Abstract: The invention relates to a method, a device and an item of equipment for filtering alarms originating from a windshear detection system embedded in an aircraft being able to emit an alarm. The aircraft has at least one sensor allowing the acquisition of a flight parameter. The device according to the invention includes: means (302), (402) for the calculation of the second derivative of the flight parameter, means (303), (403) for the calculation of the absolute value of the second derivative of the flight parameter, means (304), (404) for the comparison of the absolute value of the second derivative of the flight parameter with a threshold C1, means for evaluating whether the absolute value of the second derivative of the flight parameter exceeds the threshold C1 over a duration greater than a time threshold T, and means for suppressing the alarm originating from the windshear detection system (350), (450).

Abstract: A measurement system for an aircraft having the three-axis components of the airspeed of the aircraft, the three-axis components of the wind speed currently encountered by the aircraft, and the wind speed distribution ahead of the aircraft simultaneously in real time. It comprises a Doppler anemometer measuring the airflow speeds at a plurality of points separated by a prescribed distance in the beam irradiation direction that changes in a time series, and an inertial data measurement device measuring the movement information and positional information of the aircraft. Moreover, the display system of the aircraft includes the horizontal two-axis airspeed of the aircraft, the three-axis components of the wind speed currently encountered by the aircraft, and information on the wind speed distribution ahead of the aircraft are displayed simultaneously in real time.

Abstract: A method of detecting a windshear hazard on aircraft is disclosed. The method includes determining a first wind velocity of the aircraft at the location of the aircraft using a wind velocity detector. The method also includes determining a second wind velocity at a distance ahead of the aircraft using a forward-looking wind velocity detection system onboard the aircraft. Further, the method comprises determining the wind velocity gradient over the distance and determining whether windshear hazard exists for the aircraft.

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: A method and a system are recited for obtaining a true azimuth heading for correcting a coarse azimuth heading measured from an observation position to a specific selected target by operating a data acquisition system disposed at the observation position. In principle, data is acquired and measurements are taken to allow calculation of a calculated target, including error area limits. The calculated target surrounded by error area limits is presented as a search zone to an operator for searching, finding and indicating on a display, on which is superimposed at least one map, of the specific selected target. Once found, calculations of the true azimuth are performed, allowing the derivation of the true North. The method and a system are operative with a variety of maps, including digital terrain models and stellar maps.

Abstract: A circuit and method for predicting an intersection of a host aircraft flight path with the wake vortex of another aircraft.

Abstract: Systems, methods and computer program products for alerting a flight crew during landing that the tailwind exceeds acceptable limits. The system determines a base tailwind threshold speed for a candidate runway based on a performance constant associated with an aircraft and candidate runway information and determines present tailwind speed. If the tailwind speed is greater than the base tailwind threshold speed, a tailwind alert is generated. Also, the system determines if the aircraft is in a tailwind alerting mode based on configuration of the aircraft and activates tailwind alerting, if it is determined that the aircraft is in the tailwind alerting mode.

Abstract: A method for implementing a weather alarm in an outdoor computer includes defining atmospheric-pressure data repeatedly, defining altitude data repeatedly and essentially simultaneously with the atmospheric-pressure data, with the aid of a satellite positioning system, and converting both measured variables into the same measurement unit, either pressure or altitude. The difference between the converted variables is determined and is stored as a reference value, the difference between the converted variables is repeatedly monitored, and when the difference changes by more than a preset limit-value relative to the reference value, a weather alarm is given. Also an apparatus for performing the method.

Abstract: An Aviation Weather Awareness and Reporting Enhancements (AWARE) system provides situational awareness by effectively filtering, analyzing and visualizing aviation weather data and specific hazard alerts in preflight, in-cockpit and controller applications. The AWARE system includes a temporal-spatial databases that filters weather data and a Bayesian network that assesses specific hazards in the filtered weather data in the context of pilot preferences, aircraft properties and airport properties. The filtered weather data and hazard alerts are then displayed on a client.

