公开(公告)号：US4849900A

公开(公告)日：1989-07-18

申请号：US860944

申请日：1986-05-02

申请人： James D. Blight ,  Dagfinn Gangsaas

发明人： James D. Blight ,  Dagfinn Gangsaas

IPC分类号： G05D1/00 ,  G05D1/06

CPC分类号： G05D1/0061 ,  G05D1/0623

摘要： A flight control system combines airspeed with normal acceleration to produce a feedback signal and combines the feedback signal with a feedforward signal consisting of a pilot command signal to produce a differential acceleration signal which is used to control elevator control surface of an aircraft to provide enhanced pitch stability.

摘要翻译： 飞行控制系统将空速与正常加速度结合以产生反馈信号，并将反馈信号与由导频命令信号组成的前馈信号组合以产生差分加速度信号，该差分加速度信号用于控制飞机的电梯控制面以提供增强的俯仰 稳定性。

公开(公告)号：US08165733B2

公开(公告)日：2012-04-24

申请号：US11849501

申请日：2007-09-04

申请人： Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Alvaro Vito Polati de Souza ,  Eduardo da Saiva Martins ,  Marco Tulio Sguerra Vita ,  Jose Marcio Vieira Dias Filho ,  Marcos Vinicius Campos ,  Emerson Freitas

发明人： Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Alvaro Vito Polati de Souza ,  Eduardo da Saiva Martins ,  Marco Tulio Sguerra Vita ,  Jose Marcio Vieira Dias Filho ,  Marcos Vinicius Campos ,  Emerson Freitas

IPC分类号： G05D1/06

CPC分类号： G05D1/0833

摘要： A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.

公开(公告)号：US09405295B2

公开(公告)日：2016-08-02

申请号：US12518361

申请日：2007-12-11

申请人： Alvaro Vitor Polati De Souza ,  Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Jerome Klein ,  Lauro Rocha Borges ,  Reneu Luiz Andrioli, Jr. ,  Luciano Tury Pastorini ,  Marco Paulo Fonseca

发明人： Alvaro Vitor Polati De Souza ,  Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Jerome Klein ,  Lauro Rocha Borges ,  Reneu Luiz Andrioli, Jr. ,  Luciano Tury Pastorini ,  Marco Paulo Fonseca

IPC分类号： G01C23/00 ,  G05D1/00 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00 ,  G05D1/06 ,  G05D1/08

CPC分类号： G05D1/0676 ,  G05D1/08 ,  G05D1/0808

摘要： A flight control system commands drag devices such as flight spoilers according to pilot or autopilot longitudinal command. Furthermore, the flight control system monitors a set of flight parameters to determine whether the aircraft is operating inside the permitted safe envelope, hence, incorporating envelope automatic exceeding disengagement. This invention allows the aircraft to descend in a steeper glide path than the 3° used in the normal approach, while keeping speeds unchanged.

摘要翻译： 飞行控制系统根据飞行员或自动驾驶仪纵向命令来命令拖动装置，例如飞行扰流板。 此外，飞行控制系统监视一组飞行参数，以确定飞行器是否在允许的安全信封内操作，因此，将信封自动超出分离。 本发明允许飞行器以比正常进近中使用的3°更陡的滑行路径下降，同时保持速度不变。

公开(公告)号：US20130138274A1

公开(公告)日：2013-05-30

申请号：US13304979

申请日：2011-11-28

申请人： Fabrício Reis Caldeira ,  Marcos Vinicius Campos ,  Reneu Luiz Andrioli Junior ,  Wagner de Oliveira Carvalho ,  Dagfinn Gangsaas ,  Eduardo Camelier ,  Daniel Siqueira ,  Lucas Rubiano

发明人： Fabrício Reis Caldeira ,  Marcos Vinicius Campos ,  Reneu Luiz Andrioli Junior ,  Wagner de Oliveira Carvalho ,  Dagfinn Gangsaas ,  Eduardo Camelier ,  Daniel Siqueira ,  Lucas Rubiano

IPC分类号： G05D1/06

CPC分类号： G05D1/0676

摘要： A longitudinal control law is designed to optimize the flying qualities when aircraft is set to approach configuration, i.e. when the flap lever is set to the landing position and landing gears are locked down. Under such circumstances, the effort of trimming the aircraft speed can be extremely reduced by the usage of a momentary on-off switch or other control in the sidestick, instead of or in addition to a conventional trim up-down switch, making easier the task of airspeed selection by the pilot. This control law provides excellent handling qualities during approach and landing, with the benefit of not needing or using radio altimeter information in safety-critical applications.

