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: 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: Collision avoidance method and device for an aircraft formation relative to an intrusive aircraft. The device manages a collision avoidance for an aircraft formation, relative to an aircraft external to the aircraft formation, the aircraft formation comprising a lead aircraft and at least one following aircraft, the device comprising a formation flight management unit with which all the aircraft of the aircraft formation are equipped and configured to manage the formation flight thereof, and management and control assemblies for determining and applying a coordinated avoidance maneuver intended for all the aircraft of the aircraft formation, this coordinated avoidance maneuver being determined so as to make it possible to avoid the collision with the intrusive aircraft while maintaining the formation flight.

Abstract: A collision avoidance method and system for a trailer aircraft of an aircraft formation relative to an intruder aircraft. The collision avoidance system is embedded in a trailer aircraft of an aircraft formation and it is intended to avoid a collision relative to at least one aircraft external to the aircraft formation, called intruder aircraft, the aircraft formation including a lead aircraft and the at least one trailer aircraft, the collision avoidance system being configured to bring the trailer aircraft to a safety point dependent on a safety zone, prior to the implementation of an avoidance maneuver, the safety zone corresponding to a zone located to the rear of the lead aircraft and with no wake turbulence generated by the lead aircraft.

Abstract: A method for transmitting flight parameters from a leading aircraft (L) to at least one intruding aircraft (I), wherein, the transmission is effected by a collision avoidance system of TCAS type. The transponder of the leading aircraft (L) is configured to measure the spectrum of an interrogation signal received from the intruding aircraft (I) and to compare the power of the spectrum to a threshold power. If the power of the interrogation signal is greater than or equal to the threshold power, then the intruding aircraft (I) is eligible to receive flight parameters from the leading aircraft to be able to compute the position of the centers or the force of circulation of wake vortexes (14L, 15L) generated by the leading aircraft (L). The exchange of flight parameters from the leading aircraft only to eligible intruding aircraft makes it possible to not exceed the maximum automated communication bandwidth capacity.

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 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: 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: A method for transmitting flight parameters of a lead aircraft to an intruder aircraft. Transmission includes a collision avoidance system connected to which is a flight parameter transmission authorization system having a database including coordinates defining a volume of confidence smaller than the monitoring volume. The flight parameter transmission authorization system of the lead aircraft authorizes, only for an intruder aircraft identified as flying within the volume of confidence, transmission of at least one flight parameter of the lead aircraft, such that this intruder aircraft is able to calculate the position of centers of wake vortices generated by the lead aircraft or the flow strength of the wake vortices. Exchanging flight parameters of the lead aircraft only with intruder aircraft flying within the volume of confidence with limited dimensions makes it possible not to exceed the maximum capacity of the bandwidth of the automated communication.

Abstract: A method and system for controlling the transmission of power of request-response messages implemented by a system to prevent collisions between a first aircraft and a second aircraft. The method comprises measuring at least the value, referred to as the quality value, of a quantity representative of the reception quality of the transponder of the second aircraft and, implemented by the anti-collision device of the first aircraft, and a control step to control the transmission power of the radio-frequency signals carrying the request-response messages according to the quality value or values contained in the response messages sent by the transponder.

Abstract: A method and system for controlling message transmission power implemented by a system for preventing collisions of aircraft during flight, the prevention system comprising an anti-collision device and a transponder with which each plane is equipped. There is a step for measuring at least the quality value of a quantity representative of the quality at which radio-frequency signals carrying response messages transmitted by a transponder of an intruding aircraft are received, and a step for controlling the power of transmission of the radio-frequency signals carrying the response messages depending o the quality value or values measured in this way.

