Abstract: A system and/or method is/are provided which reduces the likelihood of air vehicles being utilized by terrorists as weapons. In certain embodiments, when it is determined that the air vehicle is about to hit a designated structure (e.g., high-rise office building or apartment building, national monument, and/or government building), a controller automatically takes control of the air vehicle away from the pilot(s) and causes an automatic computerized pilot (auto-pilot) to take over control of the air vehicle and causes it to land at a selected airport and/or runway.

Abstract: The present invention provides several apparatus, methods, and computer program products for generating a terrain clearance floor envelope for use in a ground proximity warning system. In one embodiment, the present invention includes a processor that defines a terrain clearance floor envelope having at least two boundaries. In this embodiment, the processor defines at least one of the boundaries based on a runway position quality factor, an altitude data quality factor, and an aircraft position quality factor. Using these factors, the processor of the present invention can more precisely define the boundaries of the envelope about the selected runway. Further, the processor of the present invention does not unnecessarily increase the region between the envelope and runway where no ground proximity alarms are generated.

Abstract: An automated terrain awareness and avoidance system includes a transmitter located in a region to be protected from controlled flight into terrain accidents. The transmitter transmits an identification value to an aircraft. In response, a safety checking routine on the aircraft identifies a danger zone around the transmitter, and determines whether the aircraft has (or will) enter the danger zone. If the safety checking routine determines that the aircraft has (or will) enter the danger zone, the safety checking routine determines a safe route and engages the autopilot, which steers the aircraft along the safe route. The safety checking routine also causes a password to be transmitted to an air route traffic control center (ARTCC). The autopilot is disengaged if the safety checking routine determines the aircraft is no longer on course to enter the danger zone, or when the password, which must be received from the ARTCC, is entered.

Abstract: An aircraft surveillance system that includes an uninterruptible aircraft information broadcasting system (such as an ADS-B system) for transmitting flight information from an aircraft, and one or more ground stations for receiving the broadcast flight information. The flight information preferably includes the aircraft's aircraft ID, current three-dimensional position, and intended path. Optional components according to the invention include a system and method for validating messages received from the aircraft, and an alternative system and method for determining the aircraft's position if a primary navigation aid, such as GPS, is not available. In one embodiment of the invention, the system includes a transmitter and an uninterruptible power supply that are disposed within a secure housing within the aircraft. This serves to prevent passengers and crew members from disabling the system.

Abstract: An automated terrain awareness and avoidance system includes a transmitter located in a region to be protected from controlled flight into terrain accidents. The transmitter transmits an identification value to an aircraft. In response, a safety checking routine on the aircraft identifies a danger zone around the transmitter, and determines whether the aircraft has (or will) enter the danger zone. If the safety checking routine determines that the aircraft has (or will) enter the danger zone, the safety checking routine determines a safe route and engages the autopilot, which steers the aircraft along the safe route. The safety checking routine also causes a password to be transmitted to an air route traffic control center (ARTCC). The autopilot is disengaged if the safety checking routine determines the aircraft is no longer on course to enter the danger zone, or when the password, which must be received from the ARTCC, is entered.

Abstract: The AirSafety System supports the Department of Homeland Security, NTSB and FAA initiatives. Efforts to create an environment where accidents become ‘isolated occurrences’ are enhanced; and the opportunity for transportation to move forward is better attained. By way of advanced techniques, The AirSafety System gives governing entities the means to quickly determine each situation and respond accordingly. Communications are improved and the ability to control the aircraft is acquired.

Abstract: Flight plan information is provided in the form of a series of waypoints having attributes which preferably include, among others, latitude, longitude, altitude constraint, and waypoint identifier. A flight path, defined by this information is modeled, and the flight plan model is checked against terrain information to locate any instances in which a potentially unsafe flight altitude exists. In flight, the flight path model is updated using aircraft position so that the path from the aircraft position to the next waypoint is reflected in the model. In the event that a potentially unsafe flight altitude is detected, an alert may be issued to the flight crew. The crew may then amend the flight plan or take other appropriate action.

