公开(公告)号：US20130138322A1

公开(公告)日：2013-05-30

申请号：US13671411

申请日：2012-11-07

Applicant: THALES

Inventor： Gilles Genevrier ,  Claude Bresson

IPC: F02D45/00

CPC classification number: F02D45/00 ,  F02C9/28 ,  F05D2260/84 ,  F05D2270/46

Abstract: In one aspect, a digital engine control system for an aircraft engine is provided. The control system includes a selection unit, the selection unit including a monitoring module configured to determine a measurement of the speed of rotation of the engine from the output signal from one or more protection sensors and to compare the or each speed measurement determined by the selection unit with speed measurements supplied by electronic control units to determine an operating state of each electronic control unit.

Abstract translation: 一方面，提供了一种用于飞机发动机的数字发动机控制系统。 所述控制系统包括选择单元，所述选择单元包括监视模块，所述监视模块被配置为根据来自一个或多个保护传感器的输出信号来确定所述发动机的转速的测量值，并且比较由所述选择确定的或每个速度测量值 由电子控制单元提供的速度测量单元来确定每个电子控制单元的运行状态。

公开(公告)号：US09927456B2

公开(公告)日：2018-03-27

申请号：US14608962

申请日：2015-01-29

Applicant: THALES

Inventor： Gilles Genevrier ,  Bernard Ledain ,  Jacques Mandle ,  Jean-Pierre Schlotterbeck

IPC: G01P3/36 ,  G01P5/14 ,  G01P5/26 ,  G01P21/02 ,  G01S17/58 ,  G01S17/02 ,  G01S7/481 ,  G01P5/02 ,  G01S17/95

CPC classification number: G01P5/14 ,  G01P5/02 ,  G01P5/26 ,  G01P21/025 ,  G01S7/4813 ,  G01S17/023 ,  G01S17/58 ,  G01S17/95 ,  Y02A90/19

Abstract: A probe system, mixed primary reference probe for an aircraft, associated aircraft and measuring method are disclosed. In one aspect, the probe system includes a base designed to be fastened on the cockpit of an aircraft, a plurality of regularly spaced static pressure taps, arranged through the base and designed to be connected to a pressure measurement device. The system includes at least one optical window transparent to laser radiation and inserted into the base.

公开(公告)号：US09002616B2

公开(公告)日：2015-04-07

申请号：US13671411

申请日：2012-11-07

Applicant: Thales

Inventor： Gilles Genevrier ,  Claude Bresson

IPC: F02D45/00 ,  F02C9/28

CPC classification number: F02D45/00 ,  F02C9/28 ,  F05D2260/84 ,  F05D2270/46

Abstract: In one aspect, a digital engine control system for an aircraft engine is provided. The control system includes a selection unit, the selection unit including a monitoring module configured to determine a measurement of the speed of rotation of the engine from the output signal from one or more protection sensors and to compare the or each speed measurement determined by the selection unit with speed measurements supplied by electronic control units to determine an operating state of each electronic control unit.

Abstract translation: 一方面，提供了一种用于飞机发动机的数字发动机控制系统。 所述控制系统包括选择单元，所述选择单元包括监视模块，所述监视模块被配置为根据来自一个或多个保护传感器的输出信号来确定所述发动机的转速的测量值，并且比较由所述选择确定的或每个速度测量值 由电子控制单元提供的速度测量单元来确定每个电子控制单元的运行状态。