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: A turbulence data circuit for use in an aircraft. The aircraft can include 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 turbulence. The aircraft can further include a flight management system configured to determine a phase of flight, an aircraft inertial/air data system configured to determine an altitude and an airspeed. The turbulence data circuit can include an interface for coupling to the radar system, the display, the flight management system, and the aircraft inertial/air data system. The turbulence data circuit can be configured to determine the display signal representative of turbulence based on at least one of the phase of flight, the altitude, the airspeed and the second radio frequency wave.

Abstract: The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of operational objectives each of which is designed to achieve any particular command.

Abstract: The present invention includes an artificial horizon device including a sensor unit with a movable platform, at least one actuator linked to the platform, and one or more sensors located on the platform for sensing the position orientation of the platform relative to an external mass or the motion of the platform. The horizon device also includes a processing unit signally connected to the sensors and the at least one actuator. The processing unit is adapted to receive signals from the sensors and send signals to the actuators to move the platform to a horizontal orientation. The horizon device also includes either a display unit comprising an indicator of a horizon line which substantially corresponds to the horizontal orientation of the platform or a secondary device.

Abstract: A method of determining lubrication oil consumption in a gas turbine engine that has an engine operating cycle interval comprising a starting phase, a running phase and a shutdown phase, comprises the steps of: measuring lubrication oil level upon initialization of the starting phase of each engine operating cycle interval; comparing the starting phase measured lubrication oil level during the starting phase with a starting phase baseline lubrication measurement; recording the starting phase lubrication oil level measurement; determining average engine lubrication oil consumption rate during the complete engine operating cycle interval by dividing the difference between the starting phase lubrication oil measurement and the baseline lubrication oil measurement; and repeating these steps for each subsequent engine operating cycle interval; wherein the starting phase baseline lubrication oil level measurement is initially a predetermined lubrication oil level and then the previous starting phase lubrication oil

Abstract: The present disclosure is directed to systems and methods for providing attenuation alerts for a radar-based terrain warning. A method for providing radar-based terrain warning attenuation alerts may comprise: (a) receiving a radar return; (b) detecting a region of atmospheric disturbance limiting the range of the radar return; and (c) providing a notification of radar-based terrain awareness warning system attenuation in the region of atmospheric disturbance.

Abstract: A device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system includes a first unit for determining particular parameters concerning the aircraft, including the position of a power lever controlling the supply of fuel to the engine, and a second unit for determining, based on the particular parameters, whether the aircraft is in a state authorizing an action on the operating conditions of the engine and for issuing, as the case may be, a corresponding authorization signal.

Abstract: A multidimensional sensor data analyzer that includes: discretizing values in multidimensional sensor data at index locations in value surfaces that reside in a multidimensional value space; deriving surface components resulting from the intersection of a geometric beam shape function that describing the sensor beam with the value surfaces; determining minimum-maximum index location limits for the surface components; determining surface component index points by identifying the index locations that are located within the minimum-maximum index location limits for the surface components; and generating a beam value by performing a beam function using the values at the surface component index points.

Abstract: A navigation apparatus acquires weather information along a navigation route to a destination from an information center and calculates an importance that is assigned to the weather information based on a predetermined criterion as well as a determination mode and a travel purpose inputted from a user. The importance of the weather information may be calculated by employing an importance calculation table that defines importance of the weather information itself or the importance of the weather information relative to the navigation route. The importance of the weather information is used to extract a required part of the weather information for providing the user with the information. The weather information extraction may be performed according to a criterion such as extracting the weather information with a certain importance level or higher, extracting the weather information of top n th importance, or the like.

Abstract: A method for providing an enterprise with a situational awareness for conditions related to aircraft departure is described. The method includes receiving data related to one or more events that have the potential to affect conditions related to an aircraft's departure from a plurality of enterprise related systems, correlating the received data in accordance with one or more business rules, generating an aircraft departure situational awareness data set from the correlated data, processing the aircraft departure situational awareness data set in view of at least one user profile, and providing at least one recommendation, each recommendation associated with one user profile, directed to addressing the conditions related to aircraft departure.

Abstract: A method for inferring an altitude of a computing device, involving monitoring variable data associated with a plurality of variables measured within the computing device, inferring the altitude of the computing device using the measured plurality of variables in a multivariate correlation function, and controlling operation of the computing device based on the inferred altitude.