Abstract: A portable computer system allows a pilot to efficiently and effectively manage time-oriented and other flight-related tasks. The system preferably includes a microprocessor coupled to a display/input screen. The microprocessor, which includes or is coupled to a timer, preferably executes one or more application programs that are configured to receive information from and display information to the pilot. The application program is preferably hierarchically arranged and menu-driven for navigating among the various displays and thereby retrieving the desired information or initiating the desired functionality.

Abstract: An apparatus, method and computer program product for suppressing an alert generated by a terrain awareness system rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft.

Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: An integrated control and monitoring system for airport avionics is made single-point-of-failure impervious by continuously operating pairs of parallel-connected concentrators, Remote Master Workstations and Remote Slave Workstations, and a pair of independent LANs each connecting one of the concentrators of a pair to the Remote Workstations. Each concentrator of a concentrator pair, while in secondary status, monitors the operation of the concentrator in primary status, and whenever it observes a failure of communication will assume primary status and continue to allow ICMS to function in a normal manner. Likewise, another Remote Master Workstation automatically assumes Remote Master Workstation status if it fails to see an operational active master station on the network.

Abstract: A system, method, and computer program product for alerting an aircraft flight crew of an inconsistency during an instrument landing system (ILS) approach to a selected runway. The system includes a component configured to receive glideslope and localizer signals, and a component configured to determine aircraft approach angle to runway end. Also, a component configured to alert the aircraft flight crew of an approach inconsistency, if the determined aircraft approach angle to runway end is less than a threshold angular value and one or more parameters based on aircraft position and the received glideslope and localizer signals are met. The component configured to determine aircraft approach angle to runway end determines the aircraft approach angle to runway end based on aircraft geometric altitude, a vertical figure of merit, a horizontal figure of merit, runway elevation, and aircraft distance to runway threshold.

Abstract: A remote control signal, such as a signal from a GPS satellite, is received at a servant aircraft. If the remote control signal is valid, a processor on the servant aircraft prevents or inhibits anyone on the servant aircraft from controlling the flight or course of the servant aircraft. The remote control signal controls the flight and/or course of the servant aircraft. The remote control signal may come from an escort aircraft.

Abstract: A system for reducing nuisance alerts and warnings in a terrain awareness and warning system for an aircraft, including determining if the aircraft is within a predetermined geometric volume surrounding an airport. If the aircraft is within the geometric volume, then determining the aircraft's current projected flight path for a selected distance or time and comparing it with at least one approach volume extending from a runway at the airport towards an outer boundary of the geometric volume. If the aircraft's current projected flight path is such that the aircraft is expected to be within the approach volume and stay within the approach volume to the runway, then inhibiting selected alerts and warnings associated with non-threatening terrain.

Abstract: An apparatus, method and computer program product has a first terrain awareness mode and a second terrain awareness mode selectable by the pilot.

Abstract: A terrain avoidance system, method and computer program product for reducing nuisance alarms. The system includes a geometric altitude component, first and second vertical safety margin generators, and an alert component.

Abstract: An approach suppressed TAWS system and method for suppressing nuisance alarms based upon a determination that an aircraft is properly aligned for landing based upon location within a safe zone defined by a glideslope component and a localizer component.

Abstract: A device for providing a plurality of indications of a select pressure, said device including: an electronic interface having an input and an output; a resistive structure adapted to measure the select pressure and being electrically coupled to the input of the electronic interface; a first output for providing a signal indicative of the select pressure, the first output being electrically coupled to the output of the electronic interface; and, a comparator coupled to the output of the electronic interface and being adapted to provide a signal indicative of whether the select pressure is greater than a predetermined threshold.

