EP1546830A1 - Flugzeugunterstützungsverfahren und entsprechende einrichtung - Google Patents

Flugzeugunterstützungsverfahren und entsprechende einrichtung

Info

Publication number
EP1546830A1
EP1546830A1 EP03773810A EP03773810A EP1546830A1 EP 1546830 A1 EP1546830 A1 EP 1546830A1 EP 03773810 A EP03773810 A EP 03773810A EP 03773810 A EP03773810 A EP 03773810A EP 1546830 A1 EP1546830 A1 EP 1546830A1
Authority
EP
European Patent Office
Prior art keywords
aircraft
height
profile
capture
speed
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.)
Withdrawn
Application number
EP03773810A
Other languages
English (en)
French (fr)
Inventor
Guy THALES Intellectual Property DEKER
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.)
Thales SA
Original Assignee
Thales SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Thales SA filed Critical Thales SA
Publication of EP1546830A1 publication Critical patent/EP1546830A1/de
Withdrawn legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/04—Control of altitude or depth
    • G05D1/06—Rate of change of altitude or depth
    • G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
    • G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing

Definitions

  • the invention relates to a navigation aid method and device.
  • the field of the invention is that of aid to navigation and air safety and relates more particularly to aid in controlling the guidance of an aircraft along a trajectory in the context of flight control. automatic.
  • trajectory 1 shown in FIG. 1 consists of a succession of rectilinear segments and is broken down into two parts: a first part 10 during which the plane is relatively free and which can therefore be optimized by adopting a speed setpoint and thrust to minimize fuel consumption and a second part 11 of preparing the aircraft for approach and landing on a runway 12 during which the aircraft must respect certain altitude parameters , speed and horizontal route by adopting a constrained speed and slope.
  • An airplane descent trajectory is calculated backwards from the configuration in which the airplane is landing, then ascending and establishing from point 2 to point 2 the corresponding speed and thrust instructions until start point of the descent or "TOD", English acronym of "Top Of Descent".
  • the capture zone around the profile is used to designate the zone in which it is possible to capture the profile by applying a transition between the guidance sub-mode in which the aircraft is located and the guidance mode suitable for monitoring the profile segment to be captured. Outside this zone, a guidance sub-mode is applied which makes it possible to reach this capture zone as quickly as possible.
  • This capture zone 3 represented in FIG. 2 can be defined as a strip of diameter D, fixed or dependent only on speed, centered on the profile 1.
  • the capture zone is too small and the capture of the targeted profile segment is too fast, in particular for the comfort of the passengers; similarly for a flight at low altitude and / or at low speed, the capture zone is too wide and the capture of the targeted profile segment is too long in the sense that part of this capture time could have been devoted to another flight mode and in particular to a faster capture with a flight mode more economical in fuel such as for example the mode "in the air mass” or "airmass" in English.
  • An important object of the invention is therefore to choose a capture zone which is better suited to the comfort of the passengers and to the speed of capture than in the prior art.
  • the invention proposes a method for assisting the automatic navigation of an aircraft, mainly characterized in that a capture zone being an area in which the aircraft can capture a segment of predetermined vertical profile in applying a transition between the guidance sub-mode in which the aircraft is located and the guidance sub-mode suitable for monitoring the vertical profile segment to be captured, it comprises the step of determining the width of the capture zone as a function of the height of the vertical profile to be captured and of the speed of the aircraft plumb with this height when the aircraft is not on the profile or at this height when the aircraft is on the profile .
  • the invention also relates to an automatic navigation aid device for an aircraft comprising at least one program memory, characterized in that the program memory comprises a program for calculating the width of a capture zone , a capture zone being a zone in which the aircraft can capture a segment of predetermined vertical profile by applying a transition between the guidance sub-mode in which the aircraft is located and the guidance sub-mode suitable for monitoring the profile segment to be captured, the width of the capture zone being calculated as a function of the height of the vertical profile to be captured and of the speed that the aircraft plumbs over this height when the aircraft is not on the profile or at this height when the aircraft is on the profile.
  • the program memory comprises a program for calculating the width of a capture zone , a capture zone being a zone in which the aircraft can capture a segment of predetermined vertical profile by applying a transition between the guidance sub-mode in which the aircraft is located and the guidance sub-mode suitable for monitoring the profile segment to be captured, the width of the capture zone being calculated as a function of the height of the vertical profile to be captured and
  • FIG. 1 already described schematically represents a vertical profile
  • FIG. 2 already described diagrammatically represents a capture zone according to the state of the art
  • FIG. 3 diagrammatically represents a capture zone according to the invention
  • FIG. 4 diagrammatically represents a navigation aid device according to the invention.
  • the problem posed is to determine the capture area and more precisely to determine it optimally as a function of the dynamics of the aircraft and the comfort of the passengers.
  • this capture zone it is more precisely a question of determining this capture zone so that it is wider for a flight at high altitude and / or at high speed and less wide for a flight at low altitude and / or at low speed.
  • the method according to the invention is based on the calculation of the width of the capture area also called margin, as a function of the height of the vertical profile to be captured and of the ground speed that the aircraft plumb with this height when the aircraft is not on the profile or at this height when the aircraft is on the profile. According to a particular embodiment of the invention, this function is determined from the law on total mechanical energy, such
  • E t , E c and E p being respectively the total energy, the kinetic energy and the potential energy of the airplane.
  • the margin is then expressed as a function of the total height by considering a safety height h s and an adaptation constant K varying according to the characteristics of the aircraft:
  • K allows ⁇ h to vary between h s , for a flight at low altitude and low speed, and a height limit for a flight at high altitude and high speed, whatever the ground speed v and the height h.
  • FIG. 4 An example of this device 100 is shown in FIG. 4. It conventionally comprises one or more microprocessors 101 coupled to a program memory 102 of ROM type for example, to a working memory 103 of RAM type for example and to one or more memories 104 of ROM type for example for the storage of the vertical profile to be captured, as well as circuits 105 for transferring data between these various elements.
  • the program memory 102 contains the executable program of the method, in the form of source code, while the working memory 103 includes registers which can be updated for the storage of results of the calculations.
  • This equipment 100 also includes a communication interface 106 to allow the exchange of data with devices such as for example with a user interface 107, with sensors, etc.
  • FMS flight management system

