EP1812917A1 - Vermeidung von geländekollisionen von flugzeugen sowie alarmverfahren und -vorrichtung - Google Patents

Vermeidung von geländekollisionen von flugzeugen sowie alarmverfahren und -vorrichtung

Info

Publication number
EP1812917A1
EP1812917A1 EP05817428A EP05817428A EP1812917A1 EP 1812917 A1 EP1812917 A1 EP 1812917A1 EP 05817428 A EP05817428 A EP 05817428A EP 05817428 A EP05817428 A EP 05817428A EP 1812917 A1 EP1812917 A1 EP 1812917A1
Authority
EP
European Patent Office
Prior art keywords
aircraft
flight
slope
avoidance
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.)
Granted
Application number
EP05817428A
Other languages
English (en)
French (fr)
Other versions
EP1812917B1 (de
Inventor
Christophe Bouchet
Jean-Pierre Demortier
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
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP1812917A1 publication Critical patent/EP1812917A1/de
Application granted granted Critical
Publication of EP1812917B1 publication Critical patent/EP1812917B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/04—Anti-collision systems
    • G08G5/045—Navigation or guidance aids, e.g. determination of anti-collision manoeuvers
    • 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

Definitions

  • the present invention relates to a method and a device for alerting and avoiding terrain for an aircraft, in particular a transport aircraft.
  • Such a device for example type TAWS ("Terrain Avoidance and Warning System” in English, that is to say, warning system and terrain avoidance) or type GPWS ("Ground Proximity Warning System ", in other words, a proximity warning system with the ground), is intended to detect any risk of the aircraft colliding with the surrounding terrain and to alert the crew when such a risk is detected, so that the latter can then implement a maneuver evi ⁇ ment of the ground.
  • TAWS Transmission Avoidance and Warning System
  • GPWS Global Proximity Warning System
  • a first means knowing the profile of the terrain at least at the front of the aircraft
  • a third means connected to said first and second means, for checking whether there is a risk of collision of the terrain for the aircraft;
  • a fourth means for emitting an alert signal in the event of detec ⁇ tion of a risk of collision by said third means.
  • said second means determines the evi ⁇ ment trajectory (which is taken into account by the third means to detect a risk of collision with the terrain), using a slope having a fixed and invariable value, generally 6 ° for a transport aircraft, and this regardless of the type of the aircraft and regardless of its actual performance.
  • Document EP-0 750 238 discloses a terrain avoidance device of the aforementioned type.
  • This known device provides for determining two trajectories which are then compared with the profile of the terrain overflown, one of said trajectories representing the predicted effective trajectory of the aircraft and the other trajectory may in particular correspond to a predicted climb trajectory.
  • This prior document envisages taking into account the maneuvering capabilities of the aircraft to predict these trajectories, without, however, indicating how these trajectories are actually calculated or predicted.
  • the present invention relates to a warning and terrain avoidance method for an aircraft, which makes it possible to remedy the aforementioned drawbacks.
  • said method is remarkable in that:
  • At least one aircraft performance database is formed, which performance relates to a flight avoidance maneuver slope by the aircraft, as a function of particular flight parameters;
  • the avoidance trajectory is determined by taking into account the actual performance of the aircraft, thanks to the characteristics of said base. data and measurements of said ef ⁇ fective values. Consequently, the detection of a risk of collision with the earth takes into account the actual capabilities of the aircraft, which in particular makes it possible to avoid false alarms and to obtain particularly reliable surveillance. It will be noted that the document EP-0 750 238 cited above does not provide for determining and using a slope (for an avoidance trajectory) which depends on the actual values of particular flight parameters.
  • a plurality of values for said slope are determined, each representing different values with respect to said flight parameters.
  • said flight parameters comprise at least some of the following parameters of the aircraft:
  • a predetermined fixed value is used to form said database, which makes it possible to reduce the size of the database.
  • the value of this flight parameter which has the most unfavorable effect on the slope of the aircraft, is used as a predetermined fixed value for a flight parameter.
  • the centering of the aircraft can be fixed on the front limit value which is the most penalizing.
  • a minimum stabilized speed is known for speed which is known and that the aircraft flies normally during a usual terrain avoidance procedure following a collision risk warning. i.e. a fixed value corresponding to a velocity protection value for flight control of the aircraft.
  • a predetermined value corresponding to a better slope speed, and not to a minimum speed such as in the previous example.
  • the slope of the aircraft is deduced, in the event of engine failure, from a minimum slope representative of a normal operation (without failure) of all the mo ⁇ the aircraft, to which a reduction is applied depending on the said nominal failure.
  • said abatement is calculated by means of a polynomial function modeling said nominal slope (slope of the aircraft with all engines in operation).
