Actuation system design with electrically powered actuators

摘要

This project addresses the actuation system architecture of future All-electricaircraft (AEA) with electrically powered actuators (EPA).Firstly, the information of EPAs is reviewed, and then an electro-hydrostaticactuator (EHA) and electro-mechanical actuator (EMA) are selected for furthersystem research. The actuation system architecture of Boeing and Airbus isthen presented as a conventional design where the new design concepts arealso researched and the distributed architecture was proposed as anotherdesign trend. To find out which one is better, both of them are selected forfurther research.The easily available data makes the Flying Crane a better choice for the casestudy. Stall load, maximum rate and power are the main elements for electricactuator requirements and power consumption, weight, cost and safety are themost important aspects for civil aircraft actuation systems.The conventional and distributed flight actuation system design considered theredundancy of systems and actuators, and also the relationship of the power,control channel and actuator work mode. But only primary flight actuationcontrol system specifications are calculated since this data has better precisionand also the limited time has to be taken into consideration. Brief comparisonsof the two system specifications demonstrate that the higher power actuatorhave has higher efficiency and distributed actuators could reduce the systemweight through reduce the system redundancy with a power efficiency decline.The electrically powered actuation system for future aircraft design is a balancebetween actuator number, system weight and power consumption.