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1.发明申请公开(公告)号：US20180308369A1
公开(公告)日：2018-10-25
申请号：US15957329
申请日：2018-04-19
Applicant: Airbus Operations S.A.S.
Inventor： Jean-luc Robin
CPC classification number: G08G5/0008 , G01S2205/005 , G05D1/104 , G08G5/0021 , G08G5/0078 , G08G5/0091 , G08G5/04 , G08G5/045
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.
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2.发明授权公开(公告)号：US10380903B2
公开(公告)日：2019-08-13
申请号：US15445506
申请日：2017-02-28
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Jean-luc Robin , Camille Caruhel , Sylvain Deplanche
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.
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公开(公告)号：US10170009B2
公开(公告)日：2019-01-01
申请号：US15950111
申请日：2018-04-10
Applicant: Airbus Operations (S.A.S.)
Inventor： Mathieu Hiale-Guilhamou , Jean-luc Robin
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.
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公开(公告)号：US10347143B2
公开(公告)日：2019-07-09
申请号：US15491771
申请日：2017-04-19
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Jean-luc Robin , Camille Caruhel , Sylvain Deplanche
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.
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公开(公告)号：US20190041876A1
公开(公告)日：2019-02-07
申请号：US16051216
申请日：2018-07-31
Applicant: Airbus Operations (S.A.S.)
Inventor： Jean-luc Robin , José Torralba , Julie Lebas
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.
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Patent Agency Ranking
公开(公告)号：US11467607B2
公开(公告)日：2022-10-11
申请号：US16369214
申请日：2019-03-29
Applicant: Airbus Operations (S.A.S.)
Inventor： Jean-luc Robin , José Torralba , Julie Lebas
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.
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公开(公告)号：US20190041875A1
公开(公告)日：2019-02-07
申请号：US16051143
申请日：2018-07-31
Applicant: Airbus Operations (S.A.S.)
Inventor： José Torralba , Jean-luc Robin , Julie Lebas
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.
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公开(公告)号：US20190310642A1
公开(公告)日：2019-10-10
申请号：US16369214
申请日：2019-03-29
Applicant: Airbus Operations (S.A.S.)
Inventor： Jean-luc Robin , José Torralba , Julie Lebas
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.
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公开(公告)号：US20190302808A1
公开(公告)日：2019-10-03
申请号：US16363156
申请日：2019-03-25
Applicant: Airbus Operations (S.A.S.)
Inventor： Jean-luc Robin , José Torralba , Julie Lebas
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.
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10.发明授权公开(公告)号：US10319238B2
公开(公告)日：2019-06-11
申请号：US15957329
申请日：2018-04-19
Applicant: Airbus Operations S.A.S.
Inventor： Jean-luc Robin
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.
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