Abstract: The invention relates to aiding airport navigation by emission of an alert reminding the pilot of a craft moving on the surface of an airport of the circulation constraints encountered locally over his route. The method comprises the following steps: partitioning of the circulation surfaces of the airport into elementary circulation constraint zones each enclosing a set of adjoining points subject to the same local circulation constraints, identifications of the elementary zones and of their specific circulation constraints, detection of the encroachment of the craft into the elementary zones, and upon each encroachment of the craft into an elementary zone, reminder by alert generation, to the commander of the craft, of one at least of the circulation constraints specific to the elementary zone concerned.

Abstract: The invention relates to a method to help a person responsible for a vehicle on an airport to follow running procedures in the airport, the vehicle including a device for using the method, including: a database including: data modelling all or some of an airport environment; one or several acquisition devices for acquiring procedures applicable to the running operation on the airport; one or several devices configured to acquire and determine vehicle status information; calculation means using the database; graphic transcription means and warning means; means of generating sound and visual alarms; wherein the assistance method includes at least the following steps: determine applicable procedures; continuously calculate deviations between the behaviour of the vehicle and applicable procedures; graphic transcription of progress of the vehicle while running and deviations from applicable procedures; trigger visual and/or sound alerts when a predetermined deviation threshold is crossed.

Abstract: The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure, and it is characterized in that it consists in modifying the characteristics of the clearance sensors according to the position deviation of the aircraft relative to the imposed RNP trajectory.

Abstract: The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure. The method includes conferring an additional function on the conventional TAWS functions, specific to the detection of the potential risks of collision of the aircraft with the terrain when following procedures of reduced protection corridor type, and this without modifying either the logics or the characteristics of the clearance sensor or sensors as currently defined in the TAWSs of the state of the art.

Abstract: This system accompanies the “Avoid terrain” type alarms indicating to the pilot that he has passed the limit-point of success of a standard vertical avoidance maneuver either with complementary indications such as the azimuth sectors suitable for a disengagement maneuver or a predefined disengagement path, or an automatic engagement of a predefined avoidance path.

Abstract: The invention relates to a device for measuring dynamic parameters of an aircraft progressing over an airport zone. The aircraft is in the phase of rolling along a traffic lane. The traffic lane comprises ground markings and notably a center line. The device includes at least one means for acquiring images (101), and means (102) for measuring the deviation of the aircraft with respect to the center line on the basis of the acquired images.

Abstract: Conventional terrain anticollision equipment formulates, around the short term forecast trajectory of the aircraft which is equipped therewith, virtual volumes of protection of maneuver charted by feelers and signals a risk of terrain collision as soon as it detects an intrusion of the terrain into these virtual volumes of protection of maneuver.

Abstract: This Terrain Awareness and Warning System produces a new “Too Low Terrain” predictive alert of “Caution” type when the crew of the aircraft has the possibility of resolving a detected risk of collision with the terrain without interrupting the current maneuver to stabilize at a safety altitude by a leveling-off maneuver, without performing a vertical avoidance maneuver. To do this, it measures the ability of the airplane to avoid the terrain with a sufficient margin without performing a vertical avoidance maneuver, taking into account the location or locations of the penetration or penetrations of the terrain along an alert prober C as well as the capacity of the aircraft to level off knowing the flight conditions.

Abstract: The system comprises a means of acquiring the position of the aircraft on the runway and its speed in the taxiing phase, a means of storing data concerning the runway and a predefined deceleration law, a function for calculating the distance that the aircraft will have traveled on the runway when it has reached a certain speed and/or the speed that it will have reached when it has traveled a certain distance: the calculated distance makes it possible to adapt the braking by comparison with the distance remaining to reach the end of the runway; the calculated distance makes it possible to adapt the braking by comparison with the distance remaining to reach the end of the runway; the calculated speed makes it possible to adapt the braking by comparison with the maximum speed to take the exit.

Abstract: The field of the invention is that of onboard terrain anticollision systems for aircraft. Collisions with the terrain while the aircraft is fully controlled have been and still remain one of the main causes of air disasters. Several generations of devices for warning of risk of collision with the terrain have been developed for some thirty years now. The most advanced of these systems comprise means of alarm differing according to the maneuver to be performed by the pilot. It is of course vital that the recommended maneuver best guarantee the safety of the aircraft. The device according to the invention proposes a device comprising the calculation of several different safety surfaces or profiles. Their comparisons with the topographic data of the surrounding terrain make it possible to deduce therefrom the best alarm and the best maneuver to be performed to avoid the collision between the aircraft and the ground.

Abstract: The invention relates to aiding airport navigation by emission of an alert reminding the pilot of a craft moving on the surface of an airport of the circulation constraints encountered locally over his route. The method comprises the following steps: partitioning of the circulation surfaces of the airport into elementary circulation constraint zones each enclosing a set of adjoining points subject to the same local circulation constraints, identifications of the elementary zones and of their specific circulation constraints, detection of the encroachment of the craft into the elementary zones, and upon each encroachment of the craft into an elementary zone, reminder by alert generation, to the commander of the craft, of one at least of the circulation constraints specific to the elementary zone concerned.

