Abstract: A fire detection system for an aircraft, freight transportation vehicle or freight storage facility comprises one or more RFID tags associated with one or more items of freight being transported or stored. The RFID tag is configured to detect a condition indicative of a fire in or in the vicinity the item of freight, for example a temperature rise or generation of smoke. One or more RFID readers are arranged to read the RFID tags. The RFID reader is connected to or forms part of a control system, the RFID reader or the control determining whether the RFID tag has detected a fire.

Abstract: The present invention provides an alert interactive system designed to serve as an alertness tool to ensure that a person, such as an aircraft pilot, a car or truck driver, a soldier or sailor on watch, or a security professional, remains alert. The alert interactive system provides instructions and time for the person to enter a code, and provides an alert to that person and others when the code is not entered timely and correctly. The present invention indicates when the person is not alert, and may be taking a nap, may be fully asleep, or unconsciousness.

Abstract: Embodiments of the present invention relate to avionics systems, and more particularly, to collision avoidance systems. In one embodiment, a system is delineated comprising a plurality of detection zones for a plurality of aircraft and means for issuing a report based on one or more of the plurality of detection zones.

Abstract: Systems and methods for alerting a flight crew when the vertical situation display may be providing incomplete information due to the presence of a non-computed trajectory segment in the flight plan. A processing device in signal communication with a flight management system, a position measuring system, and a velocity measuring system receives a flight plan from the flight management system and determines if the flight plan includes any non-computed trajectory segments. If at least one of time or distance to the beginning of a next non-computed trajectory segment is less than a threshold value, the processing device generates an alert that information displayed on a vertical situation display may be incomplete. An output device outputs the generated alert.

Abstract: A method for analyzing faults present on a platform includes the following steps: (a) providing a table of correspondence between a plurality of observable symptoms on the platform (10) and the fault modes capable of creating each observable symptom; (b) measuring the observable symptoms present on the platform (10); (c) establishing at least one family of faults, including determining a list of fault modes capable of creating, alone or in combination, all of the selected present symptoms, placing each given fault mode of the group in a fault family, and grouping all of the fault modes capable of creating at least one selected present symptom shared with the given fault mode together in the same fault family as the given fault mode. The method is applicable to fault analyses on aircrafts.

Abstract: A system is provided for monitoring an energy height of an aircraft during landing. The system includes a database including landing distance data; a processing unit configured to receive the landing distance data from the database and to calculate a landing distance of the aircraft based on a velocity and a height of the aircraft, the processing unit further configured to provide display signals based on the landing distance; and a visual display coupled to the processing unit and configured to provide a visual image based on the display signals.

Abstract: An airline operations control system for an airline having multiple aircraft and multiple routes formed by one or more flights, which are implemented by the aircraft flying the flights forming the routes, where the airline operations control system includes a computer searchable database, a query module configured to query the database, and a prognostic module.

Abstract: The degree of urgency of a displayed object is promptly recognized in a control display system including: an information acquisition unit that acquires a target serving as an object of monitoring and attribute information of the target; a control condition storage unit that stores the attribute information of the target and a viewpoint control condition serving as information about a display mode of the target, the attribute information and the condition being associated with each other in advance; a viewpoint control unit that detects attribute information matching the attribute information of the acquired target from the control condition storage unit and that extracts the viewpoint control condition associated with the detected attribute information; and a display unit that displays a result obtained by carrying out viewpoint control of the target on the basis of the extracted viewpoint control condition.

Abstract: A flight display for an aircraft includes a virtual ice accretion meter having a liquid water content portion and an ice thickness portion. A method for determining ice accretion includes integrating over a time period a constant K multiplied by a liquid water content (LWC) and true airspeed (TAS).

Abstract: An exemplary embodiment relates to an aircraft system for detecting wires. The system includes a processor configured to actively sense a presence of a first object and a second object. The processor determines a location of the first object and the second object. The processor determines a potential location of a wire between the first object and the second object. The processor actively senses the wire by providing electromagnetic energy to the potential location.

