearing non-covert operations at the airport, and unobtrusive covert operations whenever needed.

Abstract: An airfield guidance sign. The sign 100 (of FIG. 1a) includes a case (102), a multi-element light source (114) attached to the case (102) for providing light interior to the case (102), a light dispersion subsystem of the case for dispersing the light from the light source (114) substantially uniformly throughout the interior of the case (102); and a side panel (126) forming a side of the case (102) for displaying information.

Abstract: An acoustic signaling system comprises a transmitter, which has frequency stability to create sounds which can reliably be received and which is loud enough to be heard by a receiver. The receiver includes an electret microphone, a limiting amplifier which has high gain, high frequency roll off and produces a maximum output for any input above a minimum value and a Schmitt trigger circuit to square up the output of the limiting amplifier and function as a zero cross detector. A micro-controller measures the times of the zero crossings and performs the detection and decoding algorithms to determine what code is being received. Each code consists of an anonymous repeating sequence of tones, which are transmitted for a certain duration followed by a silence, which allows room echoes to decay. The system creates acoustic sound codes, which are pleasant, sounding, can reliably be received and convey sufficient information to activate toys or dolls.

Abstract: Device for determining the position of an aircraft (11) at an airport, includes a plurality of sensors (5) for detecting at least one radio signal originating from a vehicle (11), in which the plurality of sensors (5) are preferably positioned at regular intervals from one another on parts (2, 3) of the airport which are accessible to the vehicle (11). The present device is preferably used for detecting the position of an aircraft (11) on the runway system of an airport. The sensors (5) are preferably fitted in light positions of runway lighting provided at the airport on taxiways, take-off and landing runways (2, 3) and on plat-forms. The signal originating from a radio altimeter (12) of an aircraft (11) is preferably used as the radio signal.

Abstract: The invention refers to a method for the guidance of aircraft on the taxiways (R) of the airport apron with position lights (FE) located on the taxiways (R) and, possibly, other locations on the apron. It comprises the following steps: determination of the current aircraft position with a defined precision by means of a navigation system (NAV); position detection and measurement of the lights by means of a sensor (SEN) arranged on the aircraft, provision of reference information (REF) including the positions of the individual lights (FE), comparison of the path pursued by the navigation system (NAV) with the reference information (REF) and utilization of the detected lights (FE) as waypoints for the navigation system (NAV), and therefrom determination of the current aircraft position with a higher precision than that of the original position determination by the navigation system (NAV); generation of guidance information (FRG) based on the determined aircraft position.

Abstract: An audio system that may include a flight-worthy electronics package that connects into the airborne electronics of a passenger aircraft, and to that aircraft's passenger system. The audio system may provide passengers with a variety of audio information. The audio information may include a variety of information tailored to phases of the flight plan of the aircraft. Thus, during takeoff, the system may describe the flight plan of the aircraft, whereas during descent, the system may alternately describe the distance to destination and time to destination. Other information that may be described, as desired, may include ground speed, outside air temperature, altitude, time or distance to a point of interest, and points of interest of the area that the aircraft is flying over at any particular moment. The audio system may cause these sequences of descriptions to recite automatically as determined by the preprogramming of the system. Passengers may also be provided with audio destination information.

Abstract: FAA regulations mandate that a pilot must have sufficient visibility to see the airport, and then the runway before landing; and sufficient visibility to see a substantial portion of the runway before taking off. In adverse weather conditions when visibility is reduced flights are cancelled, delayed, and rerouted to land where visibility is adequate. Poor visibility is one of the major causes of air traffic fatalities. One aspect of this invention discloses a method of illuminating an aircraft landing location to facilitate identification and aircraft guidance thereto comprising the following steps: projecting a laser beam upwardly from the location so that an aircraft may be better able to target the landing location particularly in conditions of poor visibility.

Abstract: The present invention concerns a device for indicating the position of an aircraft (H) notably a helicopter (H) with respect to a beam (F).In accordance with the invention, said indicator includes fixed first means (6) indicating the position of said aircraft (H), movable second means (7) indicating the position of the beam (F) in a predefined direction with respect to said aircraft (H), and third means (8) indicating which way to steer the aircraft (H) in the predefined direction to capture the beam (F) to said third means (8) being activated only when the aircraft (H) has crossed the beam (F) completely and is outside it.

Abstract: A window-passage detection system has a ground system comprising: a first course generator (3) for generating a horizontal DDM (Differential Depth of Modulation) pattern for defining a horizontal width (25) of a virtual window frame by emitting a first carrier signal and a first side-band signal from a pair of first transmission antennae (6a and 6b), a second course generator (4) for generating a vertical DDM pattern for defining a vertical width (26) of the virtual window frame by emitting a second carrier signal and a second side-band signal from a pair of second transmission antennae (7a and 7b), and a third course generator (5) for generating a longitudinal DDM pattern for defining a longitudinal position (27) of the virtual window frame by emitting a third carrier signal and a third side-band signal from a pair of third transmission antenna (8a and 8b). Pairs of the first to the third transmission antennae (6a to 8b) generate three orthogonal polarization planes.