摘要翻译： 纵向控制规律被设计为当飞行器被设置为接近构造时，即当翼片杆被设置到着陆位置并且起落架被锁定时，优化飞行质量。 在这种情况下，可以通过使用瞬时开关开关或旁路中的其他控制来极大地减少飞行器速度的改进，而不是传统的调节上拉开关，也可以简化任务。 飞行员选择空速。 该控制法在接近和着陆期间提供极好的处理质量，有利于在安全关键应用中不需要或使用无线电高度计信息。

公开(公告)号：US20090138147A1

公开(公告)日：2009-05-28

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： B64C19/00

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：US20090062973A1

公开(公告)日：2009-03-05

申请号：US11849501

申请日：2007-09-04

申请人： Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Alvaro Vitor Polati de Souza ,  Eduardo da Silva Martins ,  Marco Tulio Sguerra Vita ,  Jose Marcio Vieira Dias Filho ,  Marcos Vinicius Campos ,  Emerson Freitas

发明人： Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Alvaro Vitor Polati de Souza ,  Eduardo da Silva Martins ,  Marco Tulio Sguerra Vita ,  Jose Marcio Vieira Dias Filho ,  Marcos Vinicius Campos ,  Emerson Freitas

IPC分类号： G05D1/08 ,  G06F17/00 ,  G06F7/00

CPC分类号： G05D1/0833

摘要： A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.

摘要翻译： 飞行控制系统根据与自动命令相加的飞行员指令移动电梯。 飞行控制系统监视一组飞行参数，以确定飞行器是否在允许的信封内操作。 飞行控制系统通过自动升降机命令包含自动保护，如果飞行器接近其信封限制。 这里的示例性说明性非限制性实施例提供自动保护，以便保护飞行器辆免受低速，高姿态，档位和冲击。

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：US20110054720A1

公开(公告)日：2011-03-03

申请号：US12942534

申请日：2010-11-09

申请人： Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Alvaro Vito Polati de Souza ,  Eduardo da Silva Martins ,  Marco Tulio Sguerra Vita ,  Jose Marcio Vieira Dias Filho ,  Marcos Vinicius Campos ,  Emerson Freitas

发明人： Fabricio Reis Caldeira ,  Dagfinn Gangsaas ,  Alvaro Vito Polati de Souza ,  Eduardo da Silva Martins ,  Marco Tulio Sguerra Vita ,  Jose Marcio Vieira Dias Filho ,  Marcos Vinicius Campos ,  Emerson Freitas

IPC分类号： G05D1/08

CPC分类号： G05D1/0833

摘要： A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.

摘要翻译： 飞行控制系统根据与自动命令相加的飞行员指令移动电梯。 飞行控制系统监视一组飞行参数，以确定飞行器是否在允许的信封内操作。 飞行控制系统通过自动升降机命令包含自动保护，如果飞行器接近其信封限制。 这里的示例性说明性非限制性实施例提供自动保护，以便保护飞行器辆免受低速，高姿态，档位和冲击。

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：US08606437B2

公开(公告)日：2013-12-10

申请号：US13304979

申请日：2011-11-28

申请人： Fabricio Reis Caldeira ,  Marcos Vinicius Campos ,  Reneu Luiz Andrioli, Jr. ,  Wagner de Oliveira Carvalho ,  Dagfinn Gangsaas ,  Eduardo Camelier ,  Daniel Siqueira ,  Lucas Rubiano

发明人： Fabricio Reis Caldeira ,  Marcos Vinicius Campos ,  Reneu Luiz Andrioli, Jr. ,  Wagner de Oliveira Carvalho ,  Dagfinn Gangsaas ,  Eduardo Camelier ,  Daniel Siqueira ,  Lucas Rubiano

IPC分类号： B64C13/00

CPC分类号： G05D1/0676

摘要： A longitudinal control law is designed to optimize the flying qualities when aircraft is set to approach configuration, i.e. when the flap lever is set to the landing position and landing gears are locked down. Under such circumstances, the effort of trimming the aircraft speed can be extremely reduced by the usage of a momentary on-off switch or other control in the sidestick, instead of or in addition to a conventional trim up-down switch, making easier the task of airspeed selection by the pilot. This control law provides excellent handling qualities during approach and landing, with the benefit of not needing or using radio altimeter information in safety-critical applications.

摘要翻译： 纵向控制规律被设计为当飞行器被设置为接近构造时，即当翼片杆被设置到着陆位置并且起落架被锁定时，优化飞行质量。 在这种情况下，可以通过使用瞬时开关开关或旁路中的其他控制来极大地减少飞行器速度的改进，而不是传统的调节上拉开关，也可以简化任务。 飞行员选择空速。 该控制法在接近和着陆期间提供极好的处理质量，有利于在安全关键应用中不需要或使用无线电高度计信息。