Abstract: A method and apparatus are present for monitoring a runway. Data is received about the runway from a number of sensors associated with an aircraft while the aircraft performs an operation on the runway. A number of conditions are identified for the runway using the data received from the number of sensors.

Abstract: Methods and systems are provided for improving pilot situational awareness during brown-over-brown display situations. An image is rendered, on a display, that includes one of, or both, rendered terrain and rendered sky. A sky veil is at least selectively rendered on a portion of the display. The sky veil, when rendered, is rendered at least partially transparent and in a manner that portions of the sky veil that overlap with rendered sky are not discernable, and rendered terrain is viewable through portions of the sky veil that overlap with terrain.

Abstract: A termination system that transmits on a cyclic basis, from a control station to an unmanned vehicle, pairs of mutually dependent code and counter values whose dependency is determined by a termination algorithm. The vehicle has knowledge of the algorithm and can hence validate a received code/counter pair using the same algorithm. If the received code/counter pair is invalid, the vehicle can decide to self-terminate. The control station includes a termination actuator that allows the vehicle to be remotely terminated by invalidating, when actuated by an operator, the code/counter pairs that are transmitted to the vehicle.

Abstract: A method for indicating readiness of a predictive windshear system on an aircraft is provided. The method includes determining whether a windshear system is in a ready state and providing a first output that causes an indication of the ready state, the ready state being responsive to the windshear system being ready to detect a windshear event. Determining whether the windshear system is in the ready state includes comparing a first time until a first parameter reaches a first value with a second time for initialization of the windshear system and determining that the windshear system is ready to detect the windshear event in response to the first time being greater than the second time.

Abstract: Systems and methods for aircraft cabin noise analysis are disclosed. In one embodiment, a computer based system to monitor vehicle conditions comprises a trigger table stored in a tangible computer readable memory which stores at least one set of logic conditions which may trigger directive to analyze if alert conditions exist. The system further comprises a trigger processor to receive one or more data streams comprising vehicle condition data for a monitored vehicle and transmit the directive to analyze alert logic to an alert evaluation queue when the vehicle condition data satisfies the at least one set of logic conditions in the trigger table, and an alert evaluation processor to execute a stand-alone program to analyze vehicle data and generate an alert when the vehicle condition data satisfies the at least one set of alert conditions. In some embodiments, the system may be implemented in a computing system or as logic instructions recorded on a computer readable medium.

Abstract: A system and method for indicating a predictive windshear transmission status is provided. The method includes determining if the predictive windshear radar system is transmitting. The method also includes providing an indication of the determination to a user interface device. Additional parameters, such as the operational state of the aircraft, may be used to further define when the indication is provided.

Abstract: Methods and systems for detecting icing or incipient icing conditions external to a vehicle (100) are disclosed. An apparatus in accordance with one embodiment of the invention includes a temperature sensor (120) configured to direct a first signal corresponding to a temperature of an airstream, and a water content sensor (130) configured to direct a second signal corresponding to a water content of the airstream. A processing unit (140) can receive the first and second signals and, based on at least the first and second signals, provide an indication (150) when at least the first and second signals taken together correspond to an at least incipient icing condition. Accordingly, the system can be installed on aircraft to provide notice to the crew of incipient or existing icing conditions.

Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.

Abstract: A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

Abstract: Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision.

Abstract: A system and method is provided for adaptive control of at least one parameter of an auto guidance control algorithm for a vehicle. The parameters may be varied according to a previously established look up table, or automatically adapted through the use of control logic, such as a “fuzzy logic” algorithm. The control parameters that can be adaptively controlled include steered wheel turn rate, proportional valve current gain, line acquisition rate and/or auto guidance control valve current limits. The control algorithm responds to the vehicle's operating parameters such as vehicle speed, tracking error, predicted heading, and hydraulic oil temperature to make adjustments to the auto guidance control parameters.

