EP2463845B1 - Procédé et dispositif pour aider à l'évaluation visuelle d'une trajectoire de vol destinée à être suivie par un aéronef dans un environnement contraint - Google Patents

Procédé et dispositif pour aider à l'évaluation visuelle d'une trajectoire de vol destinée à être suivie par un aéronef dans un environnement contraint Download PDF

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Publication number
EP2463845B1
EP2463845B1 EP11191208.5A EP11191208A EP2463845B1 EP 2463845 B1 EP2463845 B1 EP 2463845B1 EP 11191208 A EP11191208 A EP 11191208A EP 2463845 B1 EP2463845 B1 EP 2463845B1
Authority
EP
European Patent Office
Prior art keywords
trial
aircraft
points
obstacles
database
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP11191208.5A
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German (de)
English (en)
French (fr)
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EP2463845A1 (fr
Inventor
Andrea Giovannini
Thomas Pastre
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
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Airbus Operations SAS
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Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP2463845A1 publication Critical patent/EP2463845A1/fr
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Publication of EP2463845B1 publication Critical patent/EP2463845B1/fr
Not-in-force legal-status Critical Current
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    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0017—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information
    • G08G5/0021—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information located in the aircraft
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0073—Surveillance aids
    • G08G5/0078—Surveillance aids for monitoring traffic from the aircraft
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0073—Surveillance aids
    • G08G5/0086—Surveillance aids for monitoring terrain
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0073—Surveillance aids
    • G08G5/0091—Surveillance aids for monitoring atmospheric conditions

