公开(公告)号：US20220139230A1

公开(公告)日：2022-05-05

申请号：US17574082

申请日：2022-01-12

Applicant: BOMBARDIER INC.

Inventor： Franck GANSMANDEL ,  Timothy SMITH

IPC: G08G5/00 ,  G05D1/08 ,  B64D45/00 ,  B64C13/50

Abstract: The aircraft control systems and methods disclosed herein are configured to detect a residual error associated with a flight control computer of an aircraft and mitigate the effect(s) of such residual error in order to maintain safe operation of the aircraft. In some embodiments, the systems and methods are configured to detect an out-of-flight-envelope situation of the aircraft and determine whether or not the flight control computer is attempting to recover the aircraft from the out-of-flight-envelope situation. If the flight control computer is perceived as attempting to recover the aircraft from the out-of-flight-envelope situation, the flight control computer is permitted to continue controlling the aircraft. Otherwise, the excursion outside of the normal flight envelope is perceives as potentially having been caused by a residual error and the flight control computer is prevented from continuing to control the aircraft.

公开(公告)号：US20170081019A1

公开(公告)日：2017-03-23

申请号：US15364308

申请日：2016-11-30

Applicant: BOMBARDIER INC.

Inventor： Shu LIN ,  Timothy SMITH ,  Pierre DE SERRES

IPC: B64C13/50 ,  B64C13/04 ,  G05D1/00

CPC classification number: B64C13/503 ,  B64C19/00 ,  G05B9/03 ,  G05D1/0077

Abstract: A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers.

公开(公告)号：US20180180446A1

公开(公告)日：2018-06-28

申请号：US15128739

申请日：2015-03-23

Applicant: BOMBARDIER INC.

Inventor： Timothy SMITH

IPC: G01D3/08 ,  G01D5/22 ,  B64C13/42

Abstract: A system for detecting mechanical failure of a connection between a variable differential transformer and a controlled element. The sensor system includes a variable differential transformer with a housing encapsulating a first coil, a bore in the housing, wherein the bore is adjacent to the first coil, a core disposed in the bore, a shaft connectible between the core, at a first end, and the controlled element, at a second end, and a biasing element connected to the shaft. Responsive to a break in the shaft, the biasing element moves the core to an out-of-range position detectable by at least the first coil.

公开(公告)号：US20160114882A1

公开(公告)日：2016-04-28

申请号：US14925623

申请日：2015-10-28

Applicant: BOMBARDIER INC.

Inventor： Shu LIN ,  Timothy SMITH ,  Pierre DE SERRES

IPC: B64C13/50 ,  G05D1/00 ,  B64C13/04

CPC classification number: B64C13/503 ,  B64C13/04 ,  B64C19/00 ,  G05D1/0077

Abstract: A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers.

Abstract translation: 多轴串行冗余，单通道，多路径逐线控制系统，其包括：在单个通道中的串行冗余飞行控制计算机，其中只有一个“主要”飞行控制计算机处于活动状态并在任何给定时间进行控制; 包括稳定器电机控制单元（SMCU）和执行机构电子控制模块（AECM）在内的并行飞行控制面控制器矩阵定义了单个通道内的多个控制路径，每个控制路径用不同的硬件实现，每个控制路径分别控制一组分布式飞行 响应于主飞行控制计算机的飞行控制表面命令来控制飞机上的表面; 以及一组（飞行员和副驾驶员）控制和飞机表面/参考/导航传感器和系统，其向主飞行控制计算机提供输入并用于产生飞行控制表面命令以根据 控制算法在飞行控制计算机中实现。