Abstract: Methods and system for recording data from an aircraft and alerting with a wireless network are disclosed. The methods contain receiving signals containing data from a plurality of aircraft, determining normal thresholds for the data, monitoring and analyzing the data, and generating an alert signal if the data is beyond the thresholds with a ground based computer terminal in real time. The system includes a ground computer and other mechanisms for implementing the disclosed method.

Abstract: A parent unit is provided having: a precedent base for accumulating data from child units; an element data determination unit for processing the data into element data; an element data classification unit for creating a classification; an element data change classification unit for determining which classification the element data belongs to, and calculates transition probabilities among the classifications, and a display unit for displaying data. The child unit collects air current data, processes the data, obtains the transition probabilities, and calculates a probability of encountering air turbulence. The child unit then displays certain data when the probability of encountering air turbulence satisfies predetermined conditions.

Abstract: A system and method for intervention control of an aircraft in the event of pilot command error whether voluntary or involuntary. Impending detection of a chaotic condition associated with a maneuvering aircraft enable early prediction and control of the aircraft where solutions based upon performance prediction are available. A further feature of the present intervention control of the aircraft enables an equipment malfunction detection signal substitution of a satisfactory equipment signal.

Abstract: A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.

Abstract: An obstacle avoidance system, apparatus, and method is described suitable for use on autonomously guided or man-in-the-loop guided vehicles such as aircraft, missiles, cars, and other types of vehicles. The system provides guidance instructions in the situation where the vehicle encounters an obstacle either directly or indirectly in its path while traveling to a desired destination or where vehicles are traveling in formation. The system can be applied not only to obstacle avoidance but also to trajectory shaping by defining obstacles, operational boundaries and/or threats which influence the trajectory of the vehicle.

Abstract: A Terrain Following Apparatus for a vehicle such as an aircraft includes means (1) for effecting autonomous following of terrain by the vehicle, a control device (2), operable by a person operating the vehicle, to engage and disengage the means (1), a Terrain Referenced Navigation system (3) operable to provide navigation data for the vehicle, and validation means (4) for validating the integrity of the navigation data to provide when the integrity of the navigation data is validated for engagement of the autonomous Terrain Following means (1) by the device (2) and when the integrity of the navigation data is invalidated, for preventing operation of the means (1) when the control device (2) is operated.

Abstract: A method and system for detecting a failure or performance degradation in a dynamic system having sensors for measuring state variables and providing corresponding output signals in response to one or more system input signals are provided. The method includes calculating estimated gains of a filter and selecting an appropriate linear model for processing the output signals based on the input signals. The step of calculating utilizes one or more models of the dynamic system to obtain estimated signals. The method further includes calculating output error residuals based on the output signals and the estimated signals. The method also includes detecting one or more hypothesized failures or performance degradations of a component or subsystem of the dynamic system based on the error residuals.

Abstract: A human centered informational display is disclosed that can be used with vehicles (e.g. aircraft) and in other operational environments where rapid human centered comprehension of an operational environment is required. The informational display integrates all cockpit information into a single display in such a way that the pilot can clearly understand with a glance, his or her spatial orientation, flight performance, engine status and power management issues, radio aids, and the location of other air traffic, runways, weather, and terrain features. With OZ the information is presented as an integrated whole, the pilot instantaneously recognizes flight path deviations, and is instinctively drawn to the corrective maneuvers. Our laboratory studies indicate that OZ transfers to the pilot all of the integrated display information in less than 200 milliseconds. The reacquisition of scan can be accomplished just as quickly. Thus, the time constants for forming a mental model are near instantaneous.

Abstract: A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.

Abstract: An embedded terrain awareness warning system for aircraft being flown by a pilot includes a signal processing component, a protection component and a pilot vehicle interface. A method for providing an embedded terrain awareness warning system for aircraft being flown by a pilot includes providing a signal processing component, a protection component and a pilot vehicle interface. The signal processing component communicates with three-dimensional digital terrain elevation data and is able to take input data from aircraft sensors, aircraft computers or navigation systems and determine aircraft position and velocity. The protection component is in communication with the signal processing unit such that the protection component is able to determine if a potential controlled flight into terrain exists and is able to predict a recovery flight path to avoid terrain.