Definitions

  • the present invention relates to a method and a device for assisting the evaluation of a flight path intended to be followed by an aircraft, in particular a transport aircraft, in a constrained environment.
  • constrained environment is understood to mean an environment (or zone of the space of given shape and size) which is defined around the position of the aircraft and which is capable of containing objects ( or obstacles), with which the aircraft must avoid colliding, in particular for obvious reasons of safety or simply for reasons of comfort of the flight, these objects being able to be fixed objects such as mountains or hills or else mobile (or dynamic) objects such as areas of weather disturbance, particularly stormy areas, or other aircraft.
  • the present invention applies to any type of flight path that is intended to be followed by an aircraft. It may be, in particular, a flight path transmitted by the flight management system of the aircraft or by another conventional system capable of providing a prediction of the geometry of the future trajectory. It can also be a filed flight plan or a trajectory generated during the flight phase.
  • the object of the present invention is to enable the pilots of the aircraft to evaluate the validity of the flight path considered in a dynamic environment (with a stormy zone or other aircraft operating in the same space for example) for the purpose in particular, to support the crew in their decision-making on board in such a constrained environment.
  • WO 2005/057133 or FR 2923008 provide examples of forecast representations on a flight plan.
  • ND Navigation Display
  • the present invention aims to overcome these disadvantages. It relates to a method for aiding the crew of an aircraft, in particular a transport aircraft, to evaluate any flight path that is intended to be followed by that aircraft in a constrained environment, that is, say in an environment that may contain fixed and mobile obstacles.
  • a display is provided showing an area free of obstacles around a flight path that is defined in a dynamic environment.
  • This free zone illustrates the possible margin of maneuver of the aircraft over the entire flight path.
  • the display of this area on a cockpit display screen thus helps the crew, and particularly the pilot (s), to make a very rapid assessment of the complexity of the piloting on the trajectory considered. .
  • the present invention therefore provides a single display that represents all the evolutions of the environment with respect to the flight path in a given time window.
  • said collision test and more generally the invention, in a horizontal (lateral) plane or in a vertical plane.
  • the invention is implemented simultaneously in the horizontal and vertical planes so as to determine and provide a free zone which is defined throughout the space around the flight path considered.
  • the present invention also relates to a device for aiding the crew of an aircraft, in particular a transport aircraft, to evaluate any flight path that is intended to be followed by this aircraft in a constrained environment. in an environment that may contain fixed and mobile obstacles.
  • the device according to the invention makes it possible to represent the complexity of an evolving environment (situation in which the extrapolation capacity of the pilot is not sufficient to represent time-dependent spatial freedom) by a simple display, the information main being the zone of freedom (called free zone) which is associated with the flight path in dynamic environment. Said device thus helps the crew of the aircraft in the evaluation and validation of its flight paths in a constrained environment.
  • the present invention also relates to an aircraft, in particular a transport aircraft, which is provided with a help device, such as that mentioned above.
  • the device 1 is intended to assist the crew of an aircraft (not shown), particularly a transport aircraft, to evaluate any flight path TV which is intended to be followed by this aircraft in a constrained environment.
  • constrained environment is meant an environment which is likely to contain objects or obstacles O1, O2, with which the aircraft must avoid colliding, in particular for obvious reasons of safety or simply for reasons of comfort of the flight. .
  • These obstacles may be fixed obstacles O1 such as mountains or hills, or moving (or dynamic) obstacles 02 such as areas of weather disturbance, particularly stormy areas, or other aircraft.
  • the device 1 provides a display ( Figures 7 and 8 ) highlighting a ZL area that is free of any obstacles around a TV flight path that is set in a dynamic environment.
  • This free zone ZL illustrates the possible margin of maneuver of the aircraft over the entire flight trajectory TV.
  • the display of this zone ZL on a visualization screen 14 of the cockpit thus makes it possible to help the crew, and in particular the pilot (s), to carry out a very rapid evaluation of the complexity of the piloting on the flight deck. TV trajectory considered.
  • the invention is implemented simultaneously in the horizontal and vertical planes so as to determine and provide a free zone ZL which is defined in the entire space around the flight trajectory TV considered.
  • the processing unit 6 proceeds iteratively. It provides a number of distinct positions (test points Pt) on the TV trajectory according to a predefined increment. For each of these positions, it provides an estimate of the transit time, based on the predictions made by a flight management system, for example, part of the set 2. It then generates a representation of the environment at the time estimated, this representation being used as a reference for measuring the critical distances with respect to the obstacles O1 02.
  • the display of all the critical points Pc for each of the positions (test points Pt) on the TV trajectory allows the representation, in a single display, potential evolutions of the environment with respect to the trajectory inscribed in a temporal window.
  • the base of fixed obstacles contains discretizations of obstacles O1.
  • the representation is a polygonal ground projection associated with a limiting height.
  • the dynamic bases 3, 4 integrate, for their part, additional information concerning the evolution of the zones.
  • the information is produced by an analysis of the recent evolution of the zones (analysis of weather monitoring or data transmitted by data transmission link for example). This analysis produces, for each construction point A1 to A6 (called the determining point) of the polygonal surface S1 (forming the moving object or obstacle 02), a measured mean displacement vector V1 to V6, as shown in FIG. figure 2 . On this figure 2 a velocity vector V0 of the wind has also been highlighted.
  • said means 15 automatically determine, as test points Pt, successive points along the flight trajectory TV, which are separated from each other, each time, by a constant distance D, as represented on FIG. figure 3 .
  • This distance D can be predetermined, or else be chosen and entered into the device 1 by an operator using appropriate means forming part of the assembly 2.
  • the means 16 estimate the passage time at each test point Pt considered. The prediction is done on an interpolation between the test points Pt provided by the flight management system. The generated time is produced with respect to a current time t0 at the current position P0 of the aircraft. The next test point P1 is therefore situated at a distance D from P0 and is identified by a transit time t0 + x.
  • said extrapolation means 17 extrapolate the positions of each of the moving obstacles 02 (aircraft on flight plan, storm cells on vectors analyzed, etc.).
  • the extrapolation is performed on a tolerance window that aims to overcome the inaccuracies in the predictions.
  • This tolerance window may be predetermined, or may be selected and entered into the device 1 by an operator using appropriate means forming part of the set 2.
  • said extrapolation means 17 For each of the test points Pt, said extrapolation means 17 analyze the predicted transit time associated with it. They then perform a position extrapolation based on the displacement vectors V1 to V6 stored in the associated database 3, 4. Each of the moving obstacles 02 is thus moved for each of the test points Pt.
  • the means 18 use a collision test vector 22 having a length that is predetermined, for example 6 nautical miles, or that is chosen by the pilot using appropriate means. for example, part of the set 2. For each of the test points Pt, they draw collision test vectors perpendicular to the displacement vector of the aircraft, on either side of the test point Pt considered. . In addition, they implement a crash test for extrapolated positions of moving obstacles 02 at two successive times TiA and TiB which correspond to the extreme times (Ti-F, Ti + F) of a time window FT which is defined with respect to said passage time Ti.
  • this window FT by taking into account a duration F around the transit time Ti, makes it possible to identify three determining positions (successive according to the time t), respectively to said times Ti-F, Ti and Ti + F.
  • the duration F represents a multiple of a pitch P.
  • this time window FT may be zero.
  • the test (or interception) vector 22 is constrained by a limit length imposed, for example, by an operator. This length is associated with a maximum margin of coverage. If the test vector 22 does not encounter obstacles within this margin, the critical point Pc is therefore defined according to the size limit. On the other hand, if a point is inside a dangerous cell, this point is identified as critical. A critical point Pc is specially processed during the display to highlight the risk associated with the TV trajectory.
  • the plot along the critical points Pc, on either side of the reference trajectory TV, defines the limits 21 of the free zone ZL dynamic, as represented on the Figures 7 and 8 .
  • the present invention therefore provides a single display that represents all the evolutions of the environment with respect to the flight trajectory TV in a given time window.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Atmospheric Sciences (AREA)
  • Traffic Control Systems (AREA)
EP11191208.5A 2010-12-07 2011-11-29 Procédé et dispositif pour aider à l'évaluation visuelle d'une trajectoire de vol destinée à être suivie par un aéronef dans un environnement contraint Not-in-force EP2463845B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1060192A FR2968442B1 (fr) 2010-12-07 2010-12-07 Procede et dispositif pour aider a l'evaluation d'une trajectoire de vol destinee a etre suivie par un aeronef dans un environnement contraint.