  • the present invention also relates to a warning and terrain avoidance device for an aircraft, in particular a transport aircraft, said device being of the type comprising:
  • a first means knowing the profile of the terrain at least at the front of the aircraft; a second means for determining an avoidance trajectory;
  • a third means connected to said first and second means, for checking whether there is a risk of collision of the terrain for the aircraft;
  • fourth means for emitting an alert signal, in the event of detecting a risk of collision by said third means.
  • said second means determines the avoidance trajectory, by calculating an avoidance slope at the running speed of the aircraft, which is greater than a minimum speed that the aircraft normally flies when a usual terrain avoidance procedure following an alert. Therefore, this avoidance slope is different from the slope that will actually be stolen during the maneuver.
  • Such a calculation mode can be the cause of erroneous alarms, initially underestimating the actual performance of the aircraft.
  • said device of the aforementioned type is remarkable, according to the invention, in that it comprises, in addition, at least one database of performance of the aircraft, relative to a slope flight avoidance maneuver by the aircraft, in function of particular flight parameters, and a fifth means for determining during a flight of the aircraft the actual values of said particular parameters, and said second means is formed so as to determine said avoidance trajectory, as a function of information received respectively from said database and said fifth means.
  • the design of said database therefore takes into account a predictive ability with respect to the climb performance of the aircraft to avoid terrain.
  • the speed of the avoidance phase being predetermined (at a minimum speed, as specified below) to then provide the associated slope, it is thus freed from the current speed of the aircraft (which is necessarily higher at said minimum speed maie), which makes it possible to stabilize the avoidance slope calculated by the dis ⁇ positive according to the invention and thus to avoid false alarms.
  • the device according to the invention comprises a plurality of such databases which relate respectively to different categories of aircraft, and a selection means for selecting, from among these databases, that which is rela ⁇ tive to the aircraft on which said device is mounted, said second means using information from the database thus selected to determine said avoidance trajectory.
  • a selection means for selecting, from among these databases, that which is rela ⁇ tive to the aircraft on which said device is mounted, said second means using information from the database thus selected to determine said avoidance trajectory.
  • Figures 1 and 2 are block diagrams of two different embodiments of a warning device and terrain avoidance according to the invention.
  • the device 1 according to the invention and shown diagrammatically in FIGS. 1 and 2 is intended to detect any risk of collision of an aircraft, in particular a transport aircraft, with the surrounding terrain and to warn the crew of the aircraft when such a risk is detected, so that the latter can then implement an evi ⁇ ment maneuvering the land.
  • Such a device for example of TAWS type ("Terrain Terrain, and Warning System” in English, that is to say, warning and terrain avoidance system) or type GPWS ("Ground Proximity” Warning System “in English, that is to say system of proximity alarm with the ground), which is embarked on the aircraft, comprises in the usual way:
  • a means 2 which knows the profile of the terrain at least in front of the aircraft and which comprises for this purpose for example a terrain database and / or terrain detection means such as a radar ;
  • a means 4 which is connected via links 5 and 6 to said means 2 and 3, to check in the usual way whether there is a risk of collision of the terrain for the aircraft, from the information transmitted by said means 2 and 3;
  • a means 7 which is connected via a link 8 to said means 4, for emitting an alert signal (sound and / or visual), in the event of detecting a risk of collision by said means 4.
  • said device 1 further comprises:
  • At least one aircraft performance database Bi, B1, B2, Bn which performance is related to a flight avoidance maneuver slope by the aircraft, and this according to particular flight parameters, such as specified below; and • means 9 for determining, during a flight of the aircraft, the actual values of said particular flight parameters; and
  • said means 3 is connected via links 10 and 11 respectively to said database Bi, B1, B2, Bn and to said means 9 and is formed so as to determine said avoidance trajectory, as a function of the information received from both said database Bi,
  • said database Bi, B1, B2, Bn is formed on the ground during a preliminary stage, before a flight of the aircraft, in the manner specified below.
  • a plurality of values of said slope, representative res ⁇ pectively of a plurality of different values with respect to said flight parameters are determined.
  • These flight parameters include parameters relating to flight characteristics (speed, mass, ...) of the aircraft, parameters relating to systems (air conditioning, anti-icing, etc.) of the aircraft, and parameters relating to the environment (temperature) external to the aircraft.
  • said flight parameters comprise at least some of the following parameters relating to the aircraft: the mass of the aircraft;
