Abstract: The present invention is a method for detecting and isolating fault modes in a system having a model describing its behavior and regularly sampled measurements. The models are used to calculate past and present deviations from measurements that would result with no faults present, as well as with one or more potential fault modes present. Algorithms that calculate and store these deviations, along with memory of when said faults, if present, would have an effect on the said actual measurements, are used to detect when a fault is present. Related algorithms are used to exonerate false fault modes and finally to isolate the true fault mode. This invention is presented with application to detection and isolation of thruster faults for a thruster-controlled spacecraft. As a supporting aspect of the invention, a novel, effective, and efficient filtering method for estimating the derivative of a noisy signal is presented.

Abstract: An FMS flight management computer equipping an aerodyne, complies with a constraint, in particular an altitude constraint, of the flight plan (Dpv) at an imposed waypoint close to the position of the aerodyne at the moment of instigation of its automatic flight plan following function. It consists in validating, in advance, such a constraint by projecting itself into a near future by way of a forecast (Pt) of the displacement of the aerodyne taking account of the motion of the aerodyne during the transition between the instances of application of the flight presets prevailing before the instigation of the automatic following function and those newly provided by the FMS flight computer (30) during this instigation.

Abstract: The invention relates to a method for aiding the setting of the barometric altitude of an aircraft equipped with a means (11, 12) for determining the altitude not using the barometric pressure, determining with the aid of the means (11, 12) for determining the altitude an altitude (Zv, Zi, Zr, Zh) and its relative precision (Pzv, Pzr), comparing the determined altitude (Zv, Zi, Zr, Zh) with a barometric altitude measured aboard the aircraft, generating an alert when the discrepancy between the determined altitude (Zv, Zi, Zr, Zh) and the measured barometric altitude exceeds a predefined value and proposing a barometric altitude setting value.

Abstract: Method and device to assist in the piloting of an aircraft in a landing phase. The device (1) comprises means (12) for applying a maximum braking of the aircraft if there is a risk of longitudinal departure from a runway, on a landing.

Abstract: A method and device for ensuring the safety of a low-altitude flight of an aircraft is disclosed, wherein low-altitude flight is flight along a flight trajectory at low altitude, for example 500 feet, that allows an aircraft to follow as closely as possible the terrain being over-flown. To avoid collision with the terrain, a safety corridor, devoid of any obstacle, is determined which is delimited on either side of the lateral trajectory, and whose width depends on a global uncertainty, and the aircraft is guided along the flight trajectory, avoiding any exit of the aircraft from the safety corridor.

Abstract: The invention concerns a device (1) comprising means (5) having knowledge of the terrain profile, means (7) for determining effective values of particular flight parameters, checking means for (9) for verifying whether a flight path determined by means of said effective values is compatible with the terrain profile, and means (13) for emitting a warning signal in case of incompatibility, said checking means (9) including at least one element (15) for calculating a height variation due to an energy transfer and to a total slope variation generated by a speed reduction, during an evasive action, an element (16) determining an evasive course using said height variation, and an element (3) verifying whether the evasive course thus determined is compatible with the terrain profile.

Abstract: Method for dynamic control of the performance of an aircraft computed on the basis of a real aircraft data input file and a computation data input file, using a computerised flight manual running on a terminal equipped with a commercial operating system, which comprises the following steps: a step of computing the performance of the aircraft on the basis of said real aircraft data input file, and said computation data input file, and obtaining at least one first result file, a step of computing reference performances on the basis of a reference data input file, and obtaining at least one third result file, which step is performed in parallel with the previous step, a first step of comparing the at least one third result file with the at least one reference result file, so as to detect any malfunction of the operating system with the application of numerical margins tolerated on the results of the result files, a step of deleting the at least one first result file and sending an error message to the user if

Abstract: Method for detecting faults in a device comprising the steps of receiving a plurality of performance parameters, applying the plurality of performance parameters to a first model to produce a plurality of estimated performance parameters, applying the plurality of performance parameters to a second model to produce a plurality of estimated device parameters, computing a plurality of residuals from the plurality of estimated device parameters, computing a plurality of distance measuring from the plurality of residuals, detecting at least one parameter deviation using the plurality of residuals and the plurality of estimated performance parameters, and setting at least one detection flag if the detected at least one parameter deviation is persistent.

