Thales

Cédric D'Silva

Jérôme Sacle

Nicolas Rossi

Benoît Dacre-Wright

A method for determining an optimized trajectory to be followed by an aircraft, the method being implemented by a determining system of the aircraft and comprising:

Method for determining an optimized trajectory to be followed by an aircraft, associated control method, computer program product and systems

An aid method for piloting an aircraft including acquiring an instruction intended to alter the flight plan, determining an applicability period of the instruction made up of a plurality of applicability moments of the instruction in which the application of the instruction is compatible with the operational capabilities of the aircraft and with the constraints of the flight plan, for each applicability moment of the instruction, determining an altered flight plan in case of application of the instruction at this applicability moment and calculating values of the operational parameters associated with this flight plan, and selecting an optimal applicability moment based on values of the operational parameters associated with the altered flight plan and operational parameters associated with the current flight plan.

Aid method for piloting an aircraft, associated computer progam product and aid device for piloting

A method for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft comprises a first step of computing an energy differential of the aircraft in the air &#x394;Ebetween a first initial state of the aircraft at an initial geodesic point Qi and a second final state of the aircraft at the final arrival target point Qf. The method comprises a second step of adjusting an adjustable modelled profile of altitude h(t) and of air speed Va(t) of the aircraft with the aid of parameters so the adjusted modelled profile of altitude h(t) and of air speed Va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air &#x394;Ein a fixed required timespan &#x394;tand a fixed required altitude variation t&#x2212;tin the required time timespan, the aircraft operating permanently in an engine regime with constant and minimum thrust. The method comprises a third step of determining a lateral geodesic trajectory of the aircraft on the basis of the adjusted altitude profile h(t), of the adjusted air speed profile Va(t) and of the knowledge of the speeds of the winds in the aircraft's scheduled geographical traversal zone.

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Toulouse, France

Cédric D'Silva