公开(公告)号：US09483885B2

公开(公告)日：2016-11-01

申请号：US14316441

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'Arbonneau ,  Olivier Breton

IPC: G07C5/00 ,  G07C5/08 ,  G01P5/16 ,  G01P21/02 ,  B64D45/00

CPC classification number: G07C5/0816 ,  B64D45/00 ,  G01P5/16 ,  G01P21/025

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract translation: 提供一种用于检测执行风检测的飞行器上的至少一个传感器的故障的方法。 该方法包括测量飞行器的空速; 测量飞机的地理速度; 基于测量的空速和地理速度确定瞬时风向量; 基于确定的瞬时风矢量建立瞬时风向量; 将瞬时风力变化矢量投影到飞行器的空气或地理速度的矢量的方向上; 以及基于所获得的投影来确定故障的存在。

公开(公告)号：US09714100B2

公开(公告)日：2017-07-25

申请号：US14316459

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'Arbonneau

IPC: G01M17/00 ,  B64F5/00 ,  G01C5/00 ,  G01C5/06 ,  G01C21/16 ,  G01P5/14 ,  G01P7/00 ,  G01P21/02 ,  G05D1/04

CPC classification number: B64F5/60 ,  G01C5/005 ,  G01C5/06 ,  G01C21/165 ,  G01P5/14 ,  G01P7/00 ,  G01P21/025 ,  G05D1/042

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

公开(公告)号：US09108745B2

公开(公告)日：2015-08-18

申请号：US14316417

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'Arbonneau

IPC: G05D1/00 ,  G05D1/08 ,  G05D3/00 ,  B64F5/00 ,  B60R25/04 ,  B60R21/017 ,  B60T8/88 ,  G01P5/16 ,  G01P7/00 ,  G01P21/02

CPC classification number: B64F5/0045 ,  B60R21/0173 ,  B60R25/04 ,  B60T8/885 ,  B64F5/60 ,  G01P5/16 ,  G01P7/00 ,  G01P21/025

Abstract: A method for detecting a failure of at least one sensor on board an aircraft is provided. The method includes implementing an anemo-inertial loop including obtaining a computed horizontal speed, based on an integration of a measured horizontal acceleration and obtainment of a short-term anemo-inertial speed from the computed horizontal speed; developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and observing a failure detection parameter obtained from an intermediate parameter of the anemo-inertial loop and determining the presence of a failure on one of the sensors of the aircraft, based on the value of the observed failure detection parameter.

Abstract translation: 提供一种用于检测飞机上的至少一个传感器的故障的方法。 该方法包括实现一个非惯性循环，包括基于所测量的水平加速度的积分和从计算出的水平速度获得短期海洋惯性速度获得计算出的水平速度; 基于短期海洋惯性速度和风速测量速度或空速之间的偏差来发展至少一个中间回路参数; 并且根据观测到的故障检测参数的值，观察从该非惯性回路的中间参数获得的故障检测参数，并确定飞机的其中一个传感器上的故障的存在。