Abstract: A system and a method for providing a continuous, semi-continuous and/or repetitive aural signal to an aircraft pilot indicative of a difference between a set value and an actual value for one or more flight characteristics of the aircraft.

Abstract: A flight situation presentation system displays a large majority of the information required for piloting an aircraft in an enhanced manner to reduce potential for misinterpretation and instances of piloting error. Approaches include visual integration of flight data indicators into various functional display areas and further visual integration of the various functional display areas. Visual integration includes creating a synergism amongst the flight data indicators being presented so that the indicators tend not to distract from each other, but rather help to reinforce each other in presenting fully representative flight situation information. Techniques for visual integration include placement of flight data indicators in certain positions on a display relative to one another based upon functional relationships between the operational parameters being monitored.

Abstract: A dynamic wake avoidance system utilizes aircraft and atmospheric parameters readily available in flight to model and predict airborne wake vortices in real time. A novel combination of algorithms allows for a relatively simple yet robust wake model to be constructed based on information extracted from a broadcast. The system predicts the location and movement of the wake based on the nominal wake model and correspondingly performs an uncertainty analysis on the wake model to determine a wake hazard zone (no fly zone), which comprises a plurality of “wake planes,” each moving independently from another. The system selectively adjusts dimensions of each wake plane to minimize spatial and temporal uncertainty, thereby ensuring that the actual wake is within the wake hazard zone. The predicted wake hazard zone is communicated in real time directly to a user via a realistic visual representation.

Abstract: A system (24) for detecting an air disturbance in front of an aircraft (10) has a controller (26) that is coupled to an image detector (40). Image detector (40) generates an image signal corresponding to heated air in front of the aircraft (10). The air in front of the aircraft (10) is heated by direct high energy beams such as microwave beams (16, 18) from a respective microwave antenna (12, 14). By monitoring the image, the presence of an air disturbance may be determined. Position adjusters (30, 32) may be used to adjust the position of the beams (16, 18) by controlling the position of antennas (12, 14). The position of the beam is preferably maintained a predetermined distance (d) in front of the aircraft (10) so that an evasive maneuver may be performed.

Abstract: A system and method for downlinking weather data, generated by existing weather and data sensors, to a ground station. The ground station utilizes data from multiple aircraft to form refined weather information, and uplinks the refined weather information to the aircraft. The refined weather information is stored at the aircraft and picture generating equipment, such as an existing onboard ground proximity terrain or weather radar picture and symbol generator, generates pictorial information depicting weather. The pictorial information is displayed, for example by an existing EFIS or weather radar display, in the form of polygons.

Abstract: An aerial sampler system includes an enclosure, a transfer system, and a measurement system. The enclosure is connected to an external surface of an aerial vehicle and receives atmospheric flow from the external surface of the aerial vehicle. The enclosure also directs at least some of the atmospheric flow into an aperture in the external surface. The transfer system transfers some of the atmospheric flow from the aperture to a measurement system. The measurement system is internal to the external surface of the aerial vehicle and measures atmospheric trace gases in the atmospheric flow.

Abstract: A circuit and method for predicting an intersection of a host aircraft flight path with the wake vortex of another aircraft.

Abstract: An alerting and/or notification system for operator(s) of a vehicle about conditions that affect the operation of the vehicle. The system collects information from one or more hazard warning systems, groups the warnings into different alert categories, and resolves conflicts between two or more hazard warnings within the same alert category to set a priority level. The prioritized alerts are presented to the operator, and associated detailed information also made available, in the form of graphical and/or textual messages on a display. Using two- or three-dimensional surround sound techniques, directional verbal and tonal aural cues also inform the operator(s) about the presence of threats and/or conditions. Visual displays and/or directional aural commands may be issued to dictate an evasive maneuver direction, if desired.

