Generator configuration for helicopter quadruplex electric tail rotor

Abstract

With the move to more electric aircraft (MEA), a key area of investigation is the development of commercially viable systems which are reliable, efficient, low mass, and are compatible and commensurate with the power and multiplex requirements of current and future aircraft. In rotorcraft, the pace of adopting more electric systems, to replace conventional mechanical and hydraulic ones, say, is perceived as being much lower than in fixed wing aircraft. However, recently there has been growing evidence to suggest that a quadruplex electric tail rotor (ETR) is a technically viable solution. This paper shows the methodology to support the most reliable configuration of the four independent generators required to power such a quadruplex tail rotor drive, and takes account of the failure severity due to power loss in each independent channel, target reliability setting, and supporting reliability analyses. The conclusions drawn support a particular hybrid series-parallel configuration of generators, with identification of further work related to the gearbox reliabilities which support the reliability attainment for the configuration.

Keywords

• aircraft
• helicopters
• aircraft power systems
• reliability
• aerospace components
• rotors
• technically viable solution
• reliable configuration
• independent generators
• quadruplex tail rotor drive
• power loss
• target reliability setting
• supporting reliability analyses
• series-parallel configuration
• gearbox reliabilities
• reliability attainment
• generator configuration
• helicopter quadruplex electric tail rotor
• electric aircraft
• commercially viable systems
• reliable mass
• efficient mass
• low mass
• multiplex requirements
• current aircraft
• future aircraft
• electric systems
• conventional mechanical ones
• hydraulic ones
• fixed wing aircraft