Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

Abstract: A method of and a system for presenting an operating status of an aircraft engine. The method comprises accessing a first indication indicative of a position of an aircraft engine start switch and accessing a second indication indicative of an aircraft engine start operating mode, the second indication having been generated based on an analysis of a parameter associated with an operating condition of the aircraft engine. The method, upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is a healthy start causes the display of a visual indication indicative of the healthy start. The method upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is an abnormal start causes the display of a visual indication indicative of the abnormal start.

Abstract: An airspeed calculation system for determining the airspeed of an aircraft includes a static pressure device, a global positioning system device, an inertial measurement unit device, an angle of attack device, a total pressure sensor, a total air temperature sensor, at least one processor, and a memory. The at least one processor is in electronic communication with the memory, the static pressure device, the global positioning system device, the inertial measurement unit device, the angle of attack device, the total pressure sensor, and the total air temperature sensor. The memory includes programming code for execution by the at least one processor. The programming code is configured to determine the airspeed of the aircraft using data obtained from each of the static pressure device, the global positioning system device, the inertial measurement unit device, the angle of attack device, the total pressure sensor, and the total air temperature sensor.

Abstract: A procedure for facilitating the approach to a platform [PF] with an aircraft [1] including a construction stage [STP1] for a database [5] that includes, for each stored platform [PF], attributes that include at least one platform identifier, the coordinates of the platform, a landing height [HDECK] of a landing zone of the platform, and the radius (OR) of a circle within which the platform is inscribed. During a parameterization stage [STP2], the target platform to be reached is determined, along with a course (CRS) to be followed and a height parameter relative to a minimum decision altitude (MDA). During a construction stage [STP3], the position of an initial approach fix (IAF) is determined, along with the position of a final approach fix (FAF), an offset point (OIP), and a decision point (MAP), in response to the information and in response to the attributes.

Abstract: A method and apparatus is provided for enhancing situational awareness onboard an aircraft during an aircraft ground maneuver such as when taxiing on a runway or taxiway. A three-dimensional view including airport features is rendered in a first airport region that extends a first predetermined distance (D1) from the aircraft when the aircraft speed is less than a predetermined speed (V1). A three-dimensional view including airport features in a second airport region is rendered that extends beyond D1 when the aircraft speed exceeds V1.

Abstract: The disclosed embodiments relate to an aircraft that includes system for selecting an airspeed reference that is displayed within a cockpit of an aircraft. The system includes a processor and a display located in the cockpit. The processor is configured to determine whether primary airspeed is valid or invalid, and, to select a backup airspeed as the airspeed reference that is output to the display when it is determined that the primary airspeed is invalid. The display is configured to display the backup airspeed as the airspeed reference. The backup airspeed is generated based on Global Position System (GPS) information that is received by the aircraft.

Abstract: Embodiments of a flight deck display system deployed onboard an aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a cockpit display device and a controller. The controller is configured to: (i) establish the speed trend of the aircraft over a predetermined time period; (ii) generate a primary flight display on the cockpit display device including a speed trend vector graphic representative of the established speed trend; and (iii) alter the appearance of the speed trend vector graphic in a first predetermined manner if a low speed change condition is detected during at least one of aircraft takeoff and landing.

Abstract: A schematic display for presenting vertical navigation (VNAV) data is disclosed. A planned route such as a flight plan is divided into a series of VNAV legs, and only a VNAV schematic that corresponds to the active VNAV leg is displayed. The VNAV schematic in accordance with the present disclosure is a profile-view schematic for the active VNAV leg, providing a visual representation indicating the locations of the upcoming Top of Climb (TOC) or Top of Descent (TOD). Additional VNAV data may also be presented to provide content context. Since the schematic display in accordance with the present disclosure only displays VNAV data relevant to the active VNAV leg at a given time, the complexities associated with displaying the VNAV schematic is reduced, making the VNAV data easy to read and understand.

