The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Jan. 03, 2012
Filed:
Nov. 27, 2007
Erick Vile Grinits, Sao Jose dos Campos, BR;
Marco Antonio DE Oliveira Alves Junior, Sao Jose dos Campos, BR;
Dagfinn Gangsaas, Sao Jose dos Campos, BR;
Roberto Garcia Negrao, Sao Jose dos Campos, BR;
Bianca Prazim Trotta, Sao Jose dos Campos, BR;
Fabiano Prieto Silva, Sao Jose dos Campos, BR;
Mauricio Martins DE Almeida Filho, Sao Jose dos Campos, BR;
Marco Antonio Coccolin, Sao Jose dos Campos, BR;
Karina Sanches Garcia, Sao Jose dos Campos, BR;
Daniel Carmona DE Campos, Sao Jose dos Campos, BR;
Cristina Minioli Saracho, Sao Jose dos Campos, BR;
Fernando Jose DE Oliveira Moreira, Sao Jose dos Campos, BR;
Erick Vile Grinits, Sao Jose dos Campos, BR;
Marco Antonio de Oliveira Alves Junior, Sao Jose dos Campos, BR;
Dagfinn Gangsaas, Sao Jose dos Campos, BR;
Roberto Garcia Negrao, Sao Jose dos Campos, BR;
Bianca Prazim Trotta, Sao Jose dos Campos, BR;
Fabiano Prieto Silva, Sao Jose dos Campos, BR;
Mauricio Martins de Almeida Filho, Sao Jose dos Campos, BR;
Marco Antonio Coccolin, Sao Jose dos Campos, BR;
Karina Sanches Garcia, Sao Jose dos Campos, BR;
Daniel Carmona de Campos, Sao Jose dos Campos, BR;
Cristina Minioli Saracho, Sao Jose dos Campos, BR;
Fernando Jose de Oliveira Moreira, Sao Jose dos Campos, BR;
Embraer S.A., Sao Paulo, BR;
Abstract
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).