Abstract: A tree structure represents a terrain area as nested polygons organized in a parent-child relationship, each polygon associated to a specific geographic location. The tree structure defines at least one parent node and a plurality of child nodes, some being leaf nodes containing a height value. A processor uses a distance measure to change the tree structure topology assessing whether all leaf node children of a first parent node lie outside a predetermined distance from an aircraft runway, and if so, converting the first parent node into a leaf node by storing in the first parent node a height value representing the greatest of the respective height values of the leaf node children and by removing the leaf node children; and iteratively repeating for each remaining parent node until it has been determined that every remaining parent node in the data structure cannot be pruned without violating accuracy requirements.

Abstract: Methods and systems for improved positioning accuracy relative to a digital map are disclosed, and which are preferably used for highly and fully automated driving applications, and which may use localisation reference data associated with a digital map. The invention further extends to methods and systems for the generation of localisation reference data associated with a digital map.

Abstract: Apparatuses, methods, and systems are disclosed for aerial vehicle state transition configuration. One apparatus (200) includes a receiver (212) that receives (902) a state transition configuration corresponding to an aerial vehicle from a base unit. The apparatus (200) includes a transmitter (210) that transmits (904) a state transition report to the base unit based on the state transition configuration.

Abstract: A system for aiding landing includes a module for computing by extrapolation a trajectory of the aircraft on the basis of its current position, a module for determining whether the extrapolated trajectory cuts the ground ahead of a threshold of the landing runway, a module for measuring a current height of the aircraft above an overflown terrain, a module for determining whether the current height corresponds to a risk height, an alert module for generating an alert only if the two determinations carried out by the two determination modules are positive, and if the aircraft is situated at a distance with respect to the threshold of the landing runway which is less than a predetermined threshold distance.

Abstract: A system and method of displaying an Engine Failure Awareness Chart (EFAC) for aircraft with at least one engine out is shown and described herein. The EFAC may display lines and zones indicative of levels of risk of obstacles on the ground. The obstacles may be either man-made or natural structures. The EFAC may update continuously providing the pilot with a real-time awareness of the risks around the aircraft during an engine failure. Using the EFAC the pilot may navigate the aircraft to a landing area or back to the airport for landing.

Abstract: An apparatus for supporting an aircraft approaching an airfield runway of an airfield is provided. The apparatus obtains a current pose estimate of the aircraft relative to the airfield runway and determines, based on the current pose estimate of the aircraft, a plurality of proximate poses of the aircraft. The apparatus generates a plurality of images of the airfield runway from a plurality of expected points-of-view of the aircraft and acquires a real-time image of the airfield runway. The apparatus performs a comparison of the real-time image and the plurality of images to identify a best-match image from the plurality of images and generates, based on the best-match image, an updated current pose estimate of the aircraft. The apparatus outputs the updated current pose estimate to a flight control computer of the aircraft, for use in guidance of the aircraft on a final approach.

Abstract: A system includes a communication interface configured to receive squitter messages from other aircraft in the vicinity of an ownship aircraft. The system also includes a processor aboard the ownship configured to receive the squitter messages, determine the altitude and position of the other aircraft from the squitter messages, and compare the altitude of the other aircraft to terrain data at the determined position to determine whether any of the other aircraft are operating abnormally. The system also includes a display providing an indication that a first aircraft of the other aircraft is operating abnormally.

Abstract: An aircraft includes a fuselage having a cabin. The aircraft also includes a cabin pressure sensor configured to detect cabin pressure level of the cabin. The aircraft further includes a controller configured to determine a pressure threshold as a function of a pressure altitude of a destination airport of the aircraft. The controller is also configured to activate a flight safety system based on the cabin pressure level satisfying the pressure threshold.

Abstract: A method includes generating a flight plan of an aircraft. The flight plan is based on at least one waypoint and a set of operational rules associated with the aircraft. The method also includes generating an initial trajectory profile based on the at least one waypoint and the set of operational rules. The method further includes identifying an impermissible flight condition associated with the initial trajectory profile. The impermissible flight condition violates at least one operational rule of the set of operational rules. The method further includes generating a modified trajectory profile by modifying at least one aspect of the initial trajectory profile to remove the impermissible flight condition. The modified trajectory profile can be used by a pilot to fly the aircraft, the modified trajectory profile can be used by an autopilot system, or the modified trajectory profile can be displayed.