Abstract: A system and method are provided for graphically displaying airspace data including speed restrictions on an aircraft display. The system comprises an avionics display system coupled to a processor that is configured to retrieve airspace data from a database, display the aircraft data on the display, and display a visual representation of the airspace. Then the processor may alter the format of the visual representation of the airspace to a second visual representation, if the airspace data meets predetermined criteria.

Abstract: A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed.

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

Abstract: A wireless device for facilitating GPS-based asset tracking. The wireless device includes dynamically configurable event profiles which allow the wireless device to be dynamically reconfigured and to perform certain actions based on a dynamically configurable combination of received events. In addition, geofences with inherent aspects are used to trigger certain actions of the wireless device based on classes and attributes that define the inherent aspects.

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

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

Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.

Abstract: Systems and methods facilitate the monitoring of tire pressure, the detection/determination of wheel speed, or a combination thereof. A system is provided comprising a hub cap, a target coupled to the hub cap, and at least two displacement sensors configured to measure a displacement between each displacement sensor and the target. The target has a variable thickness, and the target comprises a hollow vessel in fluid communication with a tire.

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

Abstract: A flap advisory system provides an advisory to a pilot informing that a speed of the aircraft should be attended to because of a current or desired flap setting. More specifically, the flap advisory system compares a measured airspeed of the aircraft either directly to a flap placard speed or to a marginal speed range set below the flap placard speed for a given flap setting. If the measured airspeed is determined to be excessive then the system provides an advisory indicating the airspeed is too fast. Further, the system may provide an advisory when a movement of a flap handle is detected such that continued movement of the flap handle would place the flaps in a setting that is inappropriate for the measured airspeed.

Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.

Abstract: A device for confirming the engine thrust of an aircraft is disclosed. The device, via an operating logic unit (14) of each engine processing different information, including a warning indicator (15) connected to the unit (14) delivers or not thrust confirmation information at the level of the cockpit.

Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.

Abstract: A vertical profile for an in-trail procedure can provide a pilot with enhanced situational awareness. Such a vertical profile may be able to provide a graphical indication of a clearance window for change in altitude procedures, as well as the underlying bases for such a window. A method can include providing, in a hardware display, a graphical vertical profile displaying an aircraft to a pilot of the aircraft. The method can also include providing, in the vertical profile, an indication of the relative speed of at least one other aircraft and a graphical indication of a clearance window for vertical maneuvers for the aircraft of the pilot.

Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.

Abstract: An inertial navigation system which includes a first control system and a second control system is described. The first control system is configured to estimate a vertical velocity based in part on received vertical acceleration data. The second control system is configured to receive the estimated vertical velocity from the first control system and determine a compensated vertical velocity utilizing the estimated vertical velocity and airspeed.

Abstract: A wireless device for facilitating for GPS-based asset tracking via a wireless communications network and a centralized management system. The wireless device includes dynamically configurable event profiles which allow the wireless device to be dynamically reconfigured and to perform certain actions based on a dynamically configurable combination of received events.

Abstract: A system and method of at least reducing the likelihood of a rotor lock in an aircraft gas turbine engine is provided. A determination is made that each propulsion gas turbine engine on an aircraft has experienced a flameout. The rotational speed of each propulsion gas turbine engine is compared to a predetermined threshold rotational speed and, if the rotational speed of each propulsion gas turbine engine is below the predetermined threshold rotational speed, a warning is supplied to a flight crew.

Abstract: A method for filtering anti-collision alarms for aircraft, the said aircraft comprising means for calculating its speed and extrapolated positions on its trajectory, the said extrapolated positions being calculated over a fixed maximum time period, called extrapolation time, and a topographical database of the terrain, the said database comprising, within a given perimeter, data on the density of obstacles, comprises a calculation of a weighting coefficient for the extrapolation time of the calculated extrapolated trajectories of the aircraft as a function of the density of obstacles within a surface area included within the perimeter.