Abstract: A method for evaluating the licitness of the situation of a craft on the surface of an airport including the steps of: modelling of a first licitness cost surface covering a surface of the airport where the craft is deploying, termed the deployment surface, related to this deployment surface and defined by quantities assigned to its points, which quantities are representative of their memberships in flow constraint zones and of the severity in relation to the craft, of the flow constraints, modelling of a second licitness cost surface covering the deployment surface, related to the craft and defined by quantities assigned to its points, which quantities are representative of their memberships in a girth zone covering a neighbourhood of the current position of the craft, and calculation of a score evaluating the significance of the risk of violation of a flow constraint incurred by the craft on the basis of a cross-correlation function of the two licitness cost surfaces referred to one and the same benchmark.

Abstract: This system ensures autonomous protection of an aircraft against deliberate crashes resulting from a malicious act of a person on board or a trajectory error. It comprises a prohibited zone anti-penetration (cons. anti-collision) rig OAPS (54) operating in the manner of a terrain anti-collision rig TAWS (51) but intervening at the level of the flight controls (12) so as to impose an avoidance trajectory on the aircraft (83) when the need therefor is felt. This prohibited zone anti-penetration (cons. anti-collision) rig OAPS (54) uses a database (60) holding information about the prohibited zones and a system for positioning (106, 306) of the aircraft (83). Supplemented with a terrain anti-collision rig TAWS (51) and a rig for protection of the limits of the flight domain FELPS (53), it makes it possible to produce a very complete flight protection system.

Abstract: Terrain anticollision equipment generally uses a display device showing a two-dimensional synthetic map of the terrain overflown by the aircraft and in which the relief is shown by superposed slices assigned false colors representative of the magnitude of the risk of collisions. The allocation of the false colors and/or the positions of the slices is referenced with respect to a reference display altitude related to the instantaneous altitude of the aircraft or to a short term forecast altitude for the aircraft, each of the referencings having its own advantages as a function of the situation in progress for the aircraft. Here it is proposed that the reference display altitude be made to vary, with gentle transitions, with no visible jerks on the screen, as a function of the aircraft's situation deduced from the flight parameters so as to have, at any moment for the crew, the most pertinent possible and the most useful possible map having regard to the instantaneous situation vis à vis the risks of collision.

Abstract: Terrain anticollision equipment generally uses a display device showing a two-dimensional synthetic map of the terrain overflown by the aircraft and in which the relief is shown by superposed slices assigned false colors representative of the magnitude of the risk of collisions. The allocation of the false colors and/or the positions of the slices is referenced with respect to a reference display altitude related to the instantaneous altitude of the aircraft or to a short term forecast altitude for the aircraft each of the referencings having its own advantages as a function of the situation in progress for the aircraft. Here it is proposed that the reference display altitude be made to vary, with gentle transitions, with no visible jerks on the screen, as a function of the aircraft's situation deduced from the flight parameters so as to have, at any moment for the crew, the most pertinent possible and the most useful possible map having regard to the instantaneous situation vis àvis the risks of collision.

Abstract: Conventional terrain anticollision equipment formulates, around the short term forecast trajectory of the aircraft which is equipped therewith, virtual volumes of protection of maneuver charted by feelers and signals a risk of terrain collision as soon as it detects an intrusion of the terrain into these virtual volumes of protection of maneuver.

Abstract: The invention concerns a device designed to be installed on board an aircraft to provide eventual warning data corresponding to a risk of collision between the aircraft and the landform. The device comprises an assist-module (4) designed to use static and dynamic parameters of the aircraft with a database of the relief of the terrain flown over (3), and a visual display module (5) for displaying (55) a representation of the relief over a displayed domain, and inserting therein a particular signalling of possible warnings in particular based on a detected landing/take-off phase state.

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

Abstract: A landing aid device comprises processing means, which receive aircraft path data, and data regarding the position of at least one runway towards which the aircraft is steering. These processing means comprise calculation means which supply a state signal, comprising at least one condition which is dependent on the path data and on the runway data, this function being chosen so as to express the fact that the path of the aircraft converges towards the runway.

Abstract: A device for aiding aerial navigation, carried on board an aircraft, receives on an input, status indications representing its spatial position and its velocity vector, and stores a 3D representation of the relief overflown. It comprises processing define, as a function of the status indications, an exploration sector referred to the aircraft, and calculate in this sector a contour as a function of the intersection of this sector with the relief, with a view to the displaying thereof. The sector is defined by a sheet of trajectory lines obtained on the basis of the velocity vector and of auxiliary vectors calculated by shifting the velocity vector of the aircraft according to a chosen angular scanning law.