Abstract: Attitude, ground velocity, and acceleration inputs from an aircraft Inertial Navigation System (INS) and/or a Global Positioning System (GPS) instrument on board the aircraft, are used to estimate wind velocity relative to the aircraft and/or the ground in three dimensions. A wind velocity in the third dimension is assumed to be zero. In an exemplary embodiment of the invention, one or more of a) atmospheric density, b) speed of sound, c) air temperature, d) thrust of the aircraft, e) aerodynamic force coefficients of the aircraft, and f) mass of the aircraft, are used in conjunction with the inputs from the INS/GPS instrument(s) to estimate the wind velocity. Air temperature can be used, for example, together with an ambient air pressure and/or a known altitude of the aircraft to indicate an atmospheric density.

Abstract: A method and device for deriving and displaying advanced TCAS information.

Abstract: A dynamic wake avoidance system utilizes aircraft and atmospheric parameters readily available in flight to model and predict airborne wake vortices in real time. A novel combination of algorithms allows for a relatively simple yet robust wake model to be constructed based on information extracted from a broadcast. The system predicts the location and movement of the wake based on the nominal wake model and correspondingly performs an uncertainty analysis on the wake model to determine a wake hazard zone (no fly zone), which comprises a plurality of “wake planes,” each moving independently from another. The system selectively adjusts dimensions of each wake plane to minimize spatial and temporal uncertainty, thereby ensuring that the actual wake is within the wake hazard zone. The predicted wake hazard zone is communicated in real time directly to a user via a realistic visual representation.

Abstract: A display system having a display screen for graphical display of data, a graphics processor for receiving data from at least a terrain data base and data from a weather radar and for converting the received data into a single data stream to provide an input data stream to the display screen. The single display displays the weather data on one portion of the display screen and displays the terrain data on a second portion of the display screen. The weather data is displayed as a two-dimensional graphic and the terrain data is displayed as a three-dimensional graphic, thus providing a user with the necessary flight information while keeping processing resources to a reasonable level. The terrain data is displayed as an out the window display graphic, and the weather data and the terrain data displays are scaled such that the displays are dimensionally juxtaposed to allow rapid recognition of the data by a user of the display system.

Abstract: An aircraft guidance system uses radar imaging to verify airport and runway location and provide navigation updates. The system is applicable to flight operations in low visibility conditions.

Abstract: A system for detecting, identifying and docking aircraft using laser pulses to obtain a profile of an object in the distance initially scans the area in front of the gate until it locates and identifies an object. Once the identity of the object is known, the system tracks the object. The system also monitors an area of the apron near the object to detect obstacles such as ground service vehicles. The system also analyzes the laser pulses to determine whether they are reflected from a solid object or from fog or other condensation or precipitation to avoid misidentifying condensation or precipitation as a solid object.

Abstract: Providing traffic information by using operational data developed by a wireless communication network to generate traffic information. Location information from the network can be combined with computerized street maps to measure the time it takes to get from one geographic area to another. By aggregating and analyzing anonymous data from thousands of devices, the present invention is able to determine real-time and historical travel times and velocities between cities, intersections and along specific routes.

Abstract: Airspeed direct sensing transducer apparatus in a system where fast response gust sensors are aircraft wing mounted, each gust sensor mounted on opposite wing halves feeding the absolute value of low-pass filtered direct sensed airstream gust cross-component signals to a difference amplifier providing an electrical indication when one side of the aircraft “sees” disturbed or turbulent air as may be encountered when an aircraft trailing wake-vortex or similar hazardous atmospheric disturbance is approached. This enables the pilot to take evasive action to mitigate or avoid the turbulence disturbance, enhancing free flight aircraft operation.

Abstract: The invention is a method for displaying otherwise unseen atmospheric phenomenon using augmented reality (the mixing of real media with computer generated media). The method uses computer generated images to represent existing weather conditions and presents this data to the user by combining the computer generated images with the user's real environment. Computer generated images are used to represent such weather phenomenon as wake vortices, wind shear, and microbursts. These images are represented in such a way as to intuitively display relevant properties of the phenomenon to the system user, which increases the user's situational awareness and safety. The primary intended applications are for air traffic controllers and pilots to view these disturbances.

