Abstract: A method and device to assist in the piloting of an aircraft in a landing phase may apply a maximum braking of the aircraft if there is a risk of longitudinal departure from a runway.

Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.

Abstract: A system for wirelessly controlling marker lights comprising a remote controller comprising a transmitter and one or more marker lights. Each of the marker lights comprise a receiver and processing means, and each of the marker lights have a configuration mode in which the processing means is adapted to cause the receiver to wirelessly receive data from the transmitter. This data comprises one or more group identifiers to assign one or more groups to the marker light. In addition, the processing means of each of the marker lights is adapted to cause the receiver to wirelessly receive one or more commands from the transmitter for controlling the operation of the marker light. The processing means is adapted to carry out the command when the commands comprise the same one or more group identifiers that correspond to the one or more groups to which the marker light was assigned.

Abstract: The invention pertains to optoelectronic devices for aiding the guidance and taxiing of aircraft, comprising a so-called head-up collimator allowing the presentation of information in the pilot's visual field. It applies notably to large-size civil aircraft of the Boeing 747 or Airbus A380 type. The optoelectronic device comprises means for calculating a deviation factor for the actual trajectory of said aircraft relative to a theoretical trajectory on said traffic way, means for generating symbols and at least one head-up collimator comprising means for displaying and superimposing said symbols on the outside landscape. The deviation factor is calculated on the basis of an angle (PÂ?G) and that the means for generating symbols generate a symbol representing said deviation factor, so as to be superimposed on said traffic way.

Abstract: A device and associated method for determining an airport runway state includes a device that determines a runway state and is placed on board an aircraft. The device collects measured deceleration data of the aircraft during taxiing of the aircraft on the runway. Then at least one runway state is estimated from the collected data, and the estimate is transmitted to another aircraft or to a broadcasting center during the other aircraft's runway approach.

Abstract: Disclosed is a device for aiding the piloting of an aircraft in an approach phase during landing. The device includes a guidance system for aiding guidance of the aircraft. Controllers can be actuated by the system during an initial phase in accordance with a first guidance mode and during a terminal phase in accordance with a second guidance mode. The transition between the first and second guidance modes can be achieved automatically by the guidance system.

Abstract: A flight control system for an aircraft is configured for receiving command signals representing commanded values of a location of a geospatial point and a radius about the geospatial point for defining a circular groundtrack. A sensor determines a geospatial location of the aircraft and provides a location signal representing the location of the aircraft. A controller for commanding flight control devices on the aircraft controls the flight of the aircraft and is configured to receive the command signals and the location signal. The controller uses the command signals and location signal to operate the flight control devices to control the flight of the aircraft for directing the aircraft generally toward a tangent point of the circular groundtrack and then maintaining a flight path along the circular groundtrack.

Abstract: A display system and method for an aircraft displays, in real-time, the protected airspace associated with a CTL maneuver. The system processes aircraft approach category data and determines the protected airspace based at least in part on the processed aircraft approach category. An image representative of the determined protected airspace is displayed on the aircraft flight deck display system.

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: In a method of dynamically guiding an aircraft the intended path of the aircraft may be broadcast along at least one of a runway and a taxiway. The broadcasted intended path of the aircraft along the at least one runway and taxiway may be received. The lighting characteristics of an airport lighting device along the at least one runway and taxiway may be dynamically changed to dynamically guide the aircraft along the broadcasted and received intended path of the at least one runway and taxiway.

Abstract: The invention relates to a method of managing the braking of an aircraft while taxiing on an airport, the method comprising, on the basis of characteristics for a sequence of movements of the aircraft along at least one given path to be followed by the aircraft on the airport, the step of deducing information concerning the braking to be performed so that the aircraft does indeed travel in application of said sequence of movements.

Abstract: A mobile helicopter landing pad comprises a platform with one or more elongate, concave guiding channels for aligning a helicopter on the landing pad by forcing the helicopter's skates into a specific alignment upon landing. The guiding channels may have laterally disposed rollers or else be made of slick material to allow the helicopter to slide towards the base of the guiding channel under the helicopter's own weight. Additional crosswise rollers at the bottom of the guiding channel(s) may be provided to allow the helicopter to be moved forward or backward after landing. A blade locking arm swings upward and secures the top rotor. The pad may include a foldable enclosure that protects the helicopter after landing, and an electronic guidance system that assists the pilot during landing by providing instructions to the pilot or visual indications of the prevailing wind direction and velocity, through illuminated signals on the platform.