Abstract: A flap advisory system provides an advisory to a pilot informing that a speed of the aircraft should be attended to because of a current or desired flap setting. More specifically, the flap advisory system compares a measured airspeed of the aircraft either directly to a flap placard speed or to a marginal speed range set below the flap placard speed for a given flap setting. If the measured airspeed is determined to be excessive then the system provides an advisory indicating the airspeed is too fast. Further, the system may provide an advisory when a movement of a flap handle is detected such that continued movement of the flap handle would place the flaps in a setting that is inappropriate for the measured airspeed.

Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.

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

Abstract: The present invention relates to a standby instrument fitted to the instrument panel of an aircraft detecting overloads. The standby instrument includes a processor to calculate and display flight information based on data provided by associated sensors integrated into a standby system. It additionally includes a module for detecting overload of the aircraft on the basis of the data provided to display the flight information. The invention applies to the detection of overloads during a heavy landing. More generally, it applies to the detection and indication of overloads of an aircraft in various types of environment.

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

Abstract: A method of monitoring an aircraft during use. Flight parameters of the aircraft are monitored to detect an excursion from a flight envelope. While the aircraft is still in flight, the monitored flight parameters are used to determine the severity of a detected excursion, aircraft component(s) possibly affected by the excursion are identified, and flight restrictions and/or inspections responsive to the excursion severity and identified component(s) are specified. This method provides valuable information to a flight crew about flight envelope excursions, can enhance passenger safety and can prevent unnecessary inspections and aircraft downtime.

Abstract: Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.

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 display system is provided for displaying runway landing data. The system includes a processor and a display device. The processor is adapted to receive data representative of an aircraft landing operation and is operable, in response thereto, to supply one or more image rendering display commands. The display device is coupled to receive the image rendering display commands and is operable, in response thereto, to render an image representative of a runway and a segment of the runway that will be used to land and stop the aircraft during the aircraft landing operation. A method for displaying the runway landing data is also provided.

Abstract: A system and method are disclosed for controlling the speed of an aircraft having a preprogrammed speed profile when transitioning from a manually set target speed to the preprogrammed speed profile. In operation, an input is received indicating that a user desires to transition from a manually set target speed to the preprogrammed speed profile. A determination is then made as to whether the manually set target speed satisfies one or more selected conditions for qualifying as a constraint speed of the preprogrammed speed profile. If the manually set target speed satisfies the one or more selected conditions, the preprogrammed speed profile is updated to include the manually set target speed as a constraint speed and the speed of the aircraft is controlled using the updated speed profile.

Abstract: This invention relates to the concept of managing the rate of change of energy in a helicopter or other aeronautical vehicle. The invention uses energy management calculations to determine the maximum longitudinal and lateral inputs that can be made while still enabling the vehicle to maintain a desired vertical state. The results of the calculations can be cued to the pilot either tactilely, aurally, or visually, or used for internal software limiting.

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: A method for providing on-demand audio information to a pilot of a first aircraft during aerial combat engagement with a hostile aircraft. The method includes receiving a pilot-initiated request for information, identifying the pilot-initiated request as either a first request-type or a second request-type. If the pilot-initiated request is identified as the first request-type, retrieving output information relating to current flight parameters of the first aircraft; if the pilot-initiated request is identified as the second request-type, retrieving output information relating to current flight parameters of the hostile aircraft; and generating a verbal message audible to the pilot containing the output information.

Abstract: A method and a system for indicating a target idle running speed, a predicted core speed, a predicted time to running, current engine state or automation modes of an operating aircraft engine, and indicating that the current core speed of the aircraft engine is less than a target idle running speed or is abnormally decreasing towards a target idle running speed. The indicators may be visual or aural. The visual indicators may include graphical or numeric symbols indicating the target idle running speed, the direction of core speed change, the predicted core speed at some future time, or current engine state or automation mode.

