公开(公告)号：US08090485B2

公开(公告)日：2012-01-03

申请号：US11945382

申请日：2007-11-27

申请人： Erick Vile Grinits ,  Marco Antonio de Oliveira Alves Junior ,  Dagfinn Gangsaas ,  Roberto Garcia Negrao ,  Bianca Prazim Trotta ,  Fabiano Prieto Silva ,  Mauricio Martins de Almeida Filho ,  Marco Antonio Coccolin ,  Karina Sanches Garcia ,  Daniel Carmona de Campos ,  Cristina Minioli Saracho ,  Fernando Jose de Oliveira Moreira

发明人： Erick Vile Grinits ,  Marco Antonio de Oliveira Alves Junior ,  Dagfinn Gangsaas ,  Roberto Garcia Negrao ,  Bianca Prazim Trotta ,  Fabiano Prieto Silva ,  Mauricio Martins de Almeida Filho ,  Marco Antonio Coccolin ,  Karina Sanches Garcia ,  Daniel Carmona de Campos ,  Cristina Minioli Saracho ,  Fernando Jose de Oliveira Moreira

IPC分类号： G08B17/12

CPC分类号： G05D1/0825

摘要： The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).

摘要翻译： 尾部负载监测系统通过对估计的尾部负载行为和数据处理的连续评估来检测飞机控制系统故障引起的故障低频（例如在0.1至1 Hz范围内）的振荡条件 。 估计和数据处理活动都由专门的架构提供，其特征在于具有尾部负载估计模块，带通滤波器和三个独立的路径，其连续地监视故障检测事件的避免，灾难性事件回避（寻求极限载荷标准）和结构 损伤避免（解决疲劳寿命标准）。

公开(公告)号：US4821981A

公开(公告)日：1989-04-18

申请号：US147066

申请日：1988-01-25

申请人： Dagfinn Gangsaas ,  Daniel C. Norman

发明人： Dagfinn Gangsaas ,  Daniel C. Norman

IPC分类号： B64C13/16 ,  G05D1/06

CPC分类号： B64C13/16 ,  G05D1/0623

摘要： This invention provides a system for enhancing the performance of an aircraft during flight. The aircraft, which includes at least two control surfaces, such as stabilon and trailing edge flaps, includes devices for: generating a signal representative of the optimum normal acceleration from signals representative of the aircraft's flight status, generating a signal representative of the aircraft's actual normal acceleration, comparing the optimum signal to the actual signal, and generating a command to alter the position of either one or both of the aircraft's control surfaces to reduce any differences between the optimum and actual normal acceleration signals.

摘要翻译： 本发明提供了一种用于在飞行中增强飞机性能的系统。 包括至少两个控制表面（例如稳定翼和后缘翼片）的飞行器包括用于：产生代表飞机的飞行状态的信号代表最佳正常加速度的信号的装置，产生代表飞机实际正常的信号 加速度，将最佳信号与实际信号进行比较，并产生改变飞行器控制表面中的任一者或两者的位置的命令，以减少最佳和实际正常加速度信号之间的差异。

公开(公告)号：US4879643A

公开(公告)日：1989-11-07

申请号：US122780

申请日：1987-11-19

申请人： Abhijit J. M. Chakravarty ,  Dagfinn Gangsaas ,  John B. Moore

发明人： Abhijit J. M. Chakravarty ,  Dagfinn Gangsaas ,  John B. Moore

IPC分类号： G05B13/02

CPC分类号： G05B13/021

摘要： An output vector produced by a plant in response to an input vector is filtered by a plurality of bandpass filters, each filter having a different pass band. A filtered output vector from each filter is provided as input to a separate adaptive feedback controller, and feedback vectors produced by the separate controllers are summed to provide the input vector to the plant. Each adaptive feedback controller continuously identifies an open-loop transfer function of the plant characterizing a particular frequency band of plant operation, and continuously adjusts its own open-loop transfer function so that the poles of the closed-loop transfer function of the plant for that particular frequency mode of operation are assigned to constant stable values despite changes in the open-loop transfer function of the plant.

摘要翻译： 由植物响应于输入矢量产生的输出矢量被多个带通滤波器滤波，每个滤波器具有不同的通带。 提供来自每个滤波器的经滤波的输出矢量作为单独的自适应反馈控制器的输入，并且将由分离的控制器产生的反馈矢量相加以将输入矢量提供给工厂。 每个自适应反馈控制器连续地识别表征设备操作的特定频带的设备的开环传递函数，并且连续地调整其自身的开环传递函数，使得该工厂的闭环传递函数的极点 尽管工厂的开环传递功能发生了变化，特定的频率操作模式被分配给恒定的稳定值。