Abstract: Airspeed direct sensing transducer apparatus in a system where fast response gust sensors are aircraft wing mounted, each gust sensor mounted on opposite wing halves feeding the absolute value of low-pass filtered direct sensed airstream gust cross-component signals to a difference amplifier providing an electrical indication when one side of the aircraft “sees” disturbed or turbulent air as may be encountered when an aircraft trailing wake-vortex or similar hazardous atmospheric disturbance is approached. This enables the pilot to take evasive action to mitigate or avoid the turbulence disturbance, enhancing free flight aircraft operation.

Abstract: An aircraft guidance system uses radar imaging to verify airport and runway location and provide navigation updates. The system is applicable to flight operations in low visibility conditions.

Abstract: A method and apparatus for detecting in situ windshear on-board an aircraft that utilizes parameters provided by standard on-board Air Data, Flight Management, and Stall Detection Systems. No on-board accelerometers are required.

Abstract: A method for automatically providing weather advisories for an airport to pilots comprises monitoring weather conditions at the airport and then generating weather advisories in response to these weather conditions. The broadcast traffic on a common traffic advisory channel is also simultaneously monitored and then menus providing for selectable weather advisories and radio check options are broadcast to the pilots. The weather advisories or radio check can then be selected by the pilot by clicks of their transmit button. The time spacing between the menus is adaptively changed in response to traffic on the common traffic advisory frequency. Also, the length of the weather advisories is also changed in response to this traffic. The radio check option is provided automatically by first confirming selection of the radio check option and then allowing the broadcaster to broadcast a short message which is recorded by the system and then rebroadcast.

Abstract: A wake turbulence warning and caution system and method for a protected aircraft tracks and stores a trajectory of a wake trailing behind a nearby aircraft and adjusts the wake position for the effect of local wind velocity, and then calculates a distance and time to closure between the protected aircraft and the wake. A caution is annunciated aurally and/or on a navigation map display and/or on a primary flight display if the distance or time to closure is less than a first predetermined threshold, and a warning is annunciated if the distance or time to closure is less than a second predetermined threshold. The wake trajectory is calculated based on range, bearing, and altitude information about the nearby aircraft supplied by a Traffic Collision Avoidance System (TCAS) aboard the protected aircraft, and based on inertial position and attitude of the protected aircraft supplied by an inertial reference system (IRS).

Abstract: Disclosed is a method and means for qualifying, quantifying and reporting aircraft turbulence encounters. The preferred embodiment provides an indirect method of measuring turbulence based upon the implementation of the well known equation:V.sub.ground =V.sub.air +V.sub.wind.Qualification of the turbulence encounter is implemented with a filter and quantification of the turbulence encounter is implemented with analog to digital conversion. Thereafter, a transmitter broadcasts the occurrence of the turbulence encounter to remote receivers tuned to receive the transmission.

Abstract: A hazard alert device for aircraft prioritizes various alerts according to predefined criteria. The device enables more optional alerting of hazardous conditions than a system of separate independent and discrete devices.

Abstract: Two techniques for detecting vortices and their associated circulation are disclosed. The first is termed a closed path configuration, and the second is termed the dual path configuration. These techniques are useable for the detection of wake turbulence especially in the vicinity of airport runways, which results from wing tip vortices generated by aircraft during take-off and landing. The systems are similar in that they use ultrasonic measurement techniques to determine the circulation about defined areas. The circulation is reflective of the vorticity associated with trailing vortices, which are manifest within the area.