Abstract: Aircraft and methods and systems for determining airspeed of an aircraft. The methods and systems allow for calculation of airspeed in near-ground and on-ground aircraft operation. A GPS altitude and a vertical acceleration of the aircraft are obtained for a current time frame. A geometric altitude for the previous time frame is determined, and the difference between the GPS altitude and geometric altitude are combined with the vertical acceleration to calculate a geometric altitude rate of change. The geometric altitude rate of change is used to calculate a pressure altitude rate of change, which is used to calculate a pressure altitude for the aircraft. A static pressure is calculated from the pressure altitude, and the airspeed is calculated using the static pressure.

Abstract: This method of managing the display of an aeronautical map from cartographical data is implemented by an electronic management device and comprises the following steps: acquiring a display scale of the map; determining a set of symbol(s) representative of obstacle(s) to be displayed, the obstacle(s) being included in the cartographical data, where: if the distance between two obstacles is greater than a visible distance threshold that depends on the display scale, two separate symbols are determined for these obstacles, each being representative of a respective obstacle, and if the distance between two obstacles is less than or equal to the visible distance threshold, a symbol representative of a grouping of obstacles is determined for these obstacles.

Abstract: A method for controlling the warning lights of an unmanned aerial vehicle, in a system, in which one or more light modules are connected to a controller (1), which controller (1) is also connected via a communication interface (5) to a decision subsystem (6) adapted to receive an activation signal from a delivery module (7, 8, 9, 10) providing the activation signal, which method comprises the following steps: a) delivery of the activation signal by the delivery module (7, 8, 9, 10) providing the activation signal to the decision subsystem (6), b) generation of a request to turn the warning lights (4) on or off by the decision subsystem (6) based on the activation signal, and transfer of this request via the interface (5) to the controller (1), c) turning the warning lights (4) on or off by the controller (1) according to the request received in step b). The invention comprises also a system for application of this method.

Abstract: A method, a mobile device, and a computer program product for detecting if a mobile device is in an airplane environment. The method includes receiving motion sensor data from a motion sensor and calculating a velocity value based on the motion sensor data. The method further includes determining if the velocity value is greater than a velocity value threshold and in response to determining that the velocity value is greater than the velocity value threshold, a barometric pressure sensor measures barometric pressure data associated with a current environment of the mobile device. The method further includes receiving the barometric pressure data from the barometric pressure sensor and determining if the barometric pressure data matches reference barometric pressure data. In response to determining that the barometric pressure data matches the reference barometric pressure data, an airplane mode of the mobile device is enabled.

Abstract: The present invention provides a system and method for pilot(s) to avoid engaging incorrect control(s) and/or switch(es) in the event of engine fire or mechanical malfunction, to prevent shutdown of a functioning engine. The system and method employs amber or another color lights to indicate a malfunction that the pilot may correct, such as restarting a functional engine that has ceased working. Additionally, the system and method of the present invention employs red or another color lights to indicate to the pilot(s) that a mandatory shutdown of a failed engine is required, and provides guidance to the correct controls and switches, as indicated and positively identified by the lighting system and method.

Abstract: A microcontroller controlled altimeter includes a microcontroller, a digital altitude pressure sensor with a pressure indicating output coupled to the microprocessor, and at least one Form A solid state relay coupled to the microcontroller, where the microcontroller is configured to provide control signals to the at least one Form A solid state relay to provide an open circuit between normally open and common terminals of the at least one Form A solid state relay if the digital altitude pressure sensor output is less than, or equal to, a setpoint for the at least one Form A relay, and provide continuity between the normally open and common terminals of the at least one Form A solid state relay if the digital altitude pressure sensor output is greater than the setpoint for the at least one Form A relay.