  • said slope is calculated in the usual way, as a function of said flight parameters, from a usual documentation of aircraft performance (for example the flight manual), which comes from models recalibrated by flight tests.
  • a predetermined fixed value is used to form said database Bi, B1, B2, Bn, which makes it possible to reduce the size of the database Bi, B1 , B2, Bn.
  • the centering of the aircraft can be fixed on the front limit value which is the most penalizing, and the air sampling configurations (antistorage and air conditioning) can be fixed so as to remain conservative. vis-à-vis the performance of the aircraft.
  • a fixed value corresponding to a speed protection value for flight controls of the aircraft is used for the speed, that is to say a minimum speed that the aircraft flies normally during a usual terrain avoidance maneuver following an alert, for example a speed V ⁇ max (speed inci ⁇ dence maximum) or a speed VSW (type "Stall Warning" in English, that is to say - stall warning warning).
  • a speed V ⁇ max speed inci ⁇ dence maximum
  • VSW type "Stall Warning" in English, that is to say - stall warning warning.
  • the design of the database Bi, B1, B2, Bn introduces a predictive capacity, since the speed of the avoidance phase is predetermined to then provide the associated slope. This eliminates the current speed of the aircraft (which is necessarily higher than this minimum speed), which allows to stabilize the avoidance slope calc ⁇ by the device 1. Without this modeling, the device 1 should calculate an avoidance slope at the current speed of the aircraft, this avoidance slope would be different from the slope actually stolen during the maneuver (then tend towards the latter slope, as the deceleration of the aircraft). This type of calculation could cause erroneous alarms, initially underestimating the real performance of the aircraft.
  • the aforementioned modeling in accordance with the present invention thus makes it possible to provide a stable calculation slope for the device 1 (by integrating the calculation speed of the slope) and thus to avoid false alarms; the integration of this parameter (speed) considerably reduces the size of the database Bi, B1, B2, Bn;
  • the database Bi, B1, B2, Bn is built on regulatory bases (the slopes with minimum speed being certi ⁇ fi ed data), which makes it possible to easily develop a data generation process which is in accordance with to a "DO-200A" standard (and which is therefore qualifiable with respect to this standard) guaranteeing the integrity level of the databases.
  • a complementary solution of the present invention aims to model the maximum voltible slopes with engine failure (s), from the slope all engines in operation, and the ad ⁇ junction of an abatement slope ⁇ p (negative) which is modeled by a polynomial function.
  • This modeling makes it possible to significantly reduce the size of the memory intended to receive the database Bi, B1, B2, Bn (memory size reduced by a coefficient 2 or 3 in principle).
  • K1 and K2 represent constants that are applicable to a whole family of aircraft of similar geometry.
  • best slope speed is understood to mean the speed that makes it possible to acquire a maximum altitude for a minimum distance, and this without leaving the flight range of speed.
  • speed of best slope is a speed which is predetermined, depending on at least some of the aforementioned flight parameters (mass, altitude, etc.).
  • the performance database Bi, B1, B2, Bn makes it possible to calculate in real time the capabilities of the aircraft to be avoided from above, any obstacle that presents itself in front of it and / or along the flight plan. monitoring.
  • the device 1 according to the invention determines the avoidance trajectory, taking into account the actual performance of the aircraft, thanks to the characteristics of said database Bi, B1, B2, Bn and the measurements of said actual values. Consequently, the detection of a risk of collision with the terrain takes into account the ef ⁇ fective capabilities of the aircraft, which in particular makes it possible to avoid false alarms and to obtain particularly reliable surveillance.
  • the device 1 according to the invention comprises:
  • a selection means 13 which is connected by links £ 1, £ 2 to £ n respectively to said databases B1, B2 to Bn and which is designed to select, from among these databases B1, B2 to Bn, that relating to the aircraft on which said device 1 is mounted.
  • Said means 3 which is connected by the link 10 to said selection means 13 uti ⁇ read only information from the database selected by said selection means 13 to determine said path of avoidance.
  • Each of these categories of aircraft comprises either a single type of aircraft (a category then corresponds to a type), or a set of aircraft types presenting, for example, substantially equivalent performances and grouped under the same category (each category then comprises Several types).
  • the selection of the representative database of the aircraft is performed by pin programming, ie "pin programming" (that is to say with terminals of a connector between the aircraft and the disposi ⁇ tif 1, corresponding to logic levels 0 or 1 depending on the category of aé ⁇ ronef)).
  • pin programming that is to say with terminals of a connector between the aircraft and the disposi ⁇ tif 1, corresponding to logic levels 0 or 1 depending on the category of aé ⁇ ronef
  • This programming can alternatively be carried out in a software way: the selection means 13 receives for example by a data link a numerical value which depends on the category of aircraft and it realizes the selection according to this digital value received.

