Distributed and redundant electromechanical nose gear steering system

2020-04-03 02:21

Final Report Summary DRESS (Distributed and Redundant Electromechanical nose wheel Steering System) The main aim of the DRESS project was to develop a steering system that increases significantly the levels of reliability and availability.The goal of this project is to research, develop and validate a distributed and redundant electrical steering system technology for an aircraft nose landing gear, that will provide improved competitiveness and improved aircraft safety by: reduced system weight at the aircraft level, replacing the current hydraulic actuation by electrical actuation. improved aircraft safety provided by the distributed and redundant electromechanical nose gear steering system

Moreover, the system is easier to maintain: monitoring the electrical circuit is more reliable than finding a leak. Therefore, the electrical technology is used for several AC on board systems. The present research work is supported by the European DRESS project (Distributed and Redundant Electromechanical nose gear Steering System).

Fig. 1. Nose wheel Distributed and Redundant Electromechanical nose wheel Steering System DRESS early achievements presentation Paris Air S how 2009 1. PROJECT CHARACTERISTICS AND OBJECTIVES 1. 1. Background In the large commercial aircraft market, landing gear systems are currently operated using hydraulic power. The goal of this project was to research, develop and validate a distributed and redundant electrical steering system technology for an aircraft nose landing gear that would provide improved competitiveness and improved aircraft safety. Reduced system weight at the aircraft level, replacing the current hydraulic actuation by electrical actuation. distributed and redundant electromechanical nose gear steering system Scope of the DRESS project is to research, develop and validate a distributed and redundant electrical steering system technology for an aircraft nose landing gear. The new system aims to: reduce system weight at aircraft level, replacing the current hydraulic actuation system with an electric one.

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