Abstract: An automated detection and avoidance system that provides a pilot with high-fidelity knowledge of the aircraft's physical state, and notifies the pilot of any deviations in expected state based on predictive models. The automated detection and avoidance system may include a processor and a sensor payload operatively coupled to the processor to detect a non-cooperative obstacle within a first airspace adjacent the aircraft. The sensor payload may comprise a radar to radially scan the first airspace, and a camera to scan a second airspace within said first airspace.

Abstract: A method to assist in a search and rescue mission comprises: scanning at least a portion of a terrain at a search and rescue site using a scanning device to obtain searched area information, wherein searched area information is information captured by the scanning device of the at least a portion of the terrain; analyzing the searched area information obtained after scanning the at least a portion of the terrain; and communicating leading air vehicle information to at least one trailing air vehicle, wherein leading air vehicle information includes searched area information and analysis, and wherein the at least one trailing air vehicle is an air vehicle that reaches the search and rescue site after the at least one leading air vehicle.

Abstract: Avionic display systems and methods are provided for generating avionic displays including aerial firefighting symbology, which enhance pilot situational awareness and decision during aerial firefighting operations. In an embodiment, the avionic display system includes an avionic display device, a thermal image sensor configured to detect thermal image data external to the aircraft, and a controller operably coupled to the avionic display device and to the thermal image sensor. During operation of the avionic display system, the controller compiles a fire map of a fire-affected area in proximity of the aircraft based, at least in part, on the thermal image data collected by the thermal image sensor. The controller further generates a first avionic display on the avionic display device including graphics representative of a field of view (FOV) of the thermal image sensor and portions of the fire map outside of the FOV of the thermal image sensor.

Abstract: Various navigation and other instrumentation systems may benefit from appropriate methods for selection of traffic. For example, certain avionics may benefit from systems and methods for selecting and designating ADS-B or similar traffic. An apparatus can include a display and a processor. The processor and the display can be configured to permit selection of at least one target aircraft identified on the display.

Abstract: A weather radar system for an aircraft includes a weather radar system and a processing circuit. The weather radar system is configured to determine weather data, the weather data including an indication of precipitation at a plurality of altitudes, a plurality of azimuth angles, and at a plurality of ranges from the aircraft. The processing circuit is configured to receive the weather data from the weather radar system and generate an overhead display from an overhead perspective based on the weather data. The overhead display visually illustrates the precipitation at a particular distance from the aircraft and at a particular azimuth angle. The processing circuit is configured to generate a face-on on display based on the weather data and cause a display screen to display the overhead display and the face-on display. The face-on display visually illustrates a particular altitude of the precipitation and the azimuth angle of the precipitation.

Abstract: An aerial system, preferably including one or more proximity sensors, such as sensors arranged in opposing directions. A method for aerial system operation, preferably including: determining a set of sensors; sampling measurements at the set of sensors; localizing the aerial system based on the measurements, such as to determine one or more obstacle clearances; and controlling system flight, such as based on the clearances.

Abstract: A computer system 20 provided in an aircraft 1 includes, as a module of a computer program to be executed, an approach determination section 31 configured to determine whether the aircraft 1 is approaching a landing site. The approach determination section 31 includes, as a condition for determination of approaching, establishment (C1) of one or both of a condition (C11) that a first absolute altitude A1 obtained by an radio altimeter 21 mounted on the aircraft 1 is low relative to a first approach altitude AA1, and a condition (C12) that a second absolute altitude A2 that is obtained by subtracting an altitude AL of the landing site from a pressure altitude Ap determined by a barometric altimeter 22 mounted on the aircraft 1 is low relative to a predetermined second approach altitude AA2.

Abstract: A method for three-dimensional graphic representation of the outside landscape in an on-board display system for aircraft comprises a graphical computer and a display screen. The graphic representation is computed to a visibility distance. In the method the zero pitch line of the aircraft forms, with the real horizon line, a first angle, the line representing the limit of the visibility distance forming, with the real horizon line, a second angle, in a first step, the graphical computer determines the maximum visibility distance such that the difference between the first angle and the second angle remains less than a determined value; in a second step, the graphical computer determines the visibility distance as a function of the maximum visibility distance, of the maximum altitude of the relief of the local environment and of the flight phase.