Abstract: A method and system are provided for generating a restricted area alert. As a vehicle nears geographic location(s) through which traffic is restricted, sensor(s) detect the geographic position of the vehicle, and compare that geographic position with information regarding known restricted areas. Upon actual or anticipated entry of the vehicle into the restricted area, an alert message will be generated, formatted and transmitted to the vehicle, and/or additional recipients.

Abstract: Systems and methods for automatically switching to a track view mode on a vertical view display. The system determines aircraft position relative to a leg of a flight plan and switches display mode for a navigation vertical display to track view mode, if the display mode is in a plan view mode and if the determined relative position is greater than a threshold distance.

Abstract: The invention concerns a device (1) comprising first means (3) for determining a threshold value depending at least on one low altitude flight path, which is followed by an aircraft, as well as on navigation errors, for guiding and calculating the flight path, second means (4) for measuring the current real height of the aircraft above the overflown ground during a low altitude flight along the flight path, third means (5) for comparing said current real height to the threshold value, and fourth means (8) for emitting a warning signal, if the current real height drops to or below the threshold value, as well as optionally fifth means (10) for controlling the aircraft so as to increase its altitude and bring it to a secure altitude, when the current real height drops below or to the threshold value.

Abstract: An aircraft performance degradation detection system may include information sources, a central unit connected to the information sources, and a warning device that is connected to the central unit. Using information received from the information sources, the central unit computes the current weight and drag of the aircraft and computes a theoretical drag based on the current weight. The current and theoretical drags are compared, and a determination is made regarding performance degradation based on the comparison.

Abstract: The completion of an electronic checklist is facilitated by the automated display of certain data while completing the checklist. The disclosed program presents an automated display of synoptic, navigational, or flight management data for each task in a checklist. For each task in a checklist, there may be certain data which would aid the pilot or other user to complete the checklist. Such data can be displayed contemporaneously with the checklist. After the completion of each task in the checklist, the contents of the display can be restored to the state the display was in before the checklist was started.

Abstract: Systems and methods for determining if an aircraft is approaching a atmospheric pressure at field elevation (QFE) airport and for alerting if any errors that might affect the production of an accurate altitude value. In an example method a global positioning system (GPS) altitude value is compared to a corrected barometric altitude, if an airport that the aircraft is proximate to (approaching) is a QFE airport. The field elevation of the proximate airport is added to the corrected barometric altitude to generate an adjusted barometric altitude, if the comparison between the GPS altitude and the corrected barometric altitude is greater than a predefined threshold. The adjusted barometric altitude is sent to relevant aircraft systems, such as an Enhanced Ground Proximity Warning System.

Abstract: A method of and a system for controlling personal air vehicle (PAV) traffic provides a take-off-and-landing zone, and a forward flight zone. The take-off-and-landing zone may be from the ground up to a first altitude. The forward flight zone may be from the first altitude up to a second altitude. A maximum airspeed is provided in the take-off-and-landing zone. Minimum and maximum airspeeds are provided in the forward flight zone. In the forward flight zone there is a single heading for each altitude. Any change in heading must be accompanied by a change in altitude.

Abstract: A spatial data search method, system and apparatus for identifying particular data of significance around a reference vector through the spatial data. The method involves determining a reference vector within a spatial region for which spatial data exists, loading a portion of the spatial data including the data around the reference vector into a memory buffer, and searching the spatial data in a prioritized order. The method, system and apparatus have particular utility in searching geographic data for a terrain awareness and warning system (“TAWS”) and display in an aircraft. Embodiments of the present invention provide advantages over existing sequential and radial search methods, significantly reducing the processing and calculations required and providing faster alerts to pilots.