Abstract: An electronic flight bag for use aboard an aircraft during flight is disclosed. The electronic flight bag includes an electronic storage device which acts as a container for storing various user-configurable flight-related objects, such as flight routes as defined by way-points, airport information that includes approach routes, associated fight charts or other desired charts, temporary flight restrictions, and weather information as well as any other user-defined data objects associated with the flight. For example, the electronic flight bag may be used in corporate aircraft and may include one or more data objects that relate to the corporate policies with respect to flights. The data objects may also include time-sensitive data and contain time flags that can be updated by way of a communication link during flight. In accordance with an important aspect of the invention, the data objects are user-configurable so that a user can include virtually all information that is relevant to a particular flight.

Abstract: A method and device for determining the lateral path of a moving body determine, from a first lateral path and a lateral distance dependent on external visibility, a second lateral path corresponding to a lateral flight path that is followed by the moving body.

Abstract: A system and method of automatically advising an individual, in real-time, of all available facts related to a current situation. The method is facilitated by a system, which automatically retrieves data related to a situation from a plurality of aviation enterprise systems, processes the data retrieved in real time and generates a situational awareness data that is presented in an optimal format to a user on an interface device. Processing of the data retrieved from the plurality of aviation enterprise systems comprises correlating the data in accordance with business rules and interpreting the data in view of previously stored historical information that relates to the situation. The situational awareness data generated is further processed in view of a user profile in order to create a viewable situational awareness data that has been optimized for presentation to an identified user of the system in accordance with the user profile.

Abstract: A system includes an angular rate sensor disposed in a vehicle for providing angular rates of the vehicle, and an instrument disposed in the vehicle for providing line-of-sight control with respect to a line-of-sight reference. The instrument includes an integrator which is configured to integrate the angular rates of the vehicle to form non-compensated attitudes. Also included is a compensator coupled across the integrator, in a feed-forward loop, for receiving the angular rates of the vehicle and outputting compensated angular rates of the vehicle. A summer combines the non-compensated attitudes and the compensated angular rates of the to vehicle to form estimated vehicle attitudes for controlling the instrument with respect to the line-of-sight reference. The compensator is configured to provide error compensation to the instrument free-of any feedback loop that uses an error signal. The compensator may include a transfer function providing a fixed gain to the received angular rates of the vehicle.

Abstract: A method of processing altitude measurements for an aircraft is disclosed. The method involves filtering raw altimeter data within an altimeter to substantially limit random variations in the altitude measurements for one or more altimeter measurement profiles.

Abstract: In exemplary embodiments, braking of an airplane is controlled during a rejected takeoff. A rejected takeoff of an airplane from a runway is initiated. Position of the airplane is determined, such as by inputting aircraft position from a global positioning system. Distance remaining on the runway is determined. Deceleration to stop the aircraft in the determined distance remaining on the runway is calculated, and the calculated deceleration is provided to an autobraking system of the airplane. When the aircraft can not be stopped in the determined distance remaining on the runway, a predetermined deceleration that correlates to maximum braking may be provided to the aircraft's autobraking system. The calculated deceleration may be provided to the autobraking system until a pilot takes command of the aircraft's brakes or the aircraft has stopped.

Abstract: An inertial navigation system is provided. The system includes a sensor block, an outer shell that substantially surrounds the sensor block and a plurality of gas pads connected to the outer shell that float the sensor block in gas creating a near frictionless environment to allow the sensor block to rotate in all directions. Each of the plurality of gas pads is adapted to receive pressurized gas. The outer shell and the sensor block are separated by a gap created by the pressurized gas at each pad.

Abstract: A method for assisting in verifying the path of an aircraft comprising a step of computing a path by means of a flight management computer, based on lateral constraints originating from a navigation database, characterized in that it comprises a step consisting in assisting the pilot to verify that the computed path complies with the lateral constraints in order to improve safety.

Abstract: A multidimensional sensor data analyzer that includes: discretizing values in multidimensional sensor data at index locations in value surfaces that reside in a multidimensional value space; deriving surface components resulting from the intersection of a geometric beam shape function that describing the sensor beam with the value surfaces; determining minimum-maximum index location limits for the surface components; determining surface component index points by identifying the index locations that are located within the minimum-maximum index location limits for the surface components; and generating a beam value by performing a beam function using the values at the surface component index points.

Abstract: In distance maps used in order to facilitate the navigation of craft such as an aircraft, the distances estimated take into account obstacles to be circumvented but not the maneuverability of the craft. The adaptation route required by the craft in order to take the right direction is not taken into account so that certain distance estimates for accessible points located in the neighborhood of the craft are unrealistic. In order to make a distance map more realistic, it is proposed that an obstacle of concave shape associated with the craft be added behind the position of the craft, forcing the estimations of distances to be circumvented an area that is inaccessible to the craft for reasons of maneuverability.