Abstract: The embodiments described herein relate to dynamically detecting landing gear deployment of an aerial vehicle. A set of flight measurements is dynamically generated and stored. The set of measurements may include altitude, distance to a destination, and airspeed. Each of these measurements is compared to a respective threshold value to produce a landing scenario indication. The comparison includes ascertaining that the vehicle is within a defined above ground level based on the altitude measurement, ascertaining that the vehicle is within a defined distance to a destination based on the distance to a destination measurement, and ascertaining that the airspeed measurement is below a maximum gear extension speed. The produced indication is converted into a landing gear protocol.

Abstract: The present invention is a system and method for aircraft ground collision avoidance (iGCAS) comprising a modular array of software, including a sense own state module configured to gather data to compute trajectory, a sense terrain module including a digital terrain map (DTM) and map manger routine to store and retrieve terrain elevations, a predict collision threat module configured to generate an elevation profile corresponding to the terrain under the trajectory computed by said sense own state module, a predict avoidance trajectory module configured to simulate avoidance maneuvers ahead of the aircraft, a determine need to avoid module configured to determine which avoidance maneuver should be used, when it should be initiated, and when it should be terminated, a notify Module configured to display each maneuver's viability to the pilot by a colored GUI, a pilot controls module configured to turn the system on and off, and an avoid module configured to define how an aircraft will perform avoidance maneuv

Abstract: A method according to an aspect of the present invention includes determining if terrain presents a hazard to an aircraft based on the current position of the aircraft and the intended flight plan for the aircraft and providing an alert if it is determined that the terrain presents a hazard to the aircraft. The method may be employed in any situation to achieve any result, such as when the aircraft is in a low-RNP environment to prevent nuisance terrain alerts.

Abstract: The general field of the invention is that of methods for three-dimensional conformal representation of a terrain. The method is used in a piloting and navigation assistance system of an aircraft. The assistance system comprises a navigation system, a cartographic database, electronic calculation means a meteorological database and a display system allowing the superimposition of synthetic images on the exterior. The method comprises the following steps: Step 1: Calculation, for a determined position of the vehicle, of the terrain perceptible through the display system; Step 2: Selection of a part of the said terrain as a function of a distance or of an altitude or of a range of altitudes; Step 3: Calculation of a three-dimensional conformal cartographic representation of the said selected part of the terrain; and Step 4: Display of the said cartographic representation by the display system.

Abstract: A method can include determining that an aircraft is on approach to a runway. The method can include determining a flight path vector (FPV) location of the aircraft based at least in part on a projected landing location with respect to the runway and determining a current airspeed of the aircraft. The method can also include performing at least one of the following: issuing a landing short alert to a pilot of the aircraft if the FPV location is at or before the runway threshold, issuing an airspeed caution alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is below a landing short envelope, and determining not to issue an alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is at or above the landing short envelope.

Abstract: This method of determining the risks of collision of an aircraft (1) when travelling on the ground comprises the steps of: determining the path of at least one of several parts to protect of the aircraft (1), determining a protection volume (VR, VP) associated with said at least one of several parts to protect of the aircraft, in which the shape in a horizontal plane of said protection volume depends on said path of said at least one of several parts to protect, detecting an object entering said protection volume, and generating a warning in response to detecting said object.

Abstract: A polygonal mesh is generated from a collection of points that are organized for a mesh partition in accordance with a tile that includes one or more bins used to process the points that define the mesh. The resolution of the tile is related to the number of bins for the tile. The organization of the tiles in a partition of the mesh permits the mesh to be constructed with partitions that are independent of each other and that can be joined to form a continuous mesh. The resolution of the mesh can be dynamic with respect to the partitions due to the variable resolution assigned to each tile. Portions of the mesh for which points are not provided can be assigned finalization points to permit a continuous mesh to be constructed.

Abstract: A method includes receiving, at a computing device, vehicle condition data from a vehicle monitoring system of a vehicle. The method also includes analyzing the vehicle condition data based on a trigger table, and based on a determination that the vehicle condition data satisfies a particular trigger condition specified in the trigger table, adding an entry in an alert evaluation queue.

Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.

Abstract: The invention relates to a method of assisting piloting an aircraft. The method is performed when the real position of a symbol for display lies outside the display limit of the screen. The symbol is representative of a parameter associated with the dynamic behavior of the aircraft (FPV, . . . ) or liable to influence said behavior (FD, . . . ). The symbol possesses two components, and the first component is to be given precedence on display over the second component. In the method, the display of the symbol depends firstly on the orthogonal projection (FPV-lock) of the real position (FPV) of the symbol onto the axis of the first component, and secondly on the position of said projection relative to the display limit of the screen. Such a display makes it possible to give reliable information to the pilot.

Abstract: A system for visualization of 3D objects and/or 3D terrain includes a processor, a display in communication with the processor, and a range metering device in communication with the processor. The system visualizes the 3D objects and/or the 3D terrain based upon their respective distances from the mobile device and based upon a respective parameter measuring the detail of the 3D object and/or the 3D terrain.

Abstract: An object type determination apparatus mounted in a vehicle. In the apparatus, a detection unit detects an object present forward of the vehicle. A height estimation unit estimates a height of the object detected by the detection unit from a road surface. A determination unit uses the estimation result of the height estimation unit to determine, according to one of a plurality of predefined criteria, whether or not the object is an object for which a collision avoidance process is performed. A complex environment estimation unit estimates a likelihood that a complex environment is present forward of the vehicle. A criterion selection unit selects the one of the plurality of predefined criteria used by the determination unit on the basis of the estimation result of the complex environment estimation unit.

Abstract: A method of displaying navigation limits for a planned travel route of a vehicle is presented here. The method calculates estimated navigation limits for the vehicle using an onboard subsystem of the vehicle, where the estimated navigation limits represent self-assessed navigation accuracy of the vehicle relative to the planned travel route. Contracted navigation limits are acquired for the vehicle, where the contracted navigation limits represent specified navigation accuracy of the vehicle, relative to the planned travel route, as mandated by a third party navigation controller. A navigation display is rendered on an onboard display element such that it includes graphical representations of the planned travel route, at least one of the estimated navigation limits, and at least one of the contracted navigation limits.

Abstract: The invention relates to an alarm apparatus (1) for a pilot's headset (3) and to a pilot's headset having such an alarm apparatus. The alarm apparatus comprises an attitude sensor (11), which detects its inclination relative to a starting position or the horizontal, and a measuring device (12) for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit. In addition, the alarm apparatus has a means (13) which is set up to trigger an alarm signal when a recorded period of the inclination tolerance limit being exceeded is longer than a preset maximum period.

Abstract: An flight-safe indicator for a battery displays the flight-safety state of a battery to be transported by an aircraft. The indicator can be easily recognized by ground personnel anywhere regardless of the language they speak or read. The indicator comprises an icon indicating that the battery is safe for flight and would be easily recognized by personnel at an airport. The icon would be placed on the battery or on the battery packaging prior to loading on the aircraft. When the magnitude of power stored on the battery exceeds a safety threshold, the icon changes to an indication that the battery is not safe for transporting by aircraft and the operator may discharge the battery using a load until it reaches a safe level.

Abstract: According to aspects of the embodiments, there is provided an apparatus and method to synchronize trajectories from independent systems such as from a flight management system and the ground Air traffic control during the entire history of a flight. Since a number of trajectory discrepancy factors will intervene during the lifetime of a flight, such as a change in flight intent, controller intervention, or large deviations of the actual flight from the predicted trajectory due to prediction errors, there is need to dynamically monitor these deviations and control a dynamic synchronization cycle. A dynamic trajectory synchronization algorithm attempts to bring each of the systems back into balance whenever a disturbance causes an imbalance.

Abstract: A system and method are provided for increasing vertical situational awareness when the display of intruder aircraft on a vertical situation display (VSD) is restricted to a specific region of the VSD as determined by an altitude filter. The method comprises displaying a first altitude filter limit line on the VSD.