Abstract: The present invention relates to an object oriented architecture that includes a plurality of host aircraft interface objects that enable a plurality of different host aircraft or variants to be attached or interfaced to an associated store, such as a targeting pod or a weapon system. The union of all aircraft hosts and variants are packaged and maintained as one executable capable of adapting to the predetermined suite of identified hosts and host variants. At least one or more interface objects provide a virtual translation layer which is dynamically determined and allocated during instantiation. Auto detection of the host aircraft/host aircraft variant provides the specific interface protocol by which the store can process and provide status via a predetermined signal format.

Abstract: A method and apparatus that generates a 4D flight plan that takes in account weather, metrological data, and safety of flight information for 360 degree horizontal layer at all relevant altitudes and times is disclosed. The method may include receiving a flight plan request from a user, the flight plan including user preferences, receiving meteorological information and safety-of-flight information based on the user's origin, destination and preferences, generating a 4D flight plan based on the meteorological information, safety-of-flight information, and user preferences, and outputting the 4D flight plan for the user.

Abstract: Systems and methods for improving pilot situational awareness in the airport vicinity. An example method determines if at least one of an aircraft or vehicle in a predefined vicinity of the airport is a conflict based on information about an installation aircraft, information received from the at least one aircraft or vehicle, and a predefined conflict envelope, when the installation aircraft is performing one of an approach to landing, a takeoff operation or a taxi operation at an airport. The method generates and outputs a conflict alert if the installation aircraft determines that the at least one aircraft or vehicle is a conflict. The method generates a clear-of-conflict advisory if the at least one aircraft or vehicle previously determined to be conflicting is determined to no longer be conflicting based on updated information received from the at least one aircraft or vehicle.

Abstract: Embodiments of the present invention provide methods, computer programs, and apparatus for adjusting a speed target of an aircraft. In particular, the adjustment of the speed target of the aircraft may allow that aircraft to maintain merging and spacing constraints with respect to a leading aircraft. According to one embodiment of the present invention, the speed target of an aircraft may be adjusted by obtaining a speed target, obtaining own ship track data for the aircraft, obtaining lead ship track data for a leading aircraft, and calculating a speed target adjustment based on the speed target, the own ship track data, the lead ship track data and merging and spacing constraints.

Abstract: A runway identification system including a weather radar system. The weather radar system includes a receiver. The receiver is configured to receive a runway characteristic signal from a transponder associated with a runway. The runway identification system determines a runway identification based on the runway characteristic signal.

Abstract: Rooftop cargo racks, otherwise simply known as roof-racks, provide an option for transporting cargo that does not use space inside a vehicle. However, despite the usefulness of roof-racks, once cargo is secured to a roof-rack on a vehicle there is the added potential for a collision between the cargo and some overhead obstruction—such as, for example only, a garage door, over-hanging sign, public parking structures, and tree branch. Previous collision avoidance systems that employ either ultrasonic acoustic or Doppler-based radar systems are poorly suited for detecting the potential of a collision between rooftop mounted cargo and an overhead obstruction. By contrast, aspects of the present invention provide systems and methods for reducing the risk of a collision between rooftop mounted cargo and overhead obstructions by providing a more suitable radar-based means for detecting overhead obstructions and warning drivers and, if present, passengers in vehicles when there is a risk of a collision.

Abstract: A preliminary guidance data is determined for the vehicle during an evaluation time window. A vision module collects vision data from a vision module during the evaluation time window. Vision guidance data is determined from the collected vision data. A vision quality estimator estimates vision quality data for at least one of the vision data and the vision guidance data during the evaluation time window. The vision quality data is based on a cross correlations and an r-squared value. An adjuster adjusts the preliminary guidance data to a revised guidance data based on the vision guidance data such that the revised guidance data is registered with or generally coextensive with the vision guidance data, if the vision quality data exceeds a minimum threshold.

Abstract: A navigation solution of a navigation system with a Terrain Navigation Module is determined by a procedure including determining a supported position solution and the relative covered path between two height measurements, ascertaining a quality of each active supported position from each active supported position by way of a first quality function, and creating a search area and predetermined positions for each position inside the search area and each relatively stored covered path. The procedure further includes ascertaining a quality of each relatively stored terrain height measurement, and a quality of each reference height, and determining the quality of the position support by a function of all minimum probabilities of all used positions in the search area and supporting the navigation solution ascertained in the Strap Down Module by the navigation filter with the aid of the determined position support and the determined quality of the position support.