Abstract: A method of providing heading awareness on a flight display is provided. The method comprises displaying a heading awareness symbology to indicate heading relative to track, and varying the prominence of the heading awareness symbology on a display element based on at least one sensed condition.

Abstract: A method and device for attenuating on an aircraft lateral effects engendered by a turbulence. The device (1) comprises means (2, 3, 5, 7, A1, A2) for calculating and applying a roll control order and a yaw control order making it possible to attenuate the lateral effects engendered on the aircraft by a turbulence.

Abstract: A method and device for detecting, on the ground, the obstruction of a pressure tap of a static pressure sensor of an aircraft. The device includes a pressure sensor that measures the pressure inside a probe and a heating system for heating the probe. When the heating system is activated, the sensor carries out a first measurement of a parameter dependent on the pressure inside the probe. After a predetermined duration from the activation of the heating system, the sensor carries out a second measurement of the parameter. A central processing unit calculates the difference between the first and second measurements and compares this difference to a predetermined value. A warning device emits a warning signal indicating the detection of an obstruction if the difference is greater than the predetermined value.

Abstract: The invention relates to a method for assisting the piloting of an aircraft in the vicinity of a landing or takeoff point, by: determining the locus of entry and/or exit points for a given approach and/or departure altitude that are not safe for reaching the landing and/or takeoff point; and presenting a diagram including said locus on a display device.

Abstract: An aircraft display system (100) for illustrating a suggested crab angle has a processor (104) adapted to receive data representative of a desired ground tract (214) and representative of a ground tract deviation, and is configured upon receipt of these data to supply a ground tract rendering display command. A display device (116) coupled to receive the ground tract image rendering display commands is operable to render an icon (222) representative of the desired aircraft heading to maintain the desired ground tract (214). The method of how to maneuver an aircraft to correct for crosswind includes determining (306) a difference between a current ground track (224) and a current heading (218), determining a desired heading to maintain the desired ground track (214) based on the difference, and rendering on a display an aircraft icon (222) that is representative of the desired heading.

Abstract: Multiple data and images are multiplexed and sequenced in order to minimize the recording and monitoring hardware required to process the images, providing a detailed record of an event, greatly enhancing event reconstruction efforts. The multi-media safety and surveillance system for aircraft incorporates a plurality of strategically spaced sensors including video imaging generators for monitoring critical components and critical areas of both the interior and the exterior of the aircraft. The captured data and images are recorded and may be transmitted to ground control stations for real time or near real time surveillance. The system includes a plurality of strategically located video image sensors such as, by way of example, analog and/or digital video cameras, a video data recorder (VDR) and a pilot display module (MCDU or MIDU). All data is in recorded in an IP format. The IP encoder may be an integral component of the VDR, or the data may be transmitted in an IP format from the data generator device.

Abstract: Methods and apparatus are provided controlling aircraft cabin pressure, and more specifically engine bleed air manifold pressure, during aircraft descent. An aircraft engine bleed air manifold control pressure setpoint is to either a descent pressure setpoint or a cruise pressure setpoint by determining a rotational speed of an aircraft engine component, determining a component speed setpoint value, and determining aircraft vertical speed. The engine bleed air manifold control pressure setpoint is set to the descent pressure setpoint if either the determined rotational speed of the aircraft engine component is below the component speed setpoint value or the aircraft vertical speed is less than a predetermined vertical speed value.

Abstract: One embodiment of the present invention is a method for automatically reducing the effect of a component of an external force that is laterally incident on a rotorcraft. A signal of the rotorcraft indicative of and proportional to the component is monitored. An absolute value of the signal and a preset high limit are compared. If the absolute value is greater than the preset high limit, manual heading control of the rotorcraft is disabled and the heading of the rotorcraft is adjusted with respect to the external force so as to decrease the lateral component of the external force experienced by the rotorcraft.

Abstract: A system for determining an acoustic signature of a device is disclosed that includes a computer processor operable to determine strength and location of shock wave sound signals based on propagation of sound waves generated by the device. The strength and location of the shock wave signals are modified due to dissipation and dispersion effects in a non-uniform atmosphere. The shock wave signals are separated into even and odd numbered signals, and oscillations in the signals are smoothed by averaging even and odd numbered shock signals.

