• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The method of assisting the landing of an aircraft (1) on an airstrip (5) comprises the following steps implemented automatically by a processing unit (24): a) acquiring information relating to the runway; b) acquire information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow the aircraft to fly along a trajectory between a current position and a landing target position on the runway; g) comparing this maximum roll angle with a predetermined limit; and h) according to the result of the comparison made in step g), order if necessary the signaling of an alert by means of a signaling system (30) of the aircraft.
    公开号:FR3044809A1
    申请号:FR1561789
    申请日:2015-12-03
    公开日:2017-06-09
    发明作者:Pierre Scacchi；Matthieu Mayolle；Cecile Puissacq
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    CLAIMS 1- A method of assisting the landing of an aircraft (1) on an airstrip (5), the aircraft comprising a set (22) of information sources (22a, 22b), a system flight management system (32), a processing unit (24) and a signaling system (30), the method being characterized in that it comprises the following steps implemented automatically by the processing unit: - a) acquire, from the flight management system, information relating to the runway; - b) acquire, from the set of sources of information, information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position of the aircraft and a landing target position of the aircraft on the landing runway ; g) comparing this maximum roll angle with a predetermined limit of roll angle; and h) according to the result of the comparison made in step g), order if necessary the signaling of an alert using the signaling system of the aircraft. 2- Method according to claim 1, characterized in that, in step h), the processing unit controls the signaling of the alert if the maximum roll angle is greater, in absolute value, than the predetermined limit roll angle. 3- Method according to one of claims 1 or 2, characterized in that the landing target position is located on a central longitudinal axis (4) of the landing strip. 4- Method according to claim 3, characterized in that the maximum roll angle is determined using the equation:
    wherein: φ-rmax is said maximum roll angle; Τω is a time interval between a current moment and a landing moment of the aircraft on the runway;
    Vy is a current lateral speed of the aircraft; D is a current lateral deviation of the aircraft relative to the central longitudinal axis of the landing runway; Θ is a running pitch angle of the aircraft; g is the acceleration of gravity. 5. Method according to any one of the preceding claims, characterized in that it furthermore comprises the following steps: i) determining, as a function, on the one hand, of information relating to the current situation of the aircraft and of other information relating to the landing runway, a landing position of the aircraft on a central longitudinal axis (4) of the runway, this landing position being determined according to a determined trajectory between a current position of the aircraft and this landing position so as to respect at least one constraint relating to a roll angle of the aircraft; -j) determining a parameter relative to said landing position of the aircraft on the central longitudinal axis of the landing runway; - k) determining a difference between this parameter and a reference value; -1) compare this difference with a predetermined threshold; and in step h), the processing unit controls the signaling of the alert if on the one hand the maximum roll angle is greater, in absolute value, than the predetermined limit of roll angle and if, on the other hand, the difference determined in step k) is greater than the predetermined threshold. 6. Process according to any one of the preceding claims, characterized in that steps a), b), f), g), h) and, where appropriate, steps i), j), k) and I) , are implemented automatically when a current height of the aircraft is below a predetermined height threshold (A1), the method further comprising the following steps implemented automatically and repeatedly by the unit of processing when the current height of the aircraft is above this predetermined height threshold: - a) acquire, from the flight management system (32), information relating to the runway; b) acquiring, from the set (22) of sources of information, information relating to a current situation of the aircraft; c) determining, on the one hand, information relating to the current situation of the aircraft and, on the other hand, information relating to the landing runway, at least one difference between, on the one hand, at least one parameter relating to a landing position of the aircraft on the runway and, secondly, a reference relating to a central longitudinal axis of the runway; d) comparing this difference with a predetermined threshold; and e) depending on the result of the comparison made in step d), order if necessary signaling an alert using the signaling system (30) of the aircraft. 7- System (20) for landing assistance of an aircraft (1) on an airstrip (5), the aircraft comprising an assembly (22) of information sources (22a, 22b), a flight management system (32) and a signaling system (30), the landing aid system being characterized in that it comprises a processing unit (24) configured to implement the following steps : - a) acquire, from the flight management system, information relating to the runway; - b) acquire, from the set of sources of information, information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position of the aircraft and a landing target position of the aircraft on the landing runway ; g) comparing this maximum roll angle with a predetermined limit of roll angle; and h) according to the result of the comparison made in step g), order if necessary the signaling of an alert using the signaling system of the aircraft. 8- System according to claim 7 characterized in that the processing unit is configured to control the signaling of the alert if the maximum roll angle is greater, in absolute value, than the predetermined limit of angle of roll. 9- System according to one of claims 7 or 8 characterized in that, in step f), the landing target position is located on a central longitudinal axis (4) of the runway. 10- System according to claim 9 characterized in that the processing unit is configured to determine the maximum roll angle, in step f), using the equation:
