Abstract: An aircraft mission calculation system is configured to calculate an environmental benefit index. The system includes an aircraft trajectory calculation engine, able to calculate at least one potential mission trajectory between a geographic point of origin and a geographic point of destination. The aircraft trajectory calculation engine comprises an environmental benefit index calculation module, able to activate the calculation engine. The environmental benefit index calculation module is able to determine an environmental benefit index (GI) of the potential trajectory from the first amount of carbon dioxide (Q1(TR1)) produced on a first reference trajectory defining a fastest mission, the second amount of carbon dioxide produced on a second reference trajectory (Q2(TR2)), defining a mission minimizing the amount of carbon dioxide produced, and the potential amount of carbon dioxide produced on the potential trajectory.

Abstract: An aircraft mission calculation system is for indicating a risk of loss of optimality of the trajectory actually flown by the aircraft. The system includes a first trajectory calculation module, configured to calculate an optimal mission trajectory between a geographical point of origin and a geographical point of destination. The first calculation module is configured to calculate a plurality of iso-displacement curves from the geographical point of origin to the geographical point of destination. The system comprises a module for determining a level of risk of loss of optimality of the trajectory actually taken by the aircraft, associated with a modification of the trajectory of the aircraft with respect to the calculated mission trajectory, the display manager displaying on the display, in addition to the calculated trajectory, an indicator of the determined level of risk.

Abstract: An aircraft mission calculation system is configured to calculate an environmental benefit index. The system includes an aircraft trajectory calculation engine, able to calculate at least one potential mission trajectory between a geographic point of origin and a geographic point of destination. The aircraft trajectory calculation engine comprises an environmental benefit index calculation module, able to activate the calculation engine. The environmental benefit index calculation module is able to determine an environmental benefit index (GI) of the potential trajectory from the first amount of carbon dioxide (Q1(TR1)) produced on a first reference trajectory defining a fastest mission, the second amount of carbon dioxide produced on a second reference trajectory (Q2(TR2)), defining a mission minimizing the amount of carbon dioxide produced, and the potential amount of carbon dioxide produced on the potential trajectory.

Abstract: Aircraft mission calculation system includes a first calculator configured to calculate a plurality of iso-displacement curves from a selected point, at a displacement range corresponding to several successive displacement increments of the aircraft from the selected point, the iso-displacement curves being obtained at the displacement range for a displacement of the aircraft to a given flight level from displacements of the aircraft at distinct flight altitude levels. The first calculator is configured to determine, based on iso-displacement curves up to the given flight level, obtained at distinct flight altitude levels, taken at the same displacement range of the aircraft, an extended iso-displacement curve at the given flight level maximizing the displacement of the aircraft from the geographical point of origin or minimizing the displacement of the aircraft toward the geographical destination point.

Abstract: Aircraft mission calculation system includes a first calculator configured to calculate a plurality of iso-displacement curves from a selected point, at a displacement range corresponding to several successive displacement increments of the aircraft from the selected point, the iso-displacement curves being obtained at the displacement range for a displacement of the aircraft to a given flight level from displacements of the aircraft at distinct flight altitude levels. The first calculator is configured to determine, based on iso-displacement curves up to the given flight level, obtained at distinct flight altitude levels, taken at the same displacement range of the aircraft, an extended iso-displacement curve at the given flight level maximizing the displacement of the aircraft from the geographical point of origin or minimizing the displacement of the aircraft toward the geographical destination point.

Abstract: A system for calculating a mission of an aircraft by combination of algorithms includes a first path calculation module, configured for calculating an optimal mission path between a geographical point of origin and a geographical destination point as a function of airplane performance, operational mission specifications and a weather context. The first calculation module is configured to determine the optimal path in a manner non constrained by a network of waypoints and/or imposed paths between the waypoints. The system includes a definition module, around the optimal path, an optimization region of the path and a second path calculating module, configured to calculate an optimized path of the aircraft in the optimization region in a manner constrained by a network of waypoints and/or imposed paths between the waypoints.