Abstract: A method and system for assuring separation between an aircraft and potential flight hazards is provided. According to the method, an intended path of the aircraft is predicted. A potential hazard to the aircraft along the intended path is identified. A distance from the potential hazard that the aircraft is required to maintain is determined. An ability of the aircraft to maneuver to avoid the identified hazard and to remain further from the identified hazard than the distance is determined. A probability that the aircraft will not maintain the distance from the identified hazards is determined. A pilot of the aircraft is alerted if the probability is greater than a predetermined level.

Abstract: A method is disclosed for providing an indication that a vehicle has exceeded a safe driving speed. The speed and position of an obstacle are combined with a driver reaction time to arrive at a safe maximum speed. The driver reaction time is predicted based not only on generic values as in known systems, but also on at least one scaling factor which can be, for example, a scaling factor which penalises increased driving duration, or driver age, or experience, or weather conditions.

Abstract: A method of diagnosing a turbine engine includes the steps of acquiring engine operating parameters; calculating corresponding engine residual values; computing the mean and the standard deviation of each engine residual value; normalizing dynamically each engine residual value to yield normalized engine residuals; mapping, via a cluster technique mapping, the normalized engine residuals as input vectors into an engine condition space having clusters representing either normal vector engine conditions or faulty vector engine conditions; and identifying a closest cluster within the engine condition space to determine whether the engine under analysis is normal or faulty. A belief factor may be obtained as a function of the distances between the input vectors and specific clusters.

Abstract: An objective of the invention, focusing on these issues involved in the use of a small, hobby-type, unmanned helicopter, is to develop an autonomous control system comprising autonomous control systems for a small unmanned helicopter, to be mounted on said small unmanned helicopter; a servo pulse mixing/switching unit; a radio-controlled pulse generator; and autonomous control algorithms that are appropriate for the autonomous control of the aforementioned small unmanned helicopter, thereby providing an autonomous control system that provides autonomous control on the helicopter toward target values.

Abstract: Parameters having a correlation with a crowded condition of a road traveled by a vehicle are inputted to an ideal fuel consumption estimation model. This ideal fuel consumption estimation model estimates an ideal fuel consumption of vehicle based on the parameters. The ideal fuel consumption of vehicle estimated by the ideal fuel consumption estimation model is outputted to an output portion.

Abstract: The invention applies particularly to the method and device for displaying forecasts on the flight plan of an aircraft. The method according to the invention consists in representing the craft by a first symbol in its current position and by a second symbol in its future position, in modifying the position of the second symbol on the navigation plan in order to change it to a future position, in displaying on the viewing screen the first symbol and at the same time the second symbol representing the craft on the navigation plan in a future position and in displaying on the viewing screen the navigation data at the instant of the future position of the craft.

Abstract: Embodiments of the present invention automatically compensate control of an aircraft for an environmental condition, such as turbulence or wind shear. A sensor is configured to sense speed of air relative to an aircraft at a predetermined distance in front of the aircraft. A processor is coupled to receive the sensed speed of air from the sensor. The processor includes a first component configured to determine whether the speed of the air at the predetermined distance is indicative of an environmental condition, such as turbulence or wind shear. A second component is configured to automatically generate control signals for controlling the aircraft such that the environmental condition is automatically compensated by a time the aircraft enters the environmental condition.

Abstract: A vehicle satellite navigation system is provided for generating a standard height for a geographic location where the vehicle is located. The system may include a satellite receiver (100) that is capable of generating position data as a function of signals received from navigation satellites. The position data may include a longitude, a latitude, and a ellipsoidal height. The system may store undulation values for a geographic area in an undulation grid model (146) or in a digital map. The system may determine an approximate undulation value for the position, and calculate the standard height value for the position.

Abstract: A computationally efficient method and system of finding intersections of a three-dimensional path (e.g., an airpath) through a three-dimensional space (e.g., an airspace) partitioned into multiple volumes. In one embodiment, such a method includes determining whether a current point of a current segment of the path is included within one of the volumes, establishing such volume as a current volume, determining whether a boundary of the current volume is intersected by the current segment, setting the intersection point as an exit point of the path, adjusting the current point of the current segment to the exit point, identifying a volume adjacent to the current volume that includes the exit point, changing the current volume to the adjacent volume, and setting the current point of the current segment as an entry point of the path.

