Abstract: A system for controlling aircraft flight control surfaces implements a method including: obtaining a control law for the flight control surfaces as a function of flight controls of the aircraft; obtaining measurements of ground speed, true speed, roll angle, pitch angle, angle of attack, sideslip angle and slope angle; performing an estimation of the wind in three dimensions using the measurements obtained; performing an adjustment of the control law for the flight control surfaces, to counter the estimated wind effect and to obtain an adjusted control law for the flight control surfaces, by adding, to the control law, a term for wind compensation comprising a term proportional to the derivative of the wind estimation; and controlling the aircraft by applying the adjusted control law. Thus, the impact of the wind on the aircraft is reduced by digital processing and automatic adjustment of the control of the flight control surfaces.

Abstract: Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

Abstract: Method and device for controlling the path of a following aircraft with respect to a leading aircraft where the aircraft fly in formation. The device includes a data reception unit configured to receive an item of risk of collision information relating to the leading aircraft, a calculating unit configured to determine at least one what is termed safety position when an item of risk of collision information is received, the safety position corresponding to a position in which the following aircraft is not subjected to effects of vortices generated by the leading aircraft, and a control unit configured to bring the following aircraft into the safety position as soon as the calculating unit has determined the safety position.

Abstract: A method and device for monitoring and controlling a path of a following aircraft (AC2) with respect to vortices (V1, V2) generated by a leading aircraft (AC1) while both aircraft (AC1, AC2) fly in a formation (F), wherein the device includes a unit for determining, using a vortex transport model, a safety position (PS) at which the following aircraft (AC2) is not subjected to effects of the vortices (V1, V2) generated by the leading aircraft (AC1), a unit for determining, using a vortex signature model, an optimum position (PO) at which the following aircraft (AC2) benefits from at least one (V1) of the vortices (V1, V2), and a control unit for bringing and keeping the following aircraft (AC2) in the safety position (PS) while a predetermined condition(s) is met and otherwise for bringing the following aircraft (AC2) and keeping it in the optimum position (PO).

Abstract: Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

Abstract: System and method for controlling trajectory of an aircraft. The control system includes a position determination module to determine a safety position corresponding to a position in which a follower aircraft is not subject to effects of the right-hand and left-hand vortices generated by a leader aircraft while remaining in formation flight, a protection module to convey and to maintain the follower aircraft to/in the safety position when the follower aircraft comprises a wing tip located in a position that has a right-hand vortex signature that is less than or equal to a first predetermined signature or that has a left-hand vortex signature that is greater than or equal to the first predetermined signature or that has a right-hand vortex signature that is greater than or equal to a second predetermined signature or that has a left-hand vortex signature that is less than or equal to the second predetermined signature.

Abstract: A method of assisting the piloting of an aircraft having at least one actuator acting on a control member. The aircraft has a main measurement system and a secondary measurement system respectively determining at least one predicted value and at least one measured value of a parameter that is used in at least one flight-control law. A filter unit is used to estimate an estimated value of at least one parameter with the help of the predicted and measured values, and for estimating at least one measurement accuracy margin. Each measurement accuracy margin is compared with a corresponding threshold, and the flight-control law that is to be applied is selected as a function of the comparison.

Abstract: A method for anticipating displacement of a wake vortex from a leading aircraft, implemented by a flight management system of a following aircraft, flying in the wake of the leading aircraft. The method establishes formation flight, in which the flight management system defines a flight plan in which the following aircraft flies and places itself at a predetermined distance from a center of a wake vortex. In a step of reception of inertial parameters, a flight management system of the following aircraft formulates a request for inertial parameters of the leading aircraft and receives, via exchange of signals, the inertial parameters of the leading aircraft. In a decision-making step, the flight management system assesses possibility of trajectory of the following aircraft crossing that of the wake vortex and modifies the following aircraft flight plan if it estimates that the trajectory of the following aircraft crosses that of a wake vortex.

Abstract: Method and device for monitoring the position of a following aircraft with respect to a leading aircraft during a formation flight. The device includes a module for determining a position of the leading aircraft based on a flight parameter coming from a first source, a module for determining a position of the following aircraft based on a flight parameter coming from another first source, modules for determining first and second relative positions of the following aircraft with respect to the leading aircraft based on flight parameters coming from second sources separate from the first sources, a module for comparing the first and second relative positions, and a module for transmitting, depending on the result of the comparison, to a control unit of the following aircraft, a control order either for keeping the following aircraft in an optimum position or for bringing it into a safety position.

Abstract: Method and device for controlling the path of a following aircraft with respect to a leading aircraft where the aircraft fly in formation. The device includes a data reception unit configured to receive an item of risk of collision information relating to the leading aircraft, a calculating unit configured to determine at least one what is termed safety position when an item of risk of collision information is received, the safety position corresponding to a position in which the following aircraft is not subjected to effects of vortices generated by the leading aircraft, and a control unit configured to bring the following aircraft into the safety position as soon as the calculating unit has determined the safety position.

Abstract: A method and device for monitoring and controlling a path of a following aircraft (AC2) with respect to vortices (V1, V2) generated by a leading aircraft (AC1) while both aircraft (AC1, AC2) fly in a formation (F), wherein the device includes a unit for determining, using a vortex transport model, a safety position (PS) at which the following aircraft (AC2) is not subjected to effects of the vortices (V1, V2) generated by the leading aircraft (AC1), a unit for determining, using a vortex signature model, an optimum position (PO) at which the following aircraft (AC2) benefits from at least one (V1) of the vortices (V1, V2), and a control unit for bringing and keeping the following aircraft (AC2) in the safety position (PS) while a predetermined condition(s) is met and otherwise for bringing the following aircraft (AC2) and keeping it in the optimum position (PO).

Abstract: A method of assisting the piloting of an aircraft having at least one actuator acting on a control member. The aircraft has a main measurement system and a secondary measurement system respectively determining at least one predicted value and at least one measured value of a parameter that is used in at least one flight-control law. A filter unit is used to estimate an estimated value of at least one parameter with the help of the predicted and measured values, and for estimating at least one measurement accuracy margin. Each measurement accuracy margin is compared with a corresponding threshold, and the flight-control law that is to be applied is selected as a function of the comparison.