Abstract: Methods and apparatus are provided for context sensitive notifications of incoming digital communications on an aircraft. The method comprises receiving a new datalink message from a sender on a device, the datalink message including a unique identifier associated with the sender, and determining if the sender is a new sender based on the unique identifier. The method comprises determining if the device is involved in an active exchange of datalink messages based on activity data associated with the device and outputting a first alert that the new datalink message has been received at an alert level below a current alert level if the sender is not a new sender and the device is engaged in the active exchange of datalink messages.

Abstract: A control system is provided that adopts a communication network using wireless visible light and IR light communications in a galley of an aircraft which is subjected to limitations of aviation regulations regarding wired communications. Insert equipments each having a visible light receiving element and an IR emitting element are disposed in a galley of an aircraft, and a galley controller is disposed within the galley or a circumference area thereof having a visible light emitting panel, an IR receiving element and a display/control panel for controlling the insert equipments. A mutual communication function between the galley controller and the insert equipments and a remote control function for controlling the insert equipments from the galley controller are realized via transmission and reception of visible light communication data and IR communication data.

Abstract: In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display

Abstract: Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.

Abstract: The invention relates to onboard failure warning management systems on aircraft, or flight warning systems (FWS). Traditionally, the logic of these systems refers to procedures to be executed by the crew in response to warnings. Modifications, however minor, to the procedures involve a new development that can be installed on the airplane computer only as part of a costly maintenance procedure, given notably the need to carry out exhaustive tests on the application. The invention introduces the concept of tasks defined by a set of variables, notably the warning and the procedure in which the task is executed, its category, its priority level and its status. Thus, the computer programs can be organized in modules that call the tasks to be executed, the parameters of said tasks being defined in a configuration table that can be updated as the procedures change during simple operation maintenance procedures.

Abstract: Aircraft system and method are provided for a first aircraft in an airport environment, the airport environment including a second aircraft. The system includes a sensor on the first aircraft configured to determine a temperature profile of engine exhaust from the second aircraft; and a processing unit coupled to the sensor and configured to construct a velocity profile of the engine exhaust from the second aircraft based on the temperature profile and to generate a warning for a pilot of the first aircraft based on the velocity profile.

Abstract: A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft.

Abstract: A vehicle-based threat detection system (10) for detecting weapons in a vehicle includes at least one sensor (12) in a cargo holding area of the vehicle. The sensor (12) is connected to at least one detector (14) that detects presence of a weapon in the cargo holding area. A warning system (16) is capable of communicating detection of a weapon to a location remote from the cargo holding area.

Abstract: The present invention relates to a system (1) and an associated method for managing audio warning messages in an aircraft. The system (1) comprises a plurality of monitoring systems (10, 20) capable of detecting the establishment of at least one warning condition (CA), and comprises a central broadcasting module (40), to which each of the monitoring systems is connected and which is capable of broadcasting an audio message (SIG) corresponding to a detected warning condition. In particular, in this system (1), the said central broadcasting module (40) comprises means (402, 420) for determining at least one priority warning condition among the warning conditions detected by the monitoring systems, and means (410, 430) for generating at least one audio message (SIG) corresponding to the at least one determined priority warning condition, in order to broadcast it.

Abstract: A cross-architecture flight tracking system helps an individual keep track of the status of an airline flight. A subscriber receives status updates intelligently and in real time based on the individual's accessibility over an instant messaging client. The system facilitates the status updates by maintaining and listing the flight as a contact in the individual's instant messaging client contact list, processing status updates from the airline, and dynamically passing the status updates to the subscriber through a channel that will successfully deliver the message.

Abstract: A system may include a sensor for coupling with a vehicle configured for atmospheric flight. The sensor may be configured for detecting a turbulence event, where the turbulence event is at least one of experienced by the vehicle or occurs proximal to the vehicle during atmospheric flight. The system may also include a transmitter coupled with the sensor. The transmitter may be configured for automatically remotely transmitting data regarding the turbulence event to a ground based entity.