Abstract: Logic circuits and operations respond to received various control signals, including (1) data exchange commands directing the drive to read and/or write data to a media item mounted by the drive, and (2) robotic device management commands. The logic responds to incoming data exchange commands by reading and/or writing to the loaded media item. The processor responds to at least some robotic device management signals by forwarding them to a robotic media transport device. The processor withholds the data exchange commands from the robotic device, since they are only pertinent to operations of the drive itself. The robotic device may be configured to restrict host access to library components according to predefined logical partitions.

Abstract: A steering aid system for altitude and horizontal speed of an aircraft (4) includes: a measuring device (22) for delivering a measured signal based on the aircraft altitude and horizontal speed, a common predetermined reference value (26) for the aircraft altitude and horizontal speed, and elements (20) for slaving the signal to the reference value by pitch loop, the elements being adapted to vary automatically the pitch and/or propulsive performance of the lifting members to lock the measured signal to the reference value.

Abstract: In a combined GPS/altimeter device, the calibration and hence the accuracy of barometric altimeter measurements are enhanced with the aid of derived altitudes from a GPS. The device determines the need for calibration and perform the subsequent computations necessary to facilitate the calibration. Furthermore, the device determines a correction quantity that should be applied to barometric altitude readings, thereby allowing the device to be calibrated while in motion. Both of these features ultimately result in a more accurate determination of altitude.

Abstract: A method and computer program product for determining the roll rate gyro bias of an attitude and heading reference system from true air speed, heading rate and body accelerations using centripetal force equations.

Abstract: A method and apparatus for converting electronic display aeronautical chart data to aeronautical chart data that is tailored for an avionics display is disclosed. The method and apparatus received by a data processing unit, electronic display aeronautical chart data. The color palette of the electronic display aeronautical chart data is then remapped to improve viewability on the avionics quality display. Finally, signals representative of the remapped colors are sent to the avionics quality display.

Abstract: An image change detecting system may include an image processor cooperating with a geospatial scene model database for generating a reference geospatial image corresponding to the collected geospatial image, and a change detector cooperating with the image processor for detecting a change between the collected geospatial image and the reference geospatial image. The geospatial scene model database may include 3D scene model data, and the collected geospatial image and the reference geospatial image may each include respective 2D image data. The collected geospatial image may have at least one geospatial collection value associated therewith, and the image processor may generate the reference geospatial image based upon synthetically positioning a virtual geospatial image sensor within a geospatial scene model based upon the at least one geospatial collection value.

Abstract: This invention provide systems and methods for cockpit flight crew preflight planning and subsequent, systematic recall and execution of procedures, ground/inflight navigation, and communications using portable electronic data storage and display devices. A capability is provided within a portable electronic data storage and display device to replace and replicate the typical preflight planning methodology of the individual flight crew member to facilitate execution of a procedures, navigation and communications plan from preflight to postflight. A user may create a usable subset of the potentially thousands of available pages of data or data reference pages stored in the portable electronic data storage and display device, organizing the perhaps 100 or less individual pages of data, static or interactive, desired for a specific leg of the flight in order that required information is immediately available in an expected order of need.

Abstract: A smart airport automation system gathers and reinterprets a wide variety of aircraft and airport related data and information around unattended or non-towered airports. Data is gathered from many different types of sources, and in otherwise incompatible data formats. The smart airport automation system then decodes, assembles, fuses, and broadcasts structured information, in real-time, to aircraft pilots. The fused information is also useful to remotely located air traffic controllers who monitor non-towered airport operations. The system includes a data fusion and distribution computer that imports aircraft position and velocity, weather, and airport specific data. The data inputs are used to compute safe takeoff and landing sequences, and other airport advisory information for participating aircraft.

Abstract: A device performs oxygen flight planning calculations for estimating oxygen usage. The device includes a storage device, an input device for inputting a known flight parameter value into the storage device, and an output device for outputting the known flight parameter value input by the input device. A logic device is configured to control the storage device, the input device, the output device and provide to the output device a further flight parameter. A value of the further flight parameter is calculable by the logic device from the known flight parameter value previously input into the storage device. Upon the further flight parameter being selected by use of the input device, the logic device calculates the value of the further flight parameter and provides the value of the further flight parameter to the output device.

Abstract: It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself.

Abstract: A system and method are provided for the efficient entry and display of ground taxi routes on an electronic airport map display. The system may include a touchscreen entry device, a display device, a computer, a map database, a vehicle position sensor and a transmitter/receiver. The system may be configured to check the ground taxi entries to ensure that each successive segment is contiguous with the last or next segment, and any gaps or discontinuities in the displayed taxi instructions may be annunciated. An intelligent display of next possible segments may be incorporated into the system.