Abstract: A method and apparatus for managing a programmable control panel for a vehicle. A number of first level control functions is assigned to the programmable control panel for the vehicle. A number of second level control functions is assigned to the programmable control panel based on a health of programmable control panels in the vehicle.

Abstract: An exemplary embodiment relates to an aircraft system for detecting wires. The system includes a processor configured to actively sense a presence of a first object and a second object. The processor determines a location of the first object and the second object. The processor determines a potential location of a wire between the first object and the second object. The processor actively senses the wire by providing electromagnetic energy to the potential location.

Abstract: Methods and systems are provided for improving pilot situational awareness during brown-over-brown display situations. An image is rendered, on a display, that includes one of, or both, rendered terrain and rendered sky. A sky veil is at least selectively rendered on a portion of the display. The sky veil, when rendered, is rendered at least partially transparent and in a manner that portions of the sky veil that overlap with rendered sky are not discernable, and rendered terrain is viewable through portions of the sky veil that overlap with terrain.

Abstract: A system and methods for generating alerts in a terrain awareness and warning system (“TAWS”) in an aircraft, using data acquired from a forward-looking radar The system comprises a forward-looking imaging device, an airport database, a navigation system, a forward-looking terrain alert (“FLTA”) processor, and a crew alerting system. The FLTA processor determines a measured clearance altitude of a highest cell within an area and compares it with a required minimum clearance altitude; if the measured altitude is equal or less than the required altitude, the crew is alerted. Alternatively, a terrain database may be used. with the FLTA processor for determining if the aircraft descends below the minimum operating altitude or is predicted to do so and then generating an alert. A method is disclosed for generating TAWS alerts using elevation angle measured by the forward-looking radar and terrain data retrieved from a terrain database.

Abstract: A hazard detection system is for use on board an aircraft or other vehicle. The aircraft or other vehicle is disposed in an environment. The hazard detection system includes a circuit for receiving a charge accumulation signal indicative of the electric field associated with the environment. The circuit provides a warning in response to the charge accumulation signal. The warning is indicative of a hazard or potential hazard.

Abstract: A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.

Abstract: A method of managing an aircraft in flight may include electronically monitoring for a presence of a threat object along a flight path of the aircraft and at a destination airport of the aircraft, and electronically generating an alert when the presence of the threat object is detected. The alert may include information enabling air traffic control (ATC), flight dispatch, and a pilot of the aircraft to make a collaborative flight path correction decision that may prevent the aircraft from being affected by the threat object.

Abstract: Present novel and non-trivial system, apparatus, and method for generating a lateral meteorological profile are disclosed. The system is comprised of a source for providing hazard data and a lateral profile generator (“LPG”), where the source could be comprised of an aircraft weather system and/or a datalink system through which hazard weather data is received. The apparatus is comprised of the LPG configured to perform the method comprised of receiving hazard data, determining profile location data, and generating profile image data. The hazard data represents location information of each hazard located outside the aircraft, the profile location data is representative of a plurality of locations of maximum vertical sector height within a vertical sector, and the profile image data is representative of a lateral meteorological profile comprised of a plurality of points, each point corresponding to one location of the maximum vertical sector height.

Abstract: Methods and systems are provided for displaying visually distinguishing characteristics if an aircraft is below a minimum altitude or beyond a maximum distance when executing a procedure turn. A procedure turn icon, an aircraft icon indicating the aircraft's present location, terrain/obstacles, and the visually distinguishing characteristics are displayed on a moving map.

Abstract: Methods, systems, and computer-readable media are described herein for providing comparative vertical situation displays of multiple flight routes. According to embodiments presented herein, information regarding a currently active flight route of an aircraft and one or more proposed alternate flight routes is combined with airborne constraint data to display a comparative vertical situation display for each of the active route and/or the proposed routes. Each of the comparative vertical situation displays shows the vertical component of the corresponding flight route along with the vertical components of one or more airborne constraints along the corresponding flight route. The comparative vertical situation displays are concurrently shown on a display unit, allowing the flight crew of the aircraft or route planning personnel to compare the impact of the airborne constraints along the vertical component of each of the flight routes.