Abstract: A system and method for intervention control of an aircraft in the event of pilot command error whether voluntary or involuntary. Impending detection of a chaotic condition associated with a maneuvering aircraft enable early prediction and control of the aircraft where solutions based upon performance prediction are available. A further feature of the present intervention control of the aircraft enables an equipment malfunction detection signal substitution of a satisfactory equipment signal.

Abstract: A working memory contains a local altimetric map defining an altitude envelope of the terrain in the vicinity of the aircraft. A vertical limit path of the aircraft is established, on the basis of status indications and selected flight parameters, in the vertical surface containing the axis of its path. A first comparison is undertaken between this vertical limit path and the corresponding part of the altitude envelope, so as to determine a hazard of a vertical collision with the ground, and an alarm can be established according to the result of this first comparison. A lateral limit path of the aircraft on one side of the vertical of the flight path is also established on the basis of the status indications and selected parameters. A second comparison is made between this lateral limit path and the corresponding part of the altitude envelope.

Abstract: Embodiments of the invention provide a method and apparatus for indicating aircraft height relative to an obstruction in a terrain awareness warning system. The method includes receiving data indicative of geographic features of an obstruction, lateral distance of the geographic feature from an aircraft, height and flight path of the aircraft, calculating a projected height of the aircraft at the location of the obstruction using the data, generating a result signal, and displaying a colored indication on a display screen based on the result signal. The apparatus includes inputs for signals from instruments measuring height, flight path, and location of an aircraft, as well as an input for an instrument providing information about geographic features of terrain surrounding the aircraft. The apparatus includes a means for employing the signals to calculate an effective height of the aircraft relative to the terrain, and a screen display for graphically displaying the results of the calculation.

Abstract: A system for reducing nuisance alerts and warnings in a terrain awareness and warning system for an aircraft, including determining if the aircraft is within a predetermined geometric volume surrounding an airport. If the aircraft is within the geometric volume, then determining the aircraft's current projected flight path for a selected distance or time and comparing it with at least one approach volume extending from a runway at the airport towards an outer boundary of the geometric volume. If the aircraft's current projected flight path is such that the aircraft is expected to be within the approach volume and stay within the approach volume to the runway, then inhibiting selected alerts and warnings associated with non-threatening terrain.

Abstract: An apparatus, method and computer program product for suppressing an alert generated by a terrain awareness system rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft.

Abstract: In a steering device for a vehicle, the movement of a steering actuator driven by operation of an operating member is transmitted to vehicle wheels, in such a manner that the steering angle changes, without the operating member being coupled mechanically to the vehicle wheels. A first target yaw rate is calculated in accordance with the detected vehicle speed and a first steering angle set value, which corresponds to the detected amount of operation and vehicle speed. A second target yaw rate corresponding to the detected lateral acceleration and vehicle speed is calculated. A second steering angle set value, which corresponds to the difference between the detected yaw rate and a target yaw rate, as which the first target yaw rate or the second target yaw rate whichever has the smaller absolute value is taken, is calculated.

Abstract: A positioning and proximity warning method for vehicle includes the steps of outputting global positioning system signals to an integrated positioning/ground proximity warning system processor; outputting an inertial navigation solution to an integrated positioning/ground proximity warning processor; measuring air pressure, and computing barometric measurements which is output to the integrated positioning/ground proximity warning processor; measuring time delay between transmission and reception a radio signal from a terrain surface, and computing radio altitude measurement which is output to the integrated positioning/ground proximity warning processor; accessing a terrain database for obtaining current vehicle position and surrounding terrain height data which is output to the integrated positioning/ground proximity warning processor; and receiving the position, velocity and time information or said pseudorange and delta range measurements of said global positioning system, the inertial navigation solution