Abstract: A process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of the aircraft. The detection device includes a speed measuring device for measuring an effective speed of the aircraft. A first comparator compares the measured effective speed with a maximum speed relating to the current flight configuration of the aircraft. A vertical load measuring device measures a vertical load factor of the aircraft, and a second comparator compares the measured vertical load factor with a limit value of the vertical load factor. An inspection determining device determines whether a structural inspection needs to be performed at the level of the structural part, based of the results of the first and second comparisons.

Abstract: A method of estimating the airspeed of an aircraft during low airspeed conditions includes measuring a negative impact pressure using a pitot-static probe on the aircraft. Then, the method includes estimating a non-zero airspeed of the aircraft as a function of the measured negative impact pressure.

Abstract: A method and system compares combinations of vehicle or aircraft state variables against known combinations of potentially dangerous states. Alarms and error messages are selectively generated based on such comparisons. In one embodiment, pairs of aircraft state variables are selected and compared to known undesirable pairs of state combinations that indicate an error or a condition that a crew should monitor closely. The combinations and error messages are provided by the database. The comparisons are conducted on a periodic basis monitoring real time states of the parameters collected from various sensors and commands. Experts considering a matrix that provides an exhaustive pairwise comparison of potentially important state variables initially identify undesirable state combinations. Error messages and identification of potential alarms are generated based on both knowledge of actual accidents, and on use of expert knowledge to predict potentially dangerous states.

Abstract: Method and system for analyzing, separately or in combination, kinetic energy and potential energy and/or their time derivatives, measured or estimated or computed, for an aircraft in approach phase or in takeoff phase, to determine if the aircraft is or will be put in an anomalous configuration in order to join a stable approach path or takeoff path. A reference value of kinetic energy and/or potential energy (or time derivatives thereof) is provided, and a comparison index for the estimated energy and reference energy is computed and compared with a normal range of index values for a corresponding aircraft maneuver. If the computed energy index lies outside the normal index range, this phase of the aircraft is identified as anomalous, non-normal or potentially unstable.

Abstract: There is provided a method for displaying aircraft positions, which is capable of effectively avoiding the occurrence of near miss or collision. The method displays the terrain of an air space under air traffic control apparently in three dimensions on a display screen, displays aircraft marks at positions on the display screen so as to correspond to the three-dimensional positions of the respective aircraft, and displays a warning mark when a distance between two aircraft is shorter than a threshold value, wherein the warning mark comprises a triangle having three apexes, which comprise the aircraft marks, and a position that is apart from the aircraft mark of one of the aircraft along a vertical line extending perpendicular to the one aircraft toward a ground surface of the terrain by a distance corresponding to an altitude difference between both aircrafts on the display screen.

Abstract: A display system for a vehicle is provided. The display system includes a display configured to render a representation of an intended vehicle path. At least one relative speed indicator is rendered upon the display. The at least one relative speed indicator is configured to move along the representation of the intended vehicle path, in an area of the display that is peripheral to a focus area of the display, in response to a difference between an actual value of a speed-based parameter and a preferred value of a speed-based parameter of the vehicle.

Abstract: A method for displaying flight information includes displaying a first characteristic sign illustrating a speed vector of an aircraft. The method also includes determining a first longitudinal margin of maneuver of the aircraft as a load factor, and displaying a second characteristic sign such that a position of the second characteristic sign relative to the first characteristic sign illustrates the first longitudinal margin of maneuver.

Abstract: Method and indicator for displaying information showing the airspeed tolerance margins for an aircraft. The indicator comprises a central processing unit which selects, from a plurality of longitudinal scales, the longitudinal scale representative of the current aerodynamic configuration of the aircraft and a display means which presents on a display screen the selected longitudinal scale, which is mobile in the longitudinal direction, and whose position on the display screen depends on the current angle of attack of the aircraft, shown by a characteristic marker in a fixed position on the display screen across the longitudinal scale, the latter scrolling up and down relative to the characteristic marker as a function of the current angle of attack of the aircraft.

Abstract: A display system for an aircraft includes a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft. The longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver. The display system also includes a display unit connected to the central unit. The display unit includes a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver.