초록 ▼

A method for assisting low-altitude navigation of an aircraft equipped with a system suited to determine a flight-plan ground trajectory based on intermediate points P at an altitude alt(P), and the aircraft's performance. The method includes the following steps: for each point P, calculating a safe

A method for assisting low-altitude navigation of an aircraft equipped with a system suited to determine a flight-plan ground trajectory based on intermediate points P at an altitude alt(P), and the aircraft's performance. The method includes the following steps: for each point P, calculating a safe altitude, to obtain a point Psafe, calculating a safe profile formed from segments joining the points Psafe, extracting summits S from among the points Psafe, determining the aircraft's weight at these points S, for each point S, determining the maximum climb slope MaxClimbFPA and the maximum descent slope MaxDescFPA, defining two performance segments which have slopes MaxClimbFPA and MaxDescFPA on either side of the point S and calculating a performance profile formed from performance segments.

대표청구항 ▼

The invention claimed is: 1. A method of assisting low-altitude navigation of an aircraft equipped with a flight management system suited to determining a flight-plan ground trajectory for the aircraft based on a sequence of straight and/or curved segments joining intermediate points on the ground

The invention claimed is: 1. A method of assisting low-altitude navigation of an aircraft equipped with a flight management system suited to determining a flight-plan ground trajectory for the aircraft based on a sequence of straight and/or curved segments joining intermediate points on the ground P at an altitude alt(P), where the ground trajectory takes into consideration the aircraft's performance and limitations, comprising the following steps: for each point P on the ground trajectory, calculating a safe altitude, alt safe, to obtain a point Psafe such that alt safe (Psafe)=Max[alt(P+lat mrg R), alt(P+lat mrg L)]+vert mrg, where lat mrg R and lat mrg L are respectively predetermined right and left lateral margins and vert mrg is a predetermined vertical margin, calculating a safe profile formed from safe segments joining the points Psafe, extracting summit points S from among the points Psafe of the safe profile such that the K points located before S and after S have a safe altitude below that of S, K being a determined parameter, determining the aircraft's weight at these points S as a function of the distance along the safe profile between the aircraft and this point S and of the aircraft's consumption over this distance, where the consumption is an aspect of 'the aircraft's performance and limitations, for each point S, determining the maximum climb slope (MaxClimbFPA) that the aircraft can support to reach S and the maximum-descent slope (MaxDescFPA) which the aircraft can support for following the lowest ground trajectory after having passed through S as a function of the aircraft's performance and limitations and the weight, defining two performance segments which have a first end at S, slopes MaxClimbFPA and MaxDescFPA on either side of the point S and a second end at the point of intersection with the terrain or with another performance segment arising from another point S and calculating a performance profile formed from performance segments and which makes it possible to associate at each point P of the safe profile a performance altitude, alt perf (P). 2. The method of assisting navigation as claimed in claim 1, further comprising determining a flyable low-altitude profile based on the safe profile and the performance profile. 3. The method of assisting navigation as claimed in claim 1, wherein the determination of the flyable low-altitude profile includes calculating for each point P of the ground trajectory a low-altitude flight altitude, alt flight, for obtaining a point Pflight such that alt flight(Pflight)=Max[alt safe (P),alt perf (P)], where the flyable low-altitude profile is formed from segments joining the points Pflight. 4. The method of assisting navigation as claimed in claim 1, comprising sampling the points P according to a step p, and in that K is determined as a function of p and/or a threshold slope and the terrain and/or aircraft performance and limitations. 5. The method of assisting navigation as claimed in claim 1, wherein since the flight management system has an estimated position uncertainty, lat mrg R and L are determined as a function of the aircraft's performance and limitations, and of the estimated position uncertainty. 6. The method of assisting navigation as claimed in claim 1, wherein since the flight management system has the wind speed and direction, aircraft speed, altitude of the terrain, and local temperature, the slopes MaxClimbFPA and MaxDescFPA are weighted as a function of the wind speed and direction and aircraft speed and altitude of the terrain and/or local temperature. 7. The method of assisting navigation as claimed in claim 2, wherein since the flight management system has the wind speed and direction, aircraft speed, altitude of the terrain, and local temperature, the slopes MaxClimbFPA and MaxDescFPA are weighted as a function of the wind speed and direction and/or aircraft speed and/or altitude of the terrain and local temperature. 8. The method of assisting navigation as claimed in claim 3, wherein since the flight management system has the wind speed and direction, aircraft speed, altitude of the terrain, and local temperature, the slopes MaxClimbFPA and MaxDescFPA are weighted as a function of the wind speed and direction and/or aircraft speed and/or altitude of the terrain and local temperature. 9. The method of assisting navigation, as claimed in claim 4, wherein since the flight management system has the wind speed and direction, aircraft speed, altitude of the terrain, and local temperature, the slopes MaxClimbFPA and MaxDescFPA are weighted as a function of the wind speed and direction and/or aircraft speed and/or altitude of the terrain and local temperature. 10. The method for assisting navigation as claimed in claim 5, wherein since the flight management system has the wind speed and direction, aircraft speed, altitude of the terrain, and local temperature, the slopes MaxClimbFPA and MaxDescFPA are weighted as a function of the wind speed and direction and/or aircraft speed and/or altitude of the terrain and local temperature. 11. The method of assisting navigation as claimed in claim 1, wherein since the aircraft is equipped with the engines, the slope MaxClimbFPA is calculated assuming an engine failure. 12. The method of assisting navigation as claimed in claim 2, wherein since the aircraft is equipped with the engines, the slope MaxClimbFPA is calculated assuming an engine failure. 13. The method of assisting navigation as claimed in claim 3, wherein since the aircraft is equipped with the engines, the slope MaxClimbFPA is calculated assuming an engine failure. 14. The method of assisting navigation as claimed in claim 4, wherein since the aircraft is equipped with the engines, the slope MaxClimbFPA is calculated assuming an engine failure. 15. The method of assisting navigation as claimed in claim 1, wherein the flight management system being connected to a terrain database composed of grids having a predetermined width L, and comprising information on the terrain's slope, it involves sampling the points P according to a step p determined as a function of the terrain's slope and the width L of the grids. 16. The method of assisting navigation as claimed in claim 2, wherein the flight management system being connected to a terrain database composed of grids having a predetermined width L, and comprising information on the terrain's slope, it involves sampling the points P according to a step p determined as a function of the terrain's slope, and the width L of the grids. 17. The method of assisting navigation as claimed in claim 3, wherein the flight management system being connected to a terrain database composed of grids having a predetermined width L, and comprising information on the terrain's slope, it involves sampling the points P according to a step p determined as a function of the terrain's slope, and the width L of the grids. 18. The method of assisting navigation as claimed in claim 4, wherein the flight management system being connected to a terrain database composed of grids having a predetermined width L, and comprising information on the terrain's slope, it involves sampling the points P according to a step p determined as a function of the terrain's slope, and the width L of the grids. 19. The method of assisting navigation as claimed in claim 2, wherein since a transition parabola is associated with the segments SegClimb and SegDesc of the flyable profile arising from a summit S, and since the top of the parabola is situated at ΔH from S, it consists in: calculating a new summit S' located at ΔH above the summit S; raising the transition parabola by ΔH; and defining segments SegClimb' and SegDesc' arising from S' in a manner such that they are tangent to the raised transition parabola and obtain a new flyable profile. 20. A flight management system for an aircraft comprising a central unit which communicates with an input-output interface, a program memory, a working memory, and a data storage memory, by means of data-transfer circuits, the input-output interface being connected to a database of the terrain to be flown over, wherein the program memory includes a program for implementing the method as claimed in claim 1.