Abstract: A process for managing air speed of an aircraft in flight. The method includes a first step of determining a point on the flight path at which it is theoretically possible to comply with a required time constraint by following a pre-established speed profile. In a second step, a speed is computed and a fresh speed profile is determined. This is obtained by determining speed corrections segment-by-segment from the point up to the last modifiable segment. The speed change in each segment is restricted to a maximum value. The new speed is computed on the basis of the curve showing the flight time t as a function of the speed V. This curve is approximated by a curve satisfying an equation with three coefficients (C.sub.1, C.sub.2, C.sub.3):V=c.sub.1 /t+c.sub.2 /t.sup.2 +c.sub.3 /t.sup.3Compliance with time constraints are ensured by this method while meeting the requirements of the pilot and air traffic controllers.

Abstract: A system and method for downlinking weather data, generated by existing weather and data sensors, to a ground station. The ground station utilizes data from multiple aircraft to form refined weather information, and uplinks the refined weather information to the aircraft. The refined weather information is stored at the aircraft and picture generating equipment, such as an existing onboard ground proximity terrain picture and symbol generator, generates pictorial information depicting weather. The pictorial information is displayed, for example by an existing EFIS or weather radar display, in the form of polygons.

Abstract: A hazard alert device for aircraft prioritizes various alerts according to predefined criteria. The device enables more optional alerting of hazardous conditions than a system of separate independent and discrete devices.

Abstract: A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.

Abstract: A visual display format for a terrain situational awareness system comprising a horizontal terrain elevation view and a profile terrain elevation view of potential terrain hazards integrated onto a single display.

Abstract: A terrain advisory system for an aircraft (A) comprises a processor (11) which compares terrain information, accessed from a memory (13) according to data from a navigation system (12), with dynamic flight parameters from a monitor (14) for the aircraft. The processor (11) also generates a trajectory signal and a pull-up signal to indicate, on a display (15), current aircraft trajectory relative to a line constructed from notional pull-up trajectories for the aircraft which avoid a predetermined clearance height without exceeding a predetermined acceleration acting on the aircraft during a pull-up maneuver.

Abstract: An apparatus and method for measuring airflow past an aircraft by extending a probe (14) from the aircraft into the airflow with a retraction-extension mechanism (20) when a measurement is desired, and retracting the probe (14) when a measurement is not desired. In a low observable aircraft (12), the probe (14) can extend to measure angle of sideslip for flight in a slow speed regime, such as is experienced in vertical take-offs and landings, and can retract during normal wing borne flight to reduce the aircraft's radar signature.

Abstract: A wind shear detector provides an alert to the pilot of an aircraft upon the occurrence of a sustained low-level increasing performance shear if the shear occurs for a sufficiently long period of time, even if the shear is of a relatively low magnitude. An integrator is provided to integrate signals representative of low-level increasing performance shears and to provide the alert if the accumulated energy caused by the shear exceeds a predetermined level. The integrated low-level shear signal may be combined with currently occurring shear signals and the alert generated if the combination of current increasing performance shear signals and the integrated shear signal exceeds a predetermined level.

Abstract: A system and method for detecting and viewing aircraft hazardous incidents such as flying aircraft and meteorological phenomena which includes microbursts, thunderstorms, tornadoes, and the wake turbulence of aircraft. The aircraft hazardous incidents are positionally and horizontally displayed to the pilot on a display, that is located in the aircraft cockpit, in relation to the flight path of the aircraft. The timely displaying of any of the aircraft hazardous incidents permits the pilot to take evasive action to avoid a potentially dangerous incident.

Abstract: In a vehicular warning system for sensing the approach of severe weather, a pressure sensor generates a first signal representative of the barometric pressure. A computer, coupled to the pressure sensor through the electrical system of the vehicle, generates a second signal responsive to the first signal changing in a time series pattern correlated with a known time series pattern representative of a severe weather system. The computer is coupled through the electrical system of the vehicle to the horn and/or lights for generating warning signals responsive to receiving the second signal, but only when the vehicle is not in the operating mode.