    wherein: cpimax is said maximum roll angle;
    Ttd is a time interval between a current moment and a landing moment of the aircraft on the runway;
    Vy is a current lateral speed of the aircraft; D is a current lateral deviation of the aircraft relative to the central longitudinal axis of the landing runway; Θ is a running pitch angle of the aircraft; g is the acceleration of gravity. 11- System according to any one of claims 7 to 10 characterized in that the processing unit is configured to implement, in addition, the following steps: - i) determine, depending on the one hand the information relating to the current situation of the aircraft and secondly information relating to the landing runway, a landing position of the aircraft on a central longitudinal axis (4) of the runway, this landing position being determined according to a determined trajectory between a current position of the aircraft and this landing position so as to respect at least one constraint relative to a roll angle of the aircraft; -j) determining a parameter relative to said landing position of the aircraft on the central longitudinal axis of the landing runway; - k) determining a difference between this parameter and a reference value; -1) compare this difference with a predetermined threshold; and in step h), the processing unit controls the signaling of the alert if on the one hand the maximum roll angle is greater, in absolute value, than the predetermined limit of roll angle and if, on the other hand, the difference determined in step k) is greater than the predetermined threshold. 12- System according to any one of claims 7 to 12 characterized in that the processing unit is configured to: - automatically implement steps a), b), f), g), h ) and, where appropriate, steps i), j), k) and I), when a current height of the aircraft is less than a predetermined height threshold (A1); and - implementing the following steps automatically and repetitively when the current height of the aircraft is greater than this predetermined height threshold: a) acquiring, from the flight management system, information relating to the runway of the aircraft; landing; - b) acquire, from the set of sources of information, information relating to a current situation of the aircraft; c) determining, on the one hand, information relating to the current situation of the aircraft and, on the other hand, information relating to the landing runway, at least one difference between, on the one hand, at least one parameter relating to a landing position of the aircraft on the runway and, secondly, a reference relating to a central longitudinal axis of the runway; d) comparing this difference with a predetermined threshold; and e) depending on the result of the comparison made in step d), order if necessary signaling an alert using the signaling system of the aircraft. An aircraft (1) having a landing aid system (20) according to any one of claims 7 to 12.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    A method of assisting the landing of an aircraft (1) on an airstrip (5), the aircraft comprising a set (22) of information sources (22a, 22b), an flight management (32), a processing unit (24) and a signaling system (30), the method being characterized in that it comprises the following steps implemented automatically by the processing unit: a) acquire, from the flight management system, information relating to the runway; - b) acquire, from the set of sources of information, information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position of the aircraft and a landing target position of the aircraft on the landing runway ; g) comparing this maximum roll angle with a predetermined limit of roll angle; and h) according to the result of the comparison made in step g), order if necessary the signaling of an alert using the signaling system of the aircraft.
    [2" id="c-fr-0002]
    2- Method according to claim 1, characterized in that, in step h), the processing unit controls the signaling of the alert if the maximum roll angle is greater, in absolute value, than the predetermined limit roll angle.
    [3" id="c-fr-0003]
    3- Method according to one of claims 1 or 2, characterized in that the landing target position is located on a central longitudinal axis (4) of the landing strip.
    [4" id="c-fr-0004]
    4- Method according to claim 3, characterized in that the maximum roll angle is determined using the equation:

    wherein: φ-rmax is said maximum roll angle; Τω is a time interval between a current moment and a landing moment of the aircraft on the runway; Vy is a current lateral speed of the aircraft; D is a current lateral deviation of the aircraft relative to the central longitudinal axis of the landing runway; Θ is a running pitch angle of the aircraft; g is the acceleration of gravity.
    [5" id="c-fr-0005]
    5. Method according to any one of the preceding claims, characterized in that it furthermore comprises the following steps: i) determining, as a function, on the one hand, of information relating to the current situation of the aircraft and of other information relating to the landing runway, a landing position of the aircraft on a central longitudinal axis (4) of the runway, this landing position being determined according to a determined trajectory between a current position of the aircraft and this landing position so as to respect at least one constraint relating to a roll angle of the aircraft; -j) determining a parameter relative to said landing position of the aircraft on the central longitudinal axis of the landing runway; - k) determining a difference between this parameter and a reference value; -1) compare this difference with a predetermined threshold; and in step h), the processing unit controls the signaling of the alert if on the one hand the maximum roll angle is greater, in absolute value, than the predetermined limit of roll angle and if, on the other hand, the difference determined in step k) is greater than the predetermined threshold.