Publications (2)

Publication Number Publication Date
EP2463845A1 EP2463845A1 (fr) 2012-06-13
EP2463845B1 true EP2463845B1 (fr) 2014-04-16

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Application Number Title Priority Date Filing Date
EP11191208.5A Not-in-force EP2463845B1 (fr) 2010-12-07 2011-11-29 Procédé et dispositif pour aider à l'évaluation visuelle d'une trajectoire de vol destinée à être suivie par un aéronef dans un environnement contraint

Country Status (4)

Country Link
US (1) US8494761B2 (zh)
EP (1) EP2463845B1 (zh)
CN (1) CN102591352B (zh)
FR (1) FR2968442B1 (zh)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2968818B1 (fr) * 2010-12-08 2014-07-11 Airbus Operations Sas Procede et dispositif d'aide a l'approche d'un aeronef lors d'une approche en vue d'un atterrissage.
US20140067267A1 (en) * 2012-08-31 2014-03-06 Ge Aviation Systems Llc Methods for determining suitable waypoint locations
JP6133506B2 (ja) 2014-04-17 2017-05-24 エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ 飛行制限区域に対する飛行制御
JP6174258B2 (ja) * 2014-09-30 2017-08-02 エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ 飛行指示方法、飛行指示装置及び航空機
FR3031808B1 (fr) * 2015-01-16 2017-01-13 Thales Sa Procede d'aide a la navigation en fonction de conditions meteorologiques
CN113031652A (zh) 2015-03-31 2021-06-25 深圳市大疆创新科技有限公司 针对限飞区域的开放平台
FR3035962B1 (fr) * 2015-05-04 2017-04-21 Airbus Operations Sas Procede, dispositif et systeme d'affichage d'un profil vertical de vol d'un aeronef
US9536435B1 (en) 2015-07-13 2017-01-03 Double Black Aviation Technology L.L.C. System and method for optimizing an aircraft trajectory
CN106873630B (zh) * 2017-04-20 2021-05-14 广州极飞科技有限公司 一种飞行控制方法及装置，执行设备
CN107146475B (zh) * 2017-06-06 2023-07-18 中国民用航空总局第二研究所 地面服务系统、机载引导系统和飞机进近着陆引导系统
CN107424440B (zh) * 2017-06-06 2023-07-18 中国民用航空总局第二研究所 飞机进近着陆监视系统
FR3078583B1 (fr) * 2018-03-02 2020-03-13 Airbus Defence And Space Sas Systemes et procedes d'aide a l'evitement de collisions entre aeronefs ou navires
EP3907905B1 (en) * 2018-10-12 2023-12-27 OQ Technology S.à r.l. Timing synchronization for non-terrestrial cellular wireless communication networks

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITRM20020371A1 (it) * 2002-07-10 2004-01-12 Maurizio Catello Pennarola Sistema di gestione della navigazione di velivoli fuori rotta e comunicazioni di allarme.
US7948404B2 (en) * 2003-05-27 2011-05-24 Honeywell International Inc. Obstacle avoidance situation display generator
EP1687590B1 (en) * 2003-11-25 2013-11-27 Honeywell International Inc. Perspective vertical situation display system and method
FR2868835B1 (fr) * 2004-04-09 2006-11-17 Thales Sa Procede de selection, pour un aeronef, d'un point d'acces a une zone de libre evolution laterale
FR2913800B1 (fr) * 2007-03-13 2010-08-20 Thales Sa Dispositifs et procedes de filtrage d'alertes anti-collision de terrain et d'obstacles pour aeronef
FR2923008B1 (fr) * 2007-10-26 2010-01-08 Thales Sa Procede et dispositif d'affichage de previsions sur un plan de navigation
FR2931983B1 (fr) * 2008-06-02 2018-04-06 Airbus Operations Methode et systeme de gestion automatique d'un convoi d'aeronefs roulant au sol.
FR2932306B1 (fr) * 2008-06-10 2010-08-20 Thales Sa Procede et dispositif d'aide a la navigation pour un aeronef vis-a-vis des obstacles.
FR2937453B1 (fr) * 2008-10-17 2010-10-22 Thales Sa Dispositif pour le calcul d'un plan de vol d'un aeronef

Also Published As

Publication number Publication date
FR2968442B1 (fr) 2012-12-28
FR2968442A1 (fr) 2012-06-08
EP2463845A1 (fr) 2012-06-13
US8494761B2 (en) 2013-07-23
CN102591352B (zh) 2014-12-03
US20120143487A1 (en) 2012-06-07
CN102591352A (zh) 2012-07-18

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