Abstract: A system and procedures for controlling a brake status indicator for an aircraft having an electric brake system are disclosed. Electric activation and deactivation of the brake status indicator mimics that of legacy hydraulic brake systems. The control methodology obtains brake force data that indicates actual clamping force of the electric brake actuators, parking brake lever status data that indicates whether the parking brake lever is raised or lowered, and parking brake activation data that indicates whether the parking brake mechanisms are active or inactive. The individual indicator elements of the brake status indicator are independently and concurrently controlled using multiple processing modules/channels of the electric brake system.

Abstract: A system and procedures for setting a parking brake for an aircraft having an electric brake system are disclosed. Electric activation of a parking brake as described herein mimics the sequence of events that is performed to engage the parking brake of legacy hydraulic brake systems. The electric activation process obtains brake pedal deflection data and parking brake lever status data, and determines whether to set the parking brake mechanism based upon the received data. Once the electric brake actuators are set, the electric brake system engages a friction brake to hold the brake actuators in place without having to physically lock or latch the brake pedals in a depressed position.

Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Abstract: A vehicle having a first transponder circuit generating an over-the-air transmission signal and a reference signal is disclosed. The vehicle also has a receiver circuit that receives the over-the-air transmission signal. The vehicle also has an integrity-checking circuit receiving an integrity signal from the receiver circuit. The integrity signal is based on the over-the-air transmission signal received by the receiver. The integrity-checking circuit also receives the reference signal from the first transponder circuit. The integrity-checking circuit determines the integrity of the over-the-air transmission signal.

Abstract: A system and method for filtering various targets (such as ground vehicles, stationary objects, and aircraft) from display on a display screen within the cockpit of an “Own Ship” aircraft. The system and method withhold from display any non-exempt targets that have an altitude that is either: (1) greater than an upper-threshold altitude; or (2) less than a lower-threshold altitude. The upper-threshold altitude and the lower-threshold altitude may be set to user-specified, customized values as desired to accommodate current flying conditions. In addition, the system and method may also be configured to operate in a plurality of operating modes, each of which features a different upper threshold altitude/lower threshold altitude combination. The system and method are preferably configured to reset certain threshold altitudes to pre-defined default altitudes in response to the aircraft landing.

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 low-altitude flight guidance system for an aircraft including a warning generator that generates a warning based upon a predicted position. The system further including a first sensor system having a terrain database and a calculation module that determines a current position of the aircraft with respect to terrain stored in the terrain database and that determines a reference altitude hDB of the terrain at the current position. The system further includes a second sensor system and a module that determines a predetermined flight altitude difference ?hF at the predicted position and terrain data in a region U of the predicted position. Moreover, the system includes an altitude prediction module that predicts an altitude and forwards the predicted altitude to the warning generator. The warning is based upon the aircraft reaching, approaching, or exceeding a warning altitude limit, and the altitude prediction module determination for the predicted position is based upon a prediction set point.

Abstract: The invention relates to a method for automatic detection of turbulence by a second aircraft, by information exchange between the second aircraft and at least a first aircraft. The first aircraft has means for transmitting information and the second aircraft has means for receiving the information transmitted by the first aircraft. The method includes the identification of information about turbulence liable to be encountered by the second aircraft, by analyzing the information received from the first aircraft. An alarm is activated on the basis of the turbulence information.

Abstract: A portable communication device detects a current speed of travel of the portable communication device independent of any vehicle temporarily transporting the portable communication device. A speed based setting controller of the portable communication device compares the current speed to at least one threshold value set at the portable communication device. Responsive to the current speed exceeding the threshold value, the speed based setting controller automatically assigns a separate speed based setting to a current setting for each feature assigned to the threshold value, wherein each current setting for each feature designates the operability of that feature within the portable communication device, such that the current setting for each feature adjusts with a speed of travel as detected by the portable communication device.

Abstract: The invention concerns a method and a system for calculating a flight route between a first position and a second position. According to the method, the first position is chosen as the current position, and the following steps are then repeated until the second position is reached: a loss function is determined corresponding to each flight path in a set of flight paths that are predefined in relation to the current direction of flight; a flight path that yields the most advantageous value for the loss function is selected; a subsection from the current position and a predetermined number of positions forward are registered for the selected flight path, and the position at the end of the subsection is chosen as the new current position.