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 routing tool is disclosed. In one embodiment, the method and system include receiving flight data and geographic data in the aircraft, and generating route data based on the flight data and the geographic data. The route data provides information about attainable landing areas for the aircraft.

Abstract: A wireless runway incursion system is disclosed. The wireless runway incursion system method may include a runway traffic management unit that manages aircraft traffic on and around an airport's runways, a plurality of wireless relay devices located between the runway access points and the runway traffic management unit that relay wireless signals to the runway traffic management unit, and a plurality of wireless runway incursion sensors that are located in proximity of at least one airport runway that detect metallic objects. If a metallic object is detected, the wireless runway incursion sensors that detect the metallic object send signals to the runway traffic management unit, the wireless signal being an indication that the metallic object is one of entering the runway and leaving the runway.

Abstract: A system for aiding the piloting of an aircraft during a runway approach includes an information source that provides information relating to the aircraft and its environment. A computation unit determines, with the aid of information provided by the information source, an energy reference profile having a trajectory reference profile and a speed reference profile that allows the aircraft to regain a stabilized approach trajectory, if it follows the reference profile. A monitor verifies that the aircraft is following the reference profile. An indicator supplies the pilot with piloting indications for piloting the aircraft so as to follow the reference profile.

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: The device relates to the signaling, to the pilot of a craft, of the risks that it incurs due to obstacles placed in its zone of deployment. This device determines, on the zone of deployment of the craft, the contours of several types of risk region as well as the contours of two lateral regions of tight deployment tied to the craft and produces alarms as a function of the types of zones at risk found in the lateral regions of tight deployment.

Abstract: An airborne processor is linked to a ground-based, vehicle based, or satellite-based supplier of approaching aircraft data and/or terrain data, including airfield structures. The processor also has access to the aircraft's state, e.g. position, speed, intended route, aircraft dimensional data, or the like. Algorithms within the processor calculate a zone of protection about the aircraft in light of aircraft type, turning radius, and other identifying data. The processor combines the present and estimated future positions of the aircraft with the approaching aircraft and/or airfield structure data, and creates an alert to the crew if a threat of a ground incursion is detected. The display provides a visual of the zone of protection about the aircraft, and approaching aircraft and/or airfield structure to draw the attention of the crew to the threat.

Abstract: The invention discloses differing embodiments of methods, aircraft, and apparatus for communicating the braking conditions of a runway. In one embodiment, braking information may be determined from a first aircraft which has landed on the runway. The braking information may be communicated to air traffic control and/or a second aircraft. Communication of the braking information may take place utilizing an Automatic Dependent Surveillance Broadcast system (ADS-B) and/or other type of automatic networking system.

Abstract: A pilot is maneuvering an aircraft on a ground surface, such as a runway or taxiway. On a cockpit display, the pilot sees a scaled aircraft symbol overlaying a moving map on a cockpit display. The aircraft symbol represents the aircraft, while the moving map represents the ground surface on which the aircraft is located. The aircraft symbol depicts its nose gear and main gear with respect to the ground surface. The nose gear on the aircraft symbol rotates based on tiller angle. The cockpit display also shows edge guidance lines that allow the pilot to line up the main gear, while providing a margin of safety. Predictive symbology also overlays the moving map to provide an indication of whether the aircraft can safely turn on the ground surface.

Abstract: An airfield series circuit includes a transfer relay having first and second sides, and a primary regulator operatively coupled to an airfield series loop of an airfield at the first side of the transfer relay. A standby regulator is operatively coupled to the airfield series circuit at the second side of the transfer relay. The transfer relay is movable between a primary mode of operation whereby the first side of the transfer relay closed directing lighting power to the airfield series loop from the primary regulator and the second side of the transfer relay open isolating the standby regulator from the airfield series circuit, and a standby mode of operating whereby the second side of the transfer relay closed directing lighting power to the airfield series loop from the standby regulator and the first side of the transfer relay open isolating the primary regulator from the airfield series circuit.

Abstract: The present invention relates to an object oriented architecture that includes a plurality of host aircraft interface objects that enable a plurality of different host aircraft or variants to be attached or interfaced to an associated store, such as a targeting pod or a weapon system. The union of all aircraft hosts and variants are packaged and maintained as one executable capable of adapting to the predetermined suite of identified hosts and host variants. At least one or more interface objects provide a virtual translation layer which is dynamically determined and allocated during instantiation. Auto detection of the host aircraft/host aircraft variant provides the specific interface protocol by which the store can process and provide status via a predetermined signal format.

