Patents by Inventor Dagfinn Gangsaas
Dagfinn Gangsaas has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 9405295Abstract: 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.Type: GrantFiled: December 11, 2007Date of Patent: August 2, 2016Assignee: EMBRAER S.A.Inventors: 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
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Patent number: 8606437Abstract: 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.Type: GrantFiled: November 28, 2011Date of Patent: December 10, 2013Assignee: Embraer S.A.Inventors: Fabricio Reis Caldeira, Marcos Vinicius Campos, Reneu Luiz Andrioli, Jr., Wagner de Oliveira Carvalho, Dagfinn Gangsaas, Eduardo Camelier, Daniel Siqueira, Lucas Rubiano
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Publication number: 20130138274Abstract: 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.Type: ApplicationFiled: November 28, 2011Publication date: May 30, 2013Applicant: EMBRAER S.A.Inventors: Fabrício Reis Caldeira, Marcos Vinicius Campos, Reneu Luiz Andrioli Junior, Wagner de Oliveira Carvalho, Dagfinn Gangsaas, Eduardo Camelier, Daniel Siqueira, Lucas Rubiano
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Patent number: 8214089Abstract: 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.Type: GrantFiled: November 9, 2010Date of Patent: July 3, 2012Assignee: EMBRAER - Empresa Brasileira de Aeronautica S.A.Inventors: 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
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Patent number: 8165733Abstract: 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.Type: GrantFiled: September 4, 2007Date of Patent: April 24, 2012Assignee: Embraer S.A.Inventors: 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
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Patent number: 8090485Abstract: 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).Type: GrantFiled: November 27, 2007Date of Patent: January 3, 2012Assignee: Embraer S.A.Inventors: 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
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Publication number: 20110054720Abstract: 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.Type: ApplicationFiled: November 9, 2010Publication date: March 3, 2011Applicant: EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A.Inventors: 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
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Publication number: 20100217460Abstract: 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.Type: ApplicationFiled: December 11, 2007Publication date: August 26, 2010Inventors: 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
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Publication number: 20090138147Abstract: 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).Type: ApplicationFiled: November 27, 2007Publication date: May 28, 2009Inventors: 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
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Publication number: 20090062973Abstract: 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.Type: ApplicationFiled: September 4, 2007Publication date: March 5, 2009Inventors: 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
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Patent number: 4879643Abstract: 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.Type: GrantFiled: November 19, 1987Date of Patent: November 7, 1989
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Patent number: 4849900Abstract: 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.Type: GrantFiled: May 2, 1986Date of Patent: July 18, 1989Assignee: The Boeing CompanyInventors: James D. Blight, Dagfinn Gangsaas
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Patent number: 4821981Abstract: 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.Type: GrantFiled: January 25, 1988Date of Patent: April 18, 1989Assignee: The Boeing CompanyInventors: Dagfinn Gangsaas, Daniel C. Norman