Abstract: A spatial data search method, system and apparatus for identifying particular data of significance around a reference vector through the spatial data. The method involves determining a reference vector within a spatial region for which spatial data exists, loading a portion of the spatial data including the data around the reference vector into a memory buffer, and searching the spatial data in a prioritized order. The method, system and apparatus have particular utility in searching geographic data for a terrain awareness and warning system (“TAWS”) and display in an aircraft. Embodiments of the present invention provide advantages over existing sequential and radial search methods, significantly reducing the processing and calculations required and providing faster alerts to pilots.

Abstract: A system and method for remotely enforcing operational protocols is provided. In a remote environment, such as that found with a police environment, voice recognition technology is used to determine the situation and invoke actions according to an appropriate protocol. Actions may be set to be mandatory or discretionary. A secure log is maintained of the actions undertaken. Actions include automatically retrieving data from a remote database, automatically communicating with another unit or headquarters, and automating devices used in the remote environment. Voice recognition technology also extracts data from the user's speech and builds variables used as parameters in performing the actions. Data is returned to the user in either audible or textual form and either played to the user on a speaker or displayed on a display device.

Abstract: A safe interactive navigation apparatus and method allows the crew of an aircraft to prepare and follow a safe flight plan without relying on instrument flying infrastructure. An aircraft navigation assistance method calculates a continuous, three-dimensional projected path on board the aircraft as a function of data related to the route and characteristics of the aircraft.

Abstract: Systems and methods for producing an advisory if barometric altitude transition setting needs adjusting in an aircraft. In one embodiment, the method determines transition altitude, receives an uncorrected altitude, compares the uncorrected altitude to the transition altitude and to corrected altitude, and outputs a barometric altitude transition setting advisory based on the comparison between the uncorrected altitude and the transition altitude. The comparison determines if the uncorrected altitude is greater than the determined transition altitude and the advisory is output if the uncorrected altitude is determined to be greater than the transition altitude and the uncorrected altitude differs from the corrected altitude by a threshold amount. A delay is provided between the comparison of the uncorrected altitude to the transition altitude and the comparison between the uncorrected altitude and the corrected altitude.

Abstract: An airborne windshear detection and warning system includes a pitot tube for detecting the airspeed of an aircraft and an angle of attack vane for detecting an aircraft's angle of attack. Signals are generated and fed to a signal processor for determining a relationship between the airspeed and the aircraft's angle of attack. A signal indicative of the aircraft's normal relationship plus or minus a preselected value is also input into the signal processor. Then when the actual relationship exceeds the normal value plus or minus the preselected value for a preselected period of time, a signal is generated by the signal processor and is an indication of a hazardous windshear. A warning is then given to the pilot to take immediate corrective action.

Abstract: The device comprises a means for measuring a dynamic temperature on the outside of the aircraft, a means for determining a static temperature around the aircraft, using said dynamic temperature, a means for determining, using said static temperature and a thermodynamic equation, a second temperature value corresponding to an estimated temperature at said destination altitude, a means for determining the difference between said first and second temperature values, and a means for emitting a warning signal when said difference is greater than a predetermined value.

Abstract: The invention relates to methods and devices for aircraft's safe operation and is embodied in the form of a method and system for informing a user, for example an aircraft crew and/or a flight controller, on the probable penetration of the aircraft into dangerous areas of the vortex shedding of vortex generators which are located near the aircraft at a forecast time when the aircraft passes through a simulated control plane situated at a preventive distance in the direction of motion of the aircraft, said distance being calculated on a basis of a sufficient forecast period so that the aircraft carries out a flight evasive manoeuvre.