Abstract: A system for enhancing navigation or surveillance in low visibility conditions is realized by employing one or more ultraviolet radiation sources, a receiver which is capable of producing output signals from which a two dimensional image of the received radiation can be constructed, and a display device for displaying such image. In one preferred embodiment the ultraviolet radiation source is co-positioned with a critical marker such as a runway beacon or hazard beacon. The ultraviolet radiation emanates from the source, preferably modulated to form a repetitive, characteristic signal, propagates through the low visibility atmosphere, and received by the ultraviolet imaging receiver. In another preferred embodiment, an ultraviolet radiation source is placed at or near the ultraviolet imaging receiver, that is, onboard the same vehicle or at the same fixed location. One or more reflectors are co-positioned with the critical markers.

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: A light unit has a strobe operated flash tube and a non-strobe peripheral lamp immediately beneath the flash tube; a switch can turn the unit off, operate either light or enable the pilot of an aircraft to signal the light unit to operate the flash tube or to turn off the flash tube and operate the non-strobe peripheral lamp, by means of a radio receiver having a local oscillator midway between two standard distress frequencies. The light unit may have infrared or other color lenses. A ribbon assists establishing a pattern of light and/or colors to mark a landing site and indicate wind direction.

Abstract: A waveform generator suitable for use in the testing of instrument landing systems comprising: a first generator (1) for generating digitally a first waveform comprising the superposition of a second waveform (19) of a first frequency and a third waveform (21) of a second frequency; a second generator (3) for generating digitally a fourth waveform comprising the superposition of a fifth waveform (25 or 27) comprising a phase reversed version of one (19 or 21) of said second (19) and third (21) waveforms of the frequency of said one waveform (19 or 21) and a sixth waveform (23 or 29) in phase with and of the frequency of the other one (19 or 21) of said second (19) and third (21) waveforms; and a circuit (7) for combining said first and fourth waveforms thereby to produce a waveform suitable for said use.

Abstract: A method and apparatus for aiding a landing aircraft. Three differently-colored beams of laser light are produced and transmitted, one of the beams of laser light being transmitted in a plane containing the direction from which the aircraft is approaching. Another of the beams of light is transmitted on one side of the plane, and the third of the beams of light is transmit on the other side of the plane. The pilot of the aircraft can determine whether the aircraft is on the plane or to the one side or the other by the color of the light the pilot receives. If desired, at least one of the colored laser beams that is transmitted toward one side of the plane can be broken into a plurality of adjacent fan-shaped beams, the light in at least one of the fan-shaped beams being interrupted intermittently.

Abstract: A method and apparatus for monitoring moving vehicular traffic, especially adapted for the detailed profiling and counting of airport usage by aircraft employing Doppler radar and sound generated by target aircraft. A primary parabolic reflector operated in the Cassegrainian mode with respect to Doppler radar radiation, employed in combination with a hyperbolic sub-reflector constructed so that it will reflect the radar radiation but remain transparent to sound waves is used to propagate and receive radar radiation, and to receive sound waves emanating from a target aircraft. Sound waves emanating from the target are received by the parabolic reflector and directed toward the parabolic reflector's primary focus where they strike a microphone placed at the primary focus of such reflector. The signal from the microphone and the information from the Doppler radar unit are processed by a central processing unit to provide a variety of information relating to the target aircraft.

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 method and apparatus for monitoring moving vehicular traffic, especially adapted for the detailed profiling and counting of airport usage by aircraft employing Doppler radar and sound generated by target aircraft. A primary parabolic reflector operated in the Cassegrainian mode with respect to Doppler radar radiation, employed in combination with a hyperbolic sub-reflector constructed so that it will reflect the radar radiation but remain transparent to sound waves is used to propagate and receive radar radiation, and to receive sound waves emanating from a target aircraft. Sound waves emanating from the target are received by the parabolic reflector and directed toward the parabolic reflector's primary focus where they strike a microphone placed at the primary focus of such reflector. The signal from the microphone and the information from the Dopple radar unit are processed by a central processing unit to provide a variety of information relating to the aircraft.

Abstract: A piloting aid system for landing an aircraft in either normal or adverse weather conditions is disclosed. The system applies a laser scanning process for determining and correcting the aircraft's position with respect to the commanded landing trajectory and for determining the aircraft's speed, altitude, and distance from the runway. The system provides the possibility to direct the aircraft exactly towards the runway longitudinal axis and to level the aircraft exactly parallel to the runway plane all along the landing trajectory and, consequently, to effect a safe landing under visibility conditions which would otherwise prevent landing.

Abstract: A portable infrared landing site illumination system is provided for fixed ing and rotary wing aircraft having night vision capabilities as provided by the Army's second generation goggles (PVS-5) or the third generation goggles (ANVIS). The system employs special markers assembled from readily available disposable components and a simple above ground mounting stake. Also provided is a special laser illuminator which operates in several modes to assist all phases of the landing operation.

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.