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Traffic Control Systems (AREA)
  • Navigation (AREA)
EP03773810A 2002-10-01 2003-09-23 Flugzeugunterstützungsverfahren und entsprechende einrichtung Withdrawn EP1546830A1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0212134 2002-10-01
FR0212134A FR2845170B1 (fr) 2002-10-01 2002-10-01 Procede d'aide a la navigation d'un aeronef et dispositif correspondant
PCT/FR2003/002794 WO2004031879A1 (fr) 2002-10-01 2003-09-23 Procede d’aide a la navigation d’un aeronef et dispositif correspondant

Publications (1)

Publication Number Publication Date
EP1546830A1 true EP1546830A1 (de) 2005-06-29

Family

ID=31985376

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03773810A Withdrawn EP1546830A1 (de) 2002-10-01 2003-09-23 Flugzeugunterstützungsverfahren und entsprechende einrichtung

Country Status (4)

Country Link
US (1) US7774131B2 (de)
EP (1) EP1546830A1 (de)
FR (1) FR2845170B1 (de)
WO (1) WO2004031879A1 (de)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2876483B1 (fr) * 2004-10-08 2007-07-20 Airbus France Sas Procede et systeme d'evitement pour un aeronef
FR2906921B1 (fr) * 2006-10-10 2010-08-13 Thales Sa Procede de formation d'une trajectoire d'urgence en 3d pour aeronef et dispositif de mise en oeuvre
FR2908532B1 (fr) * 2006-11-10 2008-12-26 Thales Sa Methode et systeme de suivi par aeronef d'une trajectoire en descente
FR2917512B1 (fr) 2007-06-13 2011-07-15 Airbus France Procede de dispositif de pilotage d'un aeronef pour capturer un profil vertical d'un plan de vol
US8321071B2 (en) * 2009-07-31 2012-11-27 Ge Aviation Systems, Llc Method and system for vertical navigation using time-of-arrival control
US8688363B2 (en) 2010-04-30 2014-04-01 Honeywell International Inc. Aircraft systems and methods with active deceleration control
US8311687B2 (en) 2010-07-30 2012-11-13 Ge Aviation Systems Llc Method and system for vertical navigation using time-of-arrival control
US8818696B2 (en) * 2011-03-23 2014-08-26 Ge Aviation Systems Llc Method and system for aerial vehicle trajectory management
FR3016222B1 (fr) * 2014-01-03 2016-02-05 Airbus Operations Sas Procede et dispositif de guidage vertical d'un aeronef lors d'une approche d'une piste d'atterrissage le long d'une trajectoire laterale d'approche.
FR3064763B1 (fr) * 2017-03-30 2021-01-01 Thales Sa Guidage vertical d'un aeronef
CN113741521B (zh) * 2021-09-01 2024-06-21 中国航空工业集团公司西安飞行自动控制研究所 一种民用客机自动飞行高度捕获的控制方法

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3892373A (en) * 1973-12-07 1975-07-01 Bendix Corp Integrated glide path/flare automatic flight control system
FR2371006A1 (en) * 1976-11-12 1978-06-09 Sfena Approach path control for auto-gyro landing - has velocity and altitude path control to minimise noise and energy consumption during landing
US4377848A (en) * 1980-10-16 1983-03-22 Sperry Corporation Altitude capture mode for aircraft automatic flight control system
US4609988A (en) * 1983-03-17 1986-09-02 Sperry Corporation Automatic prediction and capture of a preselected altitude for aircraft
US5079711A (en) * 1990-02-26 1992-01-07 The Boeing Company Aircraft high altitude vertical flight path and speed control system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004031879A1 *

Also Published As

Publication number Publication date
US7774131B2 (en) 2010-08-10
WO2004031879A1 (fr) 2004-04-15
FR2845170A1 (fr) 2004-04-02
FR2845170B1 (fr) 2005-09-23
US20050283306A1 (en) 2005-12-22

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