Abstract: A method, computer software product, and system to generate altitude callouts according to proximity to a runway at an airport or heliport includes determining whether the helicopter is flying in proximity to the runway and automatically selecting an altitude threshold increment set based upon the determination. The threshold increment set including a plurality of altitude threshold values. A calculated terrain clearance value is calculated for each of the plurality of altitude threshold values. A suitable warning is automatically generated according to the comparison. Selecting an altitude threshold increment set includes selecting one of the group consisting of first altitude threshold increment set including a plurality of higher altitude threshold values and a second altitude increment set including the plurality of higher altitude threshold values and further including a plurality of lower altitude threshold values.

Abstract: An improved system and method for eliminating terrain color confusion in aircraft displays are disclosed. An aircraft display system is described that includes a database for storing terrain data, a processing unit, an altitude determination unit, and a visual display. As the aircraft proceeds along a flight path, the processing unit determines the aircraft's current position and compares associated terrain elevation data stored in the database with altitude data received from the altitude determination unit. For example, if the processing unit's comparison of the stored terrain data and altitude data indicates that relative terrain data need not be displayed, then the processing unit provides absolute terrain color renderings to the display.

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: The present invention provides an aircraft navigational system including a graphical user interface that is capable of displaying navigational information in a split-screen format. The split-screen format includes displaying multiple graphical user panels, each depicting different traffic information. For example, one of the panels displays a plurality of air traffic symbols corresponding to airborne obstacles and another of the panels simultaneously displays ground traffic symbols representing ground obstacles. The obstacles can include other aircraft in the air and on runways as the pilot's aircraft approaches for a landing. The navigational system also is capable of switching between a single graphical user panel and multiple panels in response to a triggering event, such as a change in the course of the aircraft.

Abstract: A system is provided which provides an indication of checklist items, for example, in an aircraft. The system monitors aircraft systems and automatically prioritizes information gathered from those systems and selects and arms the appropriate checklist. The pilot may select and/or arm a checklist via a pilot-VCS (voice checklist system) interface. The system provides checklist prompting and step verification.

Abstract: An E-field sensing system is provided to detect the presence of obstacles, including wires, power lines or trip wires, as well as towers, guy wires, buildings and elevated terrain, in which a variation or tilt of the iso-potential electrostatic field adjacent the obstacle is detected. In one embodiment the bearing to the obstacle is ascertained. The result is the detection of power lines from as far away as at least 1,000 feet and unpowered wires from as far away as at least 100 feet, thus reducing pilot anxiety for low level missions as well as providing for wire strike avoidance.

Abstract: A system and method for assisting a pilot to recover the aircraft from a variety of dangerous situations involving one or more of the following: altitude, airspeed, attitude, roll rate, and a partial equipment failure in the control panel. In accordance with the invention, these factors are sensed automatically, and voice instructions are provided to the pilot to direct him or her to get the aircraft out of the dangerous situation sensed by this system.

Abstract: A system and method for efficient intervisibility determination. The intervisibility determination method of the present invention provides a multiple threat processing capability within a specified area of terrain using a common database. Computation is simplified through the method of processing data posts in the terrain elevation database. By taking integer steps and incrementing distance, x or y, and a predicted elevation value at each step, a small number of operations may be performed. Recomputing a change in elevation value may be reduced. An umbra database provides an enhanced look-up capability for displaying and updating the intervisibility display information. The systems and methods of the present invention may be suitable for use on a vehicle and in mission management activities.

Abstract: A processor, software code, and a method for generating warning indicating that flaps are not suitably in a take-off position. A first component is configured to receive a first signal indicative of one of a group of flaps positions, the group including a take-off position. A second component is configured to receive a second signal indicative of an aircraft position. A third component is configured to compare the aircraft position to the contents of a database and to, by the comparison, determine whether the aircraft position is within a runway perimeter. A fourth component is configured to generate an alarm when the aircraft is within the runway perimeter and the flaps position is not the take-off position.

Abstract: A method and device for detecting an overstepping of design loads of the fin of an aircraft. The device includes a set of information sources and a section for determining, with the aid of information emanating from the set of information sources, a current bending moment. The device further includes a section for determining, with the aid of information emanating from the set of information sources, a current twisting moment, and a section for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformation on the fin.

