초록 ▼

Navigation of an aircraft is facilitated through the displaying on a map of an over flown region, and of the limits of zones within range of the aircraft in an emergency situation. The points of the zones within range of the aircraft are tagged on the basis of: an estimate of the vertical margins to

Navigation of an aircraft is facilitated through the displaying on a map of an over flown region, and of the limits of zones within range of the aircraft in an emergency situation. The points of the zones within range of the aircraft are tagged on the basis of: an estimate of the vertical margins to reach these points, taking into account non-maneuverability zones neighboring the aircraft to be circumvented; a vertical flight profile to be complied with; and a safety height margin.

대표청구항 ▼

The invention claimed is: 1. A method of aiding navigation for aircraft comprises: rendering on a display a navigation map formulated on the basis of: database elements of terrain elements belonging to a same region of deployment; contours of out of range zones, the out of range zones being sets of

The invention claimed is: 1. A method of aiding navigation for aircraft comprises: rendering on a display a navigation map formulated on the basis of: database elements of terrain elements belonging to a same region of deployment; contours of out of range zones, the out of range zones being sets of points of the navigation map that are assigned an estimate of vertical margin of height, with respect to the flown over relief, below an arbitrary threshold height, the estimate of vertical margin based upon a map of vertical margins obtained by comparing a terrain altitude extracted from a database of terrain elevations and a scheduled altitude based upon a preset vertical flight profile that includes a minimum descent slope; wherein the map of vertical margins is generated on the basis of a map of curvilinear distances obtained by applying a propagation distance transform based upon the current position of the aircraft, non-maneuverable zones to be circumvented, and the preset vertical flight profile in compliance with the vertical margin threshold; wherein the non-maneuverable zones are situated in proximity to the current position of the aircraft, are determined as a function of inertia, heading, course, and speed of the aircraft, as well as the performance of the aircraft in case of engine failure, and wherein the non-maneuverable zones are delimited, to the right and to the left of the current position of the aircraft, by a ground projection of the tightest possible lateral turning trajectories that are acceptable for the aircraft having regard to an exceptional situation of engine failure and a minimum of aircraft occupant comfort. 2. The method according to claim 1, wherein the map of vertical margins is established on the basis of a map of curvilinear distances obtained by: applying a propagation distance transform to points of a working image derived from the terrain elevations database with a point in the neighborhood of the current position of the aircraft as an origin, static constraints including regulated overfly zones and non-maneuverable zones situated in the neighborhood of the current position of the aircraft, and a dynamic constraint comprising the preset vertical flight profile in compliance with the vertical margin threshold. 3. The method according to claim 1, further comprising: regarding as out of range zones sets of points of the curvilinear distance map that are assigned estimates of curvilinear distance exhibiting discontinuities with respect to points of the immediate neighborhood. 4. The method according to claim 1, applied to an aircraft equipped with a system for preventing ground collisions formulating avoidance solutions, in the method further comprising: comparing the lengths of the trajectories of the avoidance solutions proposed by the ground collisions prevention system with the estimates of curvilinear distances made during the application of the distance transform, so as to avoid additional obstacles. 5. The method according to claim 1, further comprising: supplementing the out of range zones with a lateral margin taking into account limitation to the freedom of lateral maneuver due to the possible presence of reliefs in the out of range zones. 6. The method according to claim 5, wherein the lateral margin has a width of five nautical miles. 7. The method according to claim 5, wherein the lateral margin has a width corresponding to the lateral-wise precision, of the trajectory tracking by the equipment onboard the aircraft. 8. The method according to claim 5, wherein the lateral margin has a width corresponding to the minimum lateral distance allowing the aircraft to describe a diversion aerodrome. 9. The method according to claim 1, wherein the contours of the out of range zones include an external margin delimiting the neighborhoods of the out of range zones where the aircraft affected by an engine failure does not have complete freedom of lateral deployment. 10. The method according to claim 1, further comprising endowing the contours of the out of range zones with a textured wire-like representation. 11. The method according to claim 10, further comprising endowing the contours of the out of range zones with interior and exterior borders of different aspects. 12. The method according to claim 1, further comprising superimposing the contours of the out of range zones on zones determined by a ground collision prevention system as representing a danger. 13. The method according to claim 1, wherein determining the non-maneuverable zones on either side of the current position of the aircraft includes determining cycloidal arcs of a ground trace of each of two tightest right and left lateral turns permitted by a residual performance of the aircraft in case of an engine failure.