Abstract: An instrument landing system (ILS) provides signals in space receivable by an aircraft in flight to identify, for example, a point in space at which to start an approach along a glide slope path to a touchdown point on a runway. Atmospheric, ground and other conditions may cause transmission anomalies, so that the ILS signals identify a point in space displaced from its intended position. Systems and methods employed in flight use GPS or other positional data to determine the current displacement of such point, as identified by received ILS signals, from its intended position consistent with ILS specifications. In addition to reception and use of ILS and GPS signals, data on geographic runway location and correct ILS signal in space parameters is used for reference purposes in determining signal in space position discrepancies, glide slope path angular discrepancies, or both.

Abstract: An airport safety system is disclosed, comprising surface movement radar for monitoring the movement of aircraft and land vehicles on an airport, said surface movement radar providing a signal input to a computer arranged to identify from the relative motions of aircraft and vehicles detected by the radar in accordance with a pre-programmed set of rules an aircraft at risk of collision. The computer is also programmed to cause transmission by radio of an audible alert signal when a risk is predicted, said radio transmission being at a standard aircraft communication frequency, such as the standard ground communication VHF radio channel. The alert signal can alternatively be transmitted by one of a plurality of message transmitting devices arranged at different locations adjacent to airport runways and taxiways, each message transmitting device comprising a radio transmitter connected to antenna means arranged to radiate a signal within a predetermined area at the location.

Abstract: The invention concerns a device (1) comprising means (7) for searching for elements of the airport which are displayed on a display field of a screen (9), means (10) for verifying, for each of said elements, whether it forms part of a first group for which a main anchoring point is located inside a label zone or of a second group for which the main anchoring point is located outside the label zone, means (13) for determining, for the elements of the second group, a secondary anchoring point located at an intersection between an axis of said element and the label zone, and means (15) for presenting on the screen (9) for each element a label comprising data concerning said element, the labels associated with the first group being located at the main point and those associated with the second group at the secondary anchoring zone.

Abstract: The information relates to a method of transmitting information between a communications management unit on board an aircraft and a ground air control system, characterized in that it comprises the following steps consisting, in respect of the communications management unit, in: a) detecting the reception of alerts originating from an onboard surveillance system, via a communication bus, b) when an alert is detected, shaping the information contained in the alert as a report according to a predetermined format, and dispatching this report to the ground system.

Abstract: A system and method for displaying a three-dimensional image of airspace includes a series of translucent, horizontal “pavers” that lie like stepping stones marking the selected flight path. In addition, the display includes a series of vertical rectangles—called “wickets”—which bracket the selected flight path. One or more of the wickets may include a graphical representation of the direction of the aircraft should be flying through the wicket. The system accommodates changes in course by generating a new flight path when instructed to do so. The new flight path is created in a way that assures continuous guidance for the pilot and sufficient time for the pilot to adjust to the new course. The display can include a compass rose which indicates the aircraft's present heading and direction of flight.

Abstract: A method, apparatus, and computer program product for detecting anomalies in a landing system. In one embodiment, a magnitude difference between a blended inertial deviation magnitude and a raw deviation magnitude is identified to form a magnitude difference. The magnitude difference is compared to a magnitude threshold. If the magnitude difference exceeds the magnitude threshold, an anomaly in the data is detected.

Abstract: A system for wirelessly controlling marker lights comprising a remote controller comprising a transmitter and one or more marker lights. Each of the marker lights comprise a receiver and processing means, and each of the marker lights have a configuration mode in which the processing means is adapted to cause the receiver to wirelessly receive data from the transmitter This data comprises one or more group identifiers to assign one or more groups to the marker light. In addition, the processing means of each of the marker lights is adapted to cause the receiver to wirelessly receive one or more commands from the transmitter for controlling the operation of the marker light. The processing means is adapted to carry out the command when the commands comprise the same one or more group identifiers that correspond to the one or more groups to which the marker light was assigned.

Abstract: Systems, methods, and computer-program products for communicating auditory alerts about runway hazards to aircraft. A conflict on at least one arrival runway is identified using information received from an existing conflict detection system. An auditory alert associated with the conflict is generated and then modulated onto a carrier frequency. The carrier frequency may be a 75 MHz marker beacon carrier frequency, and further, the carrier frequency may be slightly offset from the 75 MHz marker beacon carrier frequency. The modulated alert is transmitted to an aircraft approaching the arrival runway through a directional antenna, which receives the transmitted auditory alert through a marker beacon receiver without requiring additional flight deck equipment. The transmitted alert does not interfere with transmissions from both an outer marker beacon associated with the arrival runway and marker beacons associated with adjacent runways due to transmitted power levels and antenna directivity.

