Abstract: 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: a first step for acquiring at least one constraint relative to at least one parameter of the trajectory to be followed, the constraint being determined by a control system of a remote station as a function of the air traffic and/or the aircraft mission; a step for calculating a desired trajectory as a function of the constraint; a step for transmitting the desired trajectory to the remote station; a second step for acquiring an instruction comprising an authorization to follow the desired trajectory or a refusal of the desired trajectory.

Abstract: 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: a first step for acquiring at least one constraint relative to at least one parameter of the trajectory to be followed, the constraint being determined by a control system of a remote station as a function of the air traffic and/or the aircraft mission; a step for calculating a desired trajectory as a function of the constraint; a step for transmitting the desired trajectory to the remote station; a second step for acquiring an instruction comprising an authorization to follow the desired trajectory or a refusal of the desired trajectory.

Abstract: 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.

Abstract: 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 ?Ea between 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 hm(t) and of air speed Vam(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 ?Ea in a fixed required timespan ?trequired and a fixed required altitude variation tf?ti in the required time timespan, the aircraft operating permanently in an engine regime with constant and minimum thrust.

Abstract: 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 ?Ea between 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 hm(t) and of air speed Vam(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 ?Ea in a fixed required timespan ?trequired and a fixed required altitude variation tf?ti in the required time timespan, the aircraft operating permanently in an engine regime with constant and minimum thrust.

Abstract: 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.

Abstract: In order to transmit information between an emitting station and a receiving station separated by a distance exceeding the range of direct communications of said stations, the method according to the invention consists in equipping aerodynes, travelling in the space included between these two stations, with open communications relay systems of limited range which can momentarily interconnect, when within range of one another, in order to pass information from relay system to relay system up to its destination. The invention applies notably to air-to-ground communications for data links in the field of air transport.

Abstract: A command device which comprises a plurality of interactive command sources enabling any number of heterogeneous systems to be accessed, each command source being reconfigurable and having commands of a first type which cause the configuration of this source to change, and commands of a second type, specific to each of the configurations, and each system transmitting at the end of execution of the command information relating to the status of the system, on the one hand, perceptibly on the command sources situated in the configuration corresponding to the command that has just been executed, and, on the other hand, blindly in the memory spaces allocated to the command sources situated in other configurations. The invention applies notably to instrumentation in aerodyne cockpits.