Abstract: A method for transmitting flight parameters from a leading aircraft (L) to at least one intruding aircraft (I), wherein, the transmission is effected by a collision avoidance system of TCAS type. The transponder of the leading aircraft (L) is configured to measure the spectrum of an interrogation signal received from the intruding aircraft (I) and to compare the power of the spectrum to a threshold power. If the power of the interrogation signal is greater than or equal to the threshold power, then the intruding aircraft (I) is eligible to receive flight parameters from the leading aircraft to be able to compute the position of the centres or the force of circulation of wake vortexes (14L, 15L) generated by the leading aircraft (L). The exchange of flight parameters from the leading aircraft only to eligible intruding aircraft makes it possible to not exceed the maximum automated communication bandwidth capacity.

Abstract: A method for transmitting flight parameters of a lead aircraft to an intruder aircraft. Transmission includes a collision avoidance system connected to which is a flight parameter transmission authorization system having a database including coordinates defining a volume of confidence smaller than the monitoring volume. The flight parameter transmission authorization system of the lead aircraft authorizes, only for an intruder aircraft identified as flying within the volume of confidence, transmission of at least one flight parameter of the lead aircraft, such that this intruder aircraft is able to calculate the position of centers of wake vortices generated by the lead aircraft or the flow strength of the wake vortices. Exchanging flight parameters of the lead aircraft only with intruder aircraft flying within the volume of confidence with limited dimensions makes it possible not to exceed the maximum capacity of the bandwidth of the automated communication.

Abstract: A method and system for controlling the transmission of power of request-response messages implemented by a system to prevent collisions between a first aircraft and a second aircraft. The method comprises measuring at least the value, referred to as the quality value, of a quantity representative of the reception quality of the transponder of the second aircraft and, implemented by the anti-collision device of the first aircraft, and a control step to control the transmission power of the radio-frequency signals carrying the request-response messages according to the quality value or values contained in the response messages sent by the transponder.

Abstract: Collision avoidance method and device for an aircraft formation relative to an intrusive aircraft. The device manages a collision avoidance for an aircraft formation, relative to an aircraft external to the aircraft formation, the aircraft formation comprising a lead aircraft and at least one following aircraft, the device comprising a formation flight management unit with which all the aircraft of the aircraft formation are equipped and configured to manage the formation flight thereof, and management and control assemblies for determining and applying a coordinated avoidance maneuver intended for all the aircraft of the aircraft formation, this coordinated avoidance maneuver being determined so as to make it possible to avoid the collision with the intrusive aircraft while maintaining the formation flight.

Abstract: A collision avoidance method and system for a trailer aircraft of an aircraft formation relative to an intruder aircraft. The collision avoidance system is embedded in a trailer aircraft of an aircraft formation and it is intended to avoid a collision relative to at least one aircraft external to the aircraft formation, called intruder aircraft, the aircraft formation including a lead aircraft and the at least one trailer aircraft, the collision avoidance system being configured to bring the trailer aircraft to a safety point dependent on a safety zone, prior to the implementation of an avoidance maneuver, the safety zone corresponding to a zone located to the rear of the lead aircraft and with no wake turbulence generated by the lead aircraft.

Abstract: Redundant storage devices in particular suitable for so-called SSD electronic disks. A data storage system is proposed based on a plurality of redundant physical storage disks in which the read/write commands intended to be sent to the redundant disks are subjected to a transfer function before being sent to at least one of the disks so that the actual commands sent to at least two disks are different. The values returned by the disks that received the commands that had undergone the transfer function are subjected to the inverse transfer function. Thus, a design error in the control module of the disks will be detected, since the control modules of the disks will not be called identically.

Abstract: A data processing apparatus includes a processing unit having first and second modes of operation for processing data, including receiving data packets from a sender and sending acknowledgements to the sender the second mode of operation requires more power than the first mode, and the processing unit switches between the first and second modes of operation based on a processing load; a metric module for determining a metric indicative of the processing load; an acknowledgement module for sending one acknowledgement in respect of n received data packets; and an acknowledgement configuration module for setting n to be a value m greater than a first predetermined value if the metric lies in a predetermined range that includes a value that the metric assumes when the processing unit switches between the first mode of operation and the second mode of operation, and to the first predetermined value otherwise.