Abstract: A present novel and non-trivial system, module, and method for presenting clearance-dependent advisory information in an aircraft is disclosed. Clearances include those corresponding to interval management operations and/or trajectory management operations. Data representative of clearance information including data representative of an actual controller intervention threshold (“CIT”) information, ownship information, target information, and alert parameter(s) information is received. The actual CIT information is comprised of the CIT of a clearance assigned to an aircraft and/or an designator from which the CIT of the assigned clearance is determined. A dynamic alerting threshold is determined as a function of the received information.

Abstract: A feathering, flapping and rotor loads indicator for use in a rotorcraft includes a calculation unit configured to calculate (a) a current temperature of a bearing of the rotor assembly using a first calculation model, (b) a projected temperature of the bearing using the first calculation model and (c) a load exerted on a selected component of the rotor assembly using a second calculation model, the first and second calculation models adapted to calculate, respectively, the projected and the current temperatures of the bearing and the load exerted on the selected component based on flight control parameters; and a display unit configured to display on a common scale a movable indicator, the movable indicator being driven by the highest value between the projected temperature of the bearing and the load exerted on the selected component. The display unit displays another movable indicator driven by the current temperature of the bearing.

Abstract: A data collection and distribution system for monitoring aircraft in flight, on the ground and at the gate or terminal for monitoring critical and catastrophic events, managing the emergency during such an event, and for investigating the event. The system generates, transmits and collects critical data generated by monitoring equipment onboard an aircraft or other commercial transport and selectively displays the data on a cockpit display console as well as for downloading, transmitting and displaying data at external monitoring and response stations, including fixed ground stations, roving ground stations and chase aircraft or vehicles. Digital surveillance information is collected, processed, dispatched, and log via remote control and access. The system includes a variety of system appliances such as surveillance cameras, sensors, detectors, and panic buttons and accommodates legacy equipment.

Abstract: The invention relates to an aircraft navigational aid system with 3D display including an anti-collision device, with means of storing data representing obstructions, means for calculating a representation of the obstructions in a three-dimensional space and a device for displaying the obstructions data in three dimensions. The system includes means for augmenting the display of the representation of the area of hazardous obstructions with at least two indicator objects for the said area of hazardous obstructions disposed together in such a manner as to form a third object targeting the localization of the point in the area of hazardous obstructions closest to the aircraft. The invention also relates to the method of display of the indicator objects in a three-dimensional display.

Abstract: A device calculates a first air speed representing an estimated air speed during flight using measurements of static pressure and total pressure onboard the aircraft. The device includes a storage device for storing in memory, in case of detection of a ground taxiing of the aircraft, the most recently determined value of static pressure corrected from induced aerodynamic effects. As a result, a second air speed representing the estimated air speed during the ground taxiing may be calculated by implementing a correction and using the most recently determined value of static pressure when the ground taxiing of the aircraft is detected. A method for automatically estimating an air speed of an aircraft is also provided.

Abstract: An airline operations control system for an airline having multiple aircraft and multiple routes formed by one or more flights where the airline operations control system includes a computer searchable database a query module configured to query the database and a prognostic module.

Abstract: Integrated surveillance systems and methods for processing multiple sensor inputs and determining a best route for avoiding multiple hazards. An example method performed on a first aircraft includes generating a plurality of routes for avoiding a previously determined alert from a first advisory system. Then, probability of success information is generated at other advisory systems for each of the plurality of routes. The best route of the plurality of routes is determined based on the generated probabilities and output to the flight crew or other aircraft. The probability of success information includes a previously defined uncertainty value. The uncertainty value corresponds to quality of data provided to or provided by the respective advisory system.

Abstract: A system for tactile presentation of information to a pilot of an aircraft. The system comprises a pilot seat, a plurality of tactors, and a controller configured to control the plurality of tactors to tactually present the threat information to the pilot by producing one or more tactile stimuli based on situational awareness information. The tactors in the plurality of tactors are physically coupled to the pilot seat and the threat information is indicative of a threat to the aircraft. In some embodiments, at least one pressure sensor may be physically coupled to the pilot seat and the plurality of tactors may be configured to tactually present the threat information to the pilot based at least in part on data obtained by the at least one pressure sensor.

Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.

Abstract: A method and system for aiding the taxiing of an aircraft on an airport domain enables automatic planning and execution of taxiing. The system includes a trajectory generating device for generating a taxiing trajectory of the aircraft on the airport domain, with the aid of a navigation data base, and piloting aiding devices that use the trajectory for aiding the taxiing of the aircraft. For example, the piloting aiding devices may include an automatic piloting/taxiing device and a display device.

Abstract: According to the invention, as a function of the altitude, the vertical speed and the heading of the aircraft, as well as of the deviation of the actual trajectory of the aircraft with respect to the automatic trajectory, a time interval (T) is determined, during which it is tolerable for said aircraft to be able to fly without any control command, both on the part of the stick (1) and on that of said automatic pilot (2) and an alert is emitted for the attention of the crew in the case where it is noted that the absences of manual piloting and of automatic piloting extend simultaneously over a duration at least equal to said tune interval (T).

Abstract: A method and a device for centralized management of warnings in an aircraft including a centralized system for management of warnings and a plurality of warning presentation interfaces. The method includes determining at least one warning in the centralized system according to at least one alarm activation signal received, presenting the at least one warning by a first interface of the plurality of warning presentation interfaces, filtering the at least one determined warning to determine whether to also present the at least one determined warning by a second interface of the plurality of warning presentation interfaces, the second interface being separate from the first interface, and presenting, by the second interface, the at least one determined warning, in response to a determination by the filtering that the at least one determined warning is to also be presented by the second interface.

Abstract: A system and method for a terrain awareness warning system. The system includes a radar system configured to transmit a first radio frequency wave and receive a second radio frequency wave and a display for receiving a display signal representative of a terrain and a terrain awareness warning system. The terrain awareness warning system includes a forward-looking terrain logic configured to be in communication with the radar system and to process a terrain signal from the radar system.

Abstract: A device for evaluation of the operational capabilities of an aircraft for informing a user about the capabilities of the aircraft to carry out a mission. Included are means for detecting malfunctions of aircraft equipment adapted for functioning during a mission. An evaluation device includes means for acquisition of information about the mission; a means for calculating observed feasibility level of the mission on the basis of at least one detected malfunction and the information obtained about the mission of the aircraft; and a means for presenting a synthetic reactive indicator, representative of the observed feasibility level of the mission in at least one instant of the mission. The means for acquisition, calculation and presentation are adapted for functioning during the mission, to inform the user about the observed feasibility level of the mission depending on the detection of new malfunctions and/or the modifications of the mission in course.

Abstract: There is described a method for generating a parameter for airfoil performance monitoring, the method comprising: receiving at least a first signal indicative of a first airflow parameter measured at one of an aft position and a side-facing position of a sensor mast mounted to an airfoil and at least a second signal indicative of a second airflow parameter measured at a fore position of the sensor mast; generating a turbulence intensity ratio for each one of the first airflow parameter and the second airflow parameter; and combining the turbulence intensity ratio of the first airflow parameter and the turbulence intensity ratio of the second airflow parameter to generate a combined turbulence intensity ratio for airfoil performance monitoring.

Abstract: The present invention allows quick detection of actual hazardous windshears while ignoring the effects of normal turbulence. A system according to one aspect of the present invention comprises a signal processor configured to determine a presence of hazardous windshear based on: (a) whether a measured windshear is beyond a first predetermined threshold, and (b) whether a measured turbulence level is beyond a second predetermined threshold.

Abstract: The present invention includes system and methods for managing information systems on an aircraft through the use of a remote management center. At the management center, the status information from aircraft computer systems is monitored for fault conditions. The management center then performs maintenance on the computer system when a fault condition is noticed. Exemplary systems include a remote management center that manages several different computer systems on several different manned aircraft. The management center connects to the aircraft and computer system through data links.

Abstract: The invention is embodied in the form of a flight simulator in the conditions of vortex danger and in conditions when a pilot is informed about the possibility to penetrate into said dangerous area of vortex sheddings produced by a vortex generator.