Abstract: A detection system for use in an aircraft which is able to monitor atmospheric conditions ahead of the aircraft, generate an alarm signal if adverse atmospheric conditions exist ahead of the aircraft and generate information which indicates the position of the adverse conditions so the adverse conditions can be avoided. The system is able to detect the presence of volcanic ash cloud ahead of the aircraft and, if desired, can also be used to detect a high density of sulphur dioxide gas and/or clear air turbulence ahead of the aircraft. The system monitors infrared radiation received by the aircraft, generates intensity signals representative of at least one predetermined wavelength of the radiation and compares intensity signals with reference signals or intensity signals of another infrared wavelength.

Abstract: A sensor that transmits data in response to detecting turbulence. The sensor is located somewhere within an aircraft. A modification circuit is connected to the sensor. This modification circuit may include a threshold detector for passing on signals exceeding a selected threshold. Other functions provided by the modification circuit could include averaging of signals and determining whether a threshold has been exceeded more than once within a particular amount of time or how many times the threshold has been exceeded within a selected amount of time. An adjustment circuit adjusts the signal based on the characteristics of the aircraft. This adjustment circuit is employed to standardize the indication of turbulence in aircraft having different characteristics. For example, a large aircraft and a small aircraft would require different adjustments of the signal to produce a standard indication of turbulence.

Abstract: A wind shear detection and alert system, compensated for the calibrated airspeed of the aircraft to minimize nuisance wind shear alerts. The wind shear detection and alert system (10) determines a reference airspeed as a function of flap position, with respect to a minimum maneuver airspeed signal (60) provided by a stall warning computer on the aircraft. The reference airspeed is subtracted from a calibrated airspeed signal (76) that has been filtered to remove minor variations in the signal using a Laplace filter (68). The differential airspeed is further filtered by another Laplace filter (78), producing a filtered differential airspeed signal (70), which the system uses to determine a delta threshold (48) to be applied in compensation for the aircraft airspeed to a wind shear alert reference signal. As the filtered differential airspeed increases, the delta threshold signal increases the absolute level of the wind shear alert threshold, reducing the likelihood of unnecessary wind shear alerts.

Abstract: A method for automatically providing weather advisories for an airport to pilots comprises monitoring weather conditions at the airport and then generating weather advisories in response to these weather conditions. The broadcast traffic on a common traffic advisory channel is also simultaneously monitored and then menus providing for selectable weather advisories and radio check options are broadcast to the pilots. The weather advisories or radio check can then be selected by the pilot by clicks of their transmit button. The time spacing between the menus is adaptively changed in response to traffic on the common traffic advisory frequency. Also, the length of the weather advisories is also changed in response to this traffic. The radio check option is provided automatically by first confirming selection of the radio check option and then allowing the broadcaster to broadcast a short message which is recorded by the system and then rebroadcast.

Abstract: A wind shear detector provides an alert to the pilot of an aircraft upon the occurrence of a sustained low-level increasing performance shear if the shear occurs for a sufficiently long period of time, even if the shear is of a relatively low magnitude. An integrator is provided to integrate signals representative of low-level increasing performance shears and to provide the alert if the accumulated energy caused by the shear exceeds a predetermined level. The integrated low-level shear signal may be combined with currently occurring shear signals and the alert generated if the combination of current increasing performance shear signals and the integrated shear signal exceeds a predetermined level.

Abstract: A method for automatically providing weather advisories for an airport to pilots comprises monitoring weather conditions at the airport and then generating weather advisories in response to these weather conditions. The broadcast traffic on a common traffic advisory channel is also simultaneously monitored and then menus providing for selectable weather advisories and radio check options are broadcast to the pilots. The weather advisories or radio check can then be selected by the pilot by clicks of their transmit button. The time spacing between the menus is adaptively changed in response to traffic on the common traffic advisory frequency. Also, the length of the weather advisories is also changed in response to this traffic. The radio check option is provided automatically by first confirming selection of the radio check option and then allowing the broadcaster to broadcast a short message which is recorded by the system and then rebroadcast.