Abstract: An airfield lighting system including an interface device for driving a light emitting diode including an isolation and step down device, a rectifier, and output terminals is provided.

Abstract: The invention relates to a portable helicopter landing area and to the use method thereof. The inventive device comprises two cases (1, 2) which can be carried by the person on the ground (X) and which are intended to be disposed on the selected surface or area (H). Moreover, two units (A, B) can be removed from the aforementioned two cases respectively. The visual positioning unit (A) comprises: a light which produces four successive white flashes (7) and which is visible from a distance of at least forty kilometers by an aircraft pilot, and a high-frequency current generator unit.

Abstract: A destination runway selection method, system and apparatus for use with a Terrain Awareness and Warning System (“TAWS”). The method involves determining upon which of a number of candidate runways an aircraft is most likely to land so that appropriate Required Terrain Clearance (“RTC”) values and other alert thresholds may be referenced. According to a first aspect of the method, a destination airport is initially selected from among candidate airports. According to a second aspect of the method, a destination runway is selected from among the candidate runways at the destination airport. In one particular embodiment of the invention, the candidate runway is selected solely on the basis of distance calculations between the runway and the aircraft.

Abstract: A navigation apparatus with image recognition, includes: an imaging section for obtaining a stereo image of a target spot; an inertial information detecting section for measuring an attitude angle of a body and an acceleration of the body; an image process calculating section for calculating a relative position of the body with respect to the target spot based on the stereo image and the attitude angle; and a navigation calculating section for calculating navigation information based on the attitude angle, the acceleration and the relative position.

Abstract: A method, computer program product and apparatus for locating aircraft with respect to airport runways, generating and annunciating imminent landing situational awareness advisories as a function of aircraft height above runway.

Abstract: There is provided a head-up display (HUD) tray harmonization assembly, including a mount alignment jig (MAJ) having a first end and a second end, the first end being connectable to an adjustable tray affixed in an aircraft front cabin at spaced-apart relationship to a front window having a lower edge located adjacent the front end of the aircraft, a telescope connected to the MAJ at, or adjacent, its second end oriented for viewing through the window, a collimator holder having a first portion connectable to the outside wall of the front edge of the aircraft and a second portion extending towards and terminating at least at the lower edge of the window, and a collimator coupled to the second portion of the holder to form a line of sight with said telescope. A method for HUD tray harmonization is also provided.

Abstract: Method and system for monitoring and comparing, in real time, performance of an aircraft during an approach to touchdown along a conventional approach path and along a contemplated modified approach path to touchdown. In a first procedure, a flight parameter value at a selected location is compared and displayed, for the planned path and for the modified path. In a second procedure, flight parameter values FP(tn) at a sequence {tn}n of measurement times is compared and displayed, for the planned path and for a contemplated or presently-executed modified path. If the flight parameter for the planned path and for the modified path differ too much from each other, the pilot in command has an option of terminating the approach along the modified path.

Abstract: A method and device for determines a safe altitude for an aircraft. The device includes a unit that determines a clear zone corresponding to a lateral area dependent on the flight of the aircraft. A unit determines the highest altitude of the ground that is located under this clear zone. A unit determines a safe altitude, by calculating the sum of the aformentioned highest altitude and a guard height.

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 timer usable in navigating and piloting an aircraft, the timer having a plurality of application modes for management of time and numeric data, including an approach mode, a fuel mode, a chronograph mode and a clock mode. Each application mode can drive independent but simultaneous time count sequences for use in flight management and navigation such as counting down approach times, fuel-tank switching intervals and other time sensitive events, as well as providing military time, standard time and UTC time.

Abstract: Methods and apparatus are provided for interactively building flight paths for entry into an aircraft flight management system (FMS). The apparatus comprises a database containing map information, a display for presenting the map information, a user controlled cursor and selection buttons, all under the control of a graphics processor. The processor presents the map information with included navigation features on the display, correlated with the aircraft position and cursor location. When the cursor overlies a navigational feature (airways, waypoints, etc.), the processor highlights the feature. Feature ID information may also pop up when the feature is highlighted. Using a mouse button or equivalent, the user selects the highlighted feature or ID, whereupon the processor sends the information associated therewith to the FMS. By successively highlighting and selecting features or IDs an entire flight path can be identified and entered automatically into the FMS without the need for individual text entry.