Embraer S.a.

Embraer - Empresa Brasileira De Aeronautica S.a.

Marcos Vinicius Campos

Dagfinn Gangsaas

Fabricio Reis Caldeira

Marcelo Galvão

Emerson Freitas

Jose Marcio Vieira Dias Filho

Marco Tulio Sguerra Vita

Alvaro Vito Polati De Souza

Daniel Paulo De Tarso Ferreira

Reneu Luiz Andrioli, Jr

Luiz Carlos Marengo

Eduardo Da Saiva Martins

Eduardo Da Silva Martins

Lucas Rubiano

Daniel Siqueira

Eduardo Camelier

Wagner De Oliveira Carvalho

Alvaro Vitor Polati De Souza

Celso Jose Amaral Fonseca

Nilson Emanuel Bezerra Chaves

Guilherme De Miranda Cará

Wagner De Oliviera Carvalho

Reneu Luiz Andrioli Jr

Fabrício Reis Caldeira

José Márcio Vieira Dias Filho

Marco Túlio Seguerra Vita

An electromechanical rudder system control using electromagnetic actuators provides dual redundancy to comply with safety demands. Diversity of possible interconnection distribution allows the manufacturer to choose the proper configuration to satisfy aircraft safety design, hardware savings and overall system quality improvements. A dual channel rudder system architecture includes reconfigurable electronic controllers used to control plural electromechanical primary actuators for rudder control, and a distribution of aircraft and cockpit sensors through the electronic controllers to guarantee minimum required safety standards in case of loss of input data. The plural electromechanical actuators driving a rudder surface are arranged in independent and redundant load paths.

Rudder system architecture for electrical actuators

A flexible distributed multi-system architecture for aircraft control integrates electronic computers comprising plural types of high integrity, dissimilar, generic and reconfigurable controllers (GECs) that can assume different purposes. GECs are configured as actuator controllers (able to control up to three channels including hydraulic or electro-mechanical actuators) or as Control Law Computers (able to calculate more sophisticated and processor demanding control laws). The multi-system architecture is built around a backbone of high performance, high integrity digital protocols and three hubs with dual connection to two different GECs.

Aircraft integrated multi system electronic architecture

A flexible flight control system enables conversion from one architecture using one type of inceptor to another architecture using another type of inceptor, through the usage of modular software and hardware pieces with common interfaces among the different types of inceptors. Longitudinal and lateral directional control laws are adapted to be compatible with the specific aspects of the operation of each configuration/architecture, giving the option to the aircraft operator to choose any one of a number of inceptor architectures at time of manufacture.

System and method to interchange flight control inceptors in an aircraft flight control system and cockpit

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.

Flight control system mode and method providing aircraft speed control through the usage of momentary on-off control

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.

Stall, buffeting, low speed and high attitude protection system

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