    [6" id="c-fr-0006]
    6. Process according to any one of the preceding claims, characterized in that steps a), b), f), g), h) and, where appropriate, steps i), j), k) and I) , are implemented automatically when a current height of the aircraft is below a predetermined height threshold (A1), the method further comprising the following steps implemented automatically and repeatedly by the unit of processing when the current height of the aircraft is above this predetermined height threshold: - a) acquire, from the flight management system (32), information relating to the runway; b) acquiring, from the set (22) of sources of information, information relating to a current situation of the aircraft; c) determining, on the one hand, information relating to the current situation of the aircraft and, on the other hand, information relating to the landing runway, at least one difference between, on the one hand, at least one parameter relating to a landing position of the aircraft on the runway and, secondly, a reference relating to a central longitudinal axis of the runway; d) comparing this difference with a predetermined threshold; and e) depending on the result of the comparison made in step d), order if necessary signaling an alert using the signaling system (30) of the aircraft.
    [7" id="c-fr-0007]
    7- System (20) for landing assistance of an aircraft (1) on an airstrip (5), the aircraft comprising an assembly (22) of information sources (22a, 22b), a flight management system (32) and a signaling system (30), the landing aid system being characterized in that it comprises a processing unit (24) configured to implement the following steps : - a) acquire, from the flight management system, information relating to the runway; - b) acquire, from the set of sources of information, information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position of the aircraft and a landing target position of the aircraft on the landing runway ; g) comparing this maximum roll angle with a predetermined limit of roll angle; and h) according to the result of the comparison made in step g), order if necessary the signaling of an alert using the signaling system of the aircraft.
    [8" id="c-fr-0008]
    8- System according to claim 7 characterized in that the processing unit is configured to control the signaling of the alert if the maximum roll angle is greater, in absolute value, than the predetermined limit of angle of roll.
    [9" id="c-fr-0009]
    9- System according to one of claims 7 or 8 characterized in that, in step f), the landing target position is located on a central longitudinal axis (4) of the runway.
    [10" id="c-fr-0010]
    10- System according to claim 9 characterized in that the processing unit is configured to determine the maximum roll angle, in step f), using the equation:

    wherein: cpimax is said maximum roll angle; Ttd is a time interval between a current moment and a landing moment of the aircraft on the runway; Vy is a current lateral speed of the aircraft; D is a current lateral deviation of the aircraft relative to the central longitudinal axis of the landing runway; Θ is a running pitch angle of the aircraft; g is the acceleration of gravity.
    [11" id="c-fr-0011]
    11- System according to any one of claims 7 to 10 characterized in that the processing unit is configured to implement, in addition, the following steps: - i) determine, depending on the one hand the information relating to the current situation of the aircraft and secondly information relating to the landing runway, a landing position of the aircraft on a central longitudinal axis (4) of the runway, this landing position being determined according to a determined trajectory between a current position of the aircraft and this landing position so as to respect at least one constraint relative to a roll angle of the aircraft; -j) determining a parameter relative to said landing position of the aircraft on the central longitudinal axis of the landing runway; - k) determining a difference between this parameter and a reference value; -1) compare this difference with a predetermined threshold; and in step h), the processing unit controls the signaling of the alert if on the one hand the maximum roll angle is greater, in absolute value, than the predetermined limit of roll angle and if, on the other hand, the difference determined in step k) is greater than the predetermined threshold.
    [12" id="c-fr-0012]
    12- System according to any one of claims 7 to 12 characterized in that the processing unit is configured to: - automatically implement steps a), b), f), g), h ) and, where appropriate, steps i), j), k) and I), when a current height of the aircraft is less than a predetermined height threshold (A1); and - implementing the following steps automatically and repetitively when the current height of the aircraft is greater than this predetermined height threshold: a) acquiring, from the flight management system, information relating to the runway of the aircraft; landing; - b) acquire, from the set of sources of information, information relating to a current situation of the aircraft; c) determining, on the one hand, information relating to the current situation of the aircraft and, on the other hand, information relating to the landing runway, at least one difference between, on the one hand, at least one parameter relating to a landing position of the aircraft on the runway and, secondly, a reference relating to a central longitudinal axis of the runway; d) comparing this difference with a predetermined threshold; and e) depending on the result of the comparison made in step d), order if necessary signaling an alert using the signaling system of the aircraft.
    [13" id="c-fr-0013]
    An aircraft (1) having a landing aid system (20) according to any one of claims 7 to 12.
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    同族专利:
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    引用文献:
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    法律状态:
    2016-12-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-09| PLSC| Publication of the preliminary search report|Effective date: 20170609 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1561789A|FR3044809B1|2015-12-03|2015-12-03|METHOD AND SYSTEM FOR AIDING THE LANDING OF AN AIRCRAFT.|FR1561789A| FR3044809B1|2015-12-03|2015-12-03|METHOD AND SYSTEM FOR AIDING THE LANDING OF AN AIRCRAFT.|
    US15/357,249| US10384800B2|2015-12-03|2016-11-21|Method and system for aiding landing of an aircraft|
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