Abstract: A number of navigation functions are performed on terrain navigation space. One function is to define a dynamic dangerous zone based on flight altitude by locating and aggregating a set of nodes of terrain height over a minimum flight altitude. Algorithms such as collision check, mountainous area boundary and region growing techniques are developed as basic operations for this terrain model. In addition, a visibility graph approach for dynamic route selection may be adapted to reduce the real-time computational requirements. This approach reduces the size of the search space by establishing a partial visibility graph of terrain and avoids details of the terrain, which do not influence the choice of flight path, independent of the size of the navigation space. By exploiting the multiple and variable resolution properties of Oct-tree terrain models, a series of CFIT warning functions using terrain data as reference are implemented efficiently with existing on-board terrain data resources.

Abstract: The present invention provides several apparatus, methods, and computer program products for determining a look ahead distance value for use in a ground proximity warning system. Specifically, the present invention provides apparatus, methods, and computer program products that generate a candidate look ahead distance value that provides a constant reaction time for varying aircraft speeds. The apparatus of the present invention includes a processor that generates the constant reaction time look ahead distance by multiplying a desired reaction time by the speed of the aircraft. This constant reaction time look ahead distance value is compared by the processor to other candidate look ahead distance values that have variable reaction times for varying aircraft speeds. If the aircraft is traveling at a relatively high speed, the processor of the present invention selects the constant reaction time look ahead distance value for use in the ground proximity warning system.

Abstract: A system and method for intervention control of an aircraft in the event of pilot command error whether voluntary or involuntary. Impending detection of a chaotic condition associated with a maneuvering aircraft enable early prediction and control of the aircraft where solutions based upon performance prediction are available. A further feature of the present intervention control of the aircraft enables an equipment malfunction detection signal substitution of a satisfactory equipment signal.

Abstract: Improved methods and systems for detecting self-alerts from upload messages in a TIS system to thereby eliminate the likelihood of TIS self-alerts appearing on CDTI displays. The present invention determines whether a self-alert was present in a previous traffic information uplink to determine whether a target in a current information uplink is real. Using a weighting algorithm, typically a fuzzy logic algorithm, a system in accordance with the present invention can distinguish between targets in consecutive radar sweeps to identify self-alerts. If the self-alert was not present in previous uplinks, then the system removes the self-alert from subsequent views on the CDTI. Thus, the present invention provides an improved visual display system for pilots and air traffic controllers.

Abstract: A number of navigation functions are performed on terrain navigation space. One function is to define a dynamic dangerous zone based on flight altitude by locating and aggregating, a set of nodes of terrain height over a minimum flight altitude. Algorithms such as collision check, mountainous area boundary and region growing technique are developed as basic operations for this terrain model. In addition a visibility graph approach for dynamic route selection may adapted to reduce the real-time computational requirements. This approach reduces the size of the search space by establishing a partial visibility graph of terrain and avoids details of the terrain, which do not influence the choice of flight path, independent of the size of the navigation space. By exploiting the multiple and variable resolution properties of Oct-tree terrain models, a series of CFIT warning functions using terrain data as reference are implemented efficiently with existing-on-board terrain data resources.

Abstract: Sensor selection status monitoring and maintenance logic for generating messages relating to intermittent and “in-range” faults are described. In one embodiment, a transition count is generated indicating a number of times the selection status number changes during a flight. A time duration table is generated indicating an amount of time a selection status number is recorded in each of its possible states during the flight. The maintenance logic utilizes outputs from the monitoring logic to generate maintenance messages.

Abstract: An automatic lane following system for a vehicle is adapted to control the direction of a moving vehicle along a predetermined path. An associated controller estimates the vehicle's lateral position in relation to the lane markings (usually the white painted lines). An optical sub-system or a video camera or equivalent sensor is mounted on a vehicle and used to detect the lane markings. An actuator coupled to the steering mechanism is used to control the steering position of the front road wheels in response to a steering signal from a controller. An interruption switch is closed to enable the steering system actuator. An interruption switch actuator is displaceable between a rest or stored position in which the interruption switch is open and an operable position in which the interruption switch is closed.

