公开(公告)号：US10906633B2

公开(公告)日：2021-02-02

申请号：US15952666

申请日：2018-04-13

Applicant: Airbus Operations S.A.S.

Inventor： Jérôme Gauvain ,  Lionel Bompart ,  Daniel Lopez Fernandez

IPC: B64C13/18 ,  G07C5/08 ,  G05D1/08 ,  B64F5/60

Abstract: A flight control computer of an aircraft is likely to operate in a so-called incidence protection mode in which it is configured to compute the deflection orders of an elevator as a function of incidence angle values supplied by a set of incidence probes, so as to keep the incidence angle of the aircraft within a range of acceptable incidence angle values. The flight control computer is configured to, when only one incidence probe is operational: compute a first estimated incidence angle value of the aircraft, by a first estimator and a second estimated incidence angle value of the aircraft, by a second estimator unlike the first estimator; and keep the incidence protection mode activated as long as the incidence angle value supplied by the single operational incidence probe is consistent with at least one out of the first estimated incidence angle value and the second estimated incidence angle value.

公开(公告)号：US20180304994A1

公开(公告)日：2018-10-25

申请号：US15952666

申请日：2018-04-13

Applicant: Airbus Operations S.A.S.

Inventor： Jérôme Gauvain ,  Lionel Bompart ,  Daniel Lopez Fernandez

IPC: B64C13/18 ,  G07C5/08

CPC classification number: B64C13/18 ,  B64F5/60 ,  G05D1/0808 ,  G05D1/0825 ,  G05D1/0833 ,  G07C5/0816

Abstract: A flight control computer of an aircraft is likely to operate in a so-called incidence protection mode in which it is configured to compute the deflection orders of an elevator as a function of incidence angle values supplied by a set of incidence probes, so as to keep the incidence angle of the aircraft within a range of acceptable incidence angle values. The flight control computer is configured to, when only one incidence probe is operational: compute a first estimated incidence angle value of the aircraft, by a first estimator and a second estimated incidence angle value of the aircraft, by a second estimator unlike the first estimator; and keep the incidence protection mode activated as long as the incidence angle value supplied by the single operational incidence probe is consistent with at least one out of the first estimated incidence angle value and the second estimated incidence angle value.

公开(公告)号：US09776729B2

公开(公告)日：2017-10-03

申请号：US14886727

申请日：2015-10-19

Applicant: Airbus Operations (S.A.S.)

Inventor： Philippe Goupil ,  Nicola Mimmo ,  Pierre Chevalier ,  Daniel Lopez Fernandez ,  Rémy Dayre

IPC: B64D43/02 ,  G01P5/14 ,  G01P5/02 ,  G01P21/02

CPC classification number: B64D43/02 ,  G01P5/02 ,  G01P5/14 ,  G01P21/025

Abstract: A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.

公开(公告)号：US20160107762A1

公开(公告)日：2016-04-21

申请号：US14886727

申请日：2015-10-19

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Philippe Goupil ,  Nicola Mimmo ,  Pierre Chevalier ,  Daniel Lopez Fernandez ,  Rémy Dayre

IPC: B64D43/02 ,  G01P5/14

CPC classification number: B64D43/02 ,  G01P5/02 ,  G01P5/14 ,  G01P21/025

Abstract: A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.

Abstract translation: 一种装置，包括用于确定飞行器的至少一个控制表面的至少一个空气动力学铰链力矩的第一数据生成单元，用于确定多个数据和至少一个外部静态压力的第二数据生成单元和铰链力矩模型 系数，用于借助于这些数据计算飞行器的至少一个速度，即马赫数和/或常规速度的计算单元，以及用于向用户系统提供该速度的数据传输单元。