Abstract: Methods for analyzing system operator coupling susceptibility are described herein. In one embodiment, an open loop frequency response can be compared to a related over-steer point. An over-steer point can be the condition where, as operator gain is increased for an open loop system, the corresponding closed loop gain at a corresponding resonance peak increases by at least approximately the same amount as the increase in operator gain or at least approximately a selected larger amount than the increase in operator gain. In other embodiments, an open loop frequency response can be compared to a critical gain rate. The critical gain rate can be the rate of change of open loop gain per open loop phase angle of the corresponding open loop system response at an over-steer point that is associated with a zero decibel closed loop gain.

Abstract: A pilot seat ejection system for use in a number of environments, can be designated for automatic operation. A microprocessor, or other on-board computer, uses avionic sensors to sense an irreversible catastrophic or dangerous situation, thereby initiating automatic ejection. While the system is particularly applicable during vertical operation of an STOVL Aircraft, the present system can be used on a wide variety of different vehicles in a wide variety of different situations.

Abstract: The present invention is directed to a system and method for a safe flight display through increasing situation awareness by an optimal presentation, given limited capacity of the system. The system may determine which terrain area needs a detail representation and which area needs a coarse representation. A view-dependent visual error metric may be utilized to define and maintain an error bound and accurately minimize the amount of terrain data being depicted. By performing a breadth-first search on the terrain database, a user can determine amount of geometry to be displayed with limited bandwidth of data presentation. The user may be allowed to scale the application to his/her desired level of detail, given a capacity of the system. Therefore, the system may provide a safe flight display with an anticipated and graceful (all portions of the screen would be given an equal quality representation) degradation in performance upon the choice of the user.

Abstract: The invention is directed to a display device for working vehicle, which is adapted so that additional information can be displayed. In the invention, display indication marks of the two types can be interchangeably displayed on a common display screen of a limited area without reducing the sizes of the individual marks, so that neither a larger size of a display device nor a drop in the visibility of the indication marks is necessary. This enables the driver to control a working machine such as a construction machine and have additional information about the construction machine without any trouble in the driving.

Abstract: The present invention provides an aircraft navigational system including a graphical user interface that is capable of displaying navigational information in a split-screen format. The split-screen format includes displaying multiple graphical user panels, each depicting different traffic information. For example, one of the panels displays a plurality of air traffic symbols corresponding to airborne obstacles and another of the panels simultaneously displays ground traffic symbols representing ground obstacles. The obstacles can include other aircraft in the air and on runways as the pilot's aircraft approaches for a landing. The navigational system also is capable of switching between a single graphical user panel and multiple panels in response to a triggering event, such as a change in the course of the aircraft.

Abstract: System and method of wireless remote control of various defense systems installed aboard an airplane, wherein such defense systems comprise at least one of releasing gases, releasing chemical sprays, fogging, spraying sticky glue, firing laser guns, and sounding alarms. Small easy to conceal, microprocessor based transmitter means communicate with receivers, which are configured and adapted to be part of the control circuitry for the defense measures aboard the airplane. The transmitter means further have bi-directional telemetry means, to facilitate communications among crew members and ground personnel, while hostile situation is likely or is present aboard the aircraft. In one aspect of the invention the transmitter means can also activate auto flight navigation system, if required. The wireless remote control system of the invention can have more than one type of transmitter, with various levels of software lockouts, for different crew members to activate the defense systems.

Abstract: The invention relates to an aircraft navigation aid method. It comprises the following steps of defining an area to be sensed to the right and to the left of a first hypothetical path of the aircraft, sensing, for each of the two areas to be sensed to the right and to the left, a corresponding predefined underlying relief, in order to identify dangerous sub-zones to the right and/or to the left, computing, for each of the dangerous sub-zones to the right and/or to the left, a time ?T remaining to begin an avoidance maneuver before a point of no return, and determining for the dangerous sub-zones to the right a minimum ?T denoted ?T right and/or for the dangerous sub-zones to the left a minimum ?T denoted ?T left, establishing a navigation aid from ?T right and/or ?T left.