Abstract: A system and method for controlling a robot (1), includes at least three setting devices (2, 3, 4) which can be extended or shortened in the longitudinal direction. Each setting device being directly or indirectly secured in a fixed frame (6) via a first joint (20, 30, 40) so that each setting device is pivotable in all directions in relation to the frame and that each setting device is attached at one end in a movable position head (8) via a second joint (21, 31, 41). Each sensor is provided with a length sensor (LS1, LS2, LS3), said sensors forming a part of control system (S1) for controlling the location (X, Y, Z), wherein the control system cooperates with a feedback control system (R2) arranged to correct the location (X, Y, Z) and feedback control system (R2) operate in accordance with different coordinate systems.

Abstract: A number of navigation functions are performed on terrain navigation space. A preferred embodiment of dynamic dangerous zone defined by flight altitude is demonstrated. In a preferred embodiment, a set of nodes of terrain height over a minimum flight altitude are located and aggregated. Algorithms such as collision check, mountainous area boundary and region growing technique are developed as basic operations for this terrain model. Yet another preferred embodiment with visibility graph approach for dynamic route selection has been adapted to reduce the real-time computational requirements. This approach reduces the size of the search space by establishing a partial visibility graph of terrain and avoids details of the terrain, which do not influence the choice of flight path, independent of the size of the navigation space.

Abstract: In order to provide the pilots with a display or a map of the terrain below the aircraft, a display is generated on a cockpit display, such as a weather radar, of the contours of the terrain below the aircraft. The terrain contour display is generated from aircraft position information, a terrain data base, and a terrain awareness envelope defined by awareness boundaries. Terrain contours are depicted with the highest terrain within the envelope colored red, high intermediate terrain contours in yellow with varying dot densities, low intermediate terrain contours in green with varying dot densities, and the lowest terrain in black. The green contours can be overwritten with a low density yellow based on a pre-caution envelope which extends certain of the awareness boundaries to provide notice to a pilot of upcoming cautions.

Abstract: An apparatus and method for automatically and independently determining aircraft altitude and alerting the pilot to deviations from a target altitude exceeding a specified tolerance. The alerter comprises an altitude sensing means for sensing the present altitude of the aircraft. The invention discloses three sources for altitude information namely, a self-contined sensor such as a pressure transducer, a Global Positioning System receive, or an altitude encoder. A target entry means is used for entering the target altitude. An indicating means signals an altitude alerting condition upon the detection of a condition wherein the absolute difference is larger than the tolerance value. The altitude alerting apparatus may also comprise a display means for display of the present aircraft altitude information.

Abstract: A traction control system of a vehicle having a device for calculating a target traction torque of each of a pair of driving wheels based upon operating conditions of the vehicle, a device for calculating a target slip ratio of each of the pair of driving wheels based upon the target traction torque calculated therefor, and a device for controlling the engine and the brake system such that actual slip ratio of each of the pair of driving wheels coincides with the target slip ratio calculated therefor according to a feedback control, with a partial feedforward control of the engine and the brake system based upon the target traction torque.

Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: Disclosed are avionics systems and methods of using the same to monitor a pitot-static system for blockages. A first aircraft movement rate is calculated as a function of a pressure sensed using the pitot-static system. A reference movement rate is calculated using an independent navigation system such as an inertial reference system, a global positioning system, or an attitude heading reference system. The calculated first aircraft movement rate is compared to the calculated reference movement rate to determine whether the calculated first aircraft movement rate falls within a predetermined tolerance range about the calculated reference movement rate. If the calculated first aircraft movement rate falls outside of the predetermined tolerance range about the calculated reference aircraft movement rate, it is determined that a blockage exists in at least one of a pitot tube or a static port of the pitot-static system.

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).