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Traffic Control Systems (AREA)
  • Alarm Systems (AREA)
  • Burglar Alarm Systems (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Navigation (AREA)
EP05817428A 2004-11-15 2005-11-10 Vermeidung von geländekollisionen von flugzeugen sowie alarmverfahren und -vorrichtung Not-in-force EP1812917B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0412067A FR2878060B1 (fr) 2004-11-15 2004-11-15 Procede et dispositif d'alerte et d'evitement de terrain pour un aeronef
PCT/FR2005/002803 WO2006051220A1 (fr) 2004-11-15 2005-11-10 Procede et dispositif d’alerte et d’evitement de terrain pour un aeronef

Publications (2)

Publication Number Publication Date
EP1812917A1 true EP1812917A1 (de) 2007-08-01
EP1812917B1 EP1812917B1 (de) 2008-09-17

Family

ID=34981909

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05817428A Not-in-force EP1812917B1 (de) 2004-11-15 2005-11-10 Vermeidung von geländekollisionen von flugzeugen sowie alarmverfahren und -vorrichtung

Country Status (11)

Country Link
US (1) US8010288B2 (de)
EP (1) EP1812917B1 (de)
JP (1) JP4940143B2 (de)
CN (1) CN100481154C (de)
AT (1) ATE408876T1 (de)
BR (1) BRPI0516330A (de)
CA (1) CA2582358A1 (de)
DE (1) DE602005009859D1 (de)
FR (1) FR2878060B1 (de)
RU (1) RU2375757C2 (de)
WO (1) WO2006051220A1 (de)

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Also Published As

Publication number Publication date
JP2008519729A (ja) 2008-06-12
CN101057270A (zh) 2007-10-17
RU2007122395A (ru) 2008-12-20
JP4940143B2 (ja) 2012-05-30
US20090076728A1 (en) 2009-03-19
DE602005009859D1 (de) 2008-10-30
BRPI0516330A (pt) 2008-09-02
FR2878060B1 (fr) 2010-11-05
CN100481154C (zh) 2009-04-22
ATE408876T1 (de) 2008-10-15
CA2582358A1 (fr) 2006-05-18
WO2006051220A1 (fr) 2006-05-18
FR2878060A1 (fr) 2006-05-19
EP1812917B1 (de) 2008-09-17
US8010288B2 (en) 2011-08-30
RU2375757C2 (ru) 2009-12-10

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