Architecture Optimization of More Electric Aircraft Actuation System  

作　　者：QI Haitao FU Yongling QI Xiaoye LANG Yan 

机构地区：[1]School of Mechanical Engineering and Automation, Beihang University, Beijing 100191, China [2]Beijing Institute of Control Engineering, Beij'ing 100190, China

出　　处：《Chinese Journal of Aeronautics》2011年第4期506-513,共8页中国航空学报（英文版）

基　　金：National Natural Science Foundation of China （50675009）; International Science ＆ Technology Cooperation Program of China （2010DFA72540）

摘　　要：The optional types of power source and actuator in the aircraft are more and more diverse due to fast development in more electric technology, which makes the combinations of different power sources and actuators become extremely complex in the architecture optimization process of airborne actuation system. The traditional ＂trial and error＂ method cannot satisfy the design demands. In this paper, firstly, the composition of more electric aircraft （MEA） flight control actuation system （FCAS） is introduced, and the possible architecture quantity is calculated. Secondly, the evaluation criteria of FCAS architecture with respect to safe reliability, weight and efficiency are proposed, and the evaluation criteria values are calculated in the case that each control surface adopts the same actuator configuration. Finally, the optimization results of MEA FCAS architecture are obtained by applying genetic algorithm （GA）. Compared to the traditional actuation system architecture, which only adopts servo valve controlled hydraulic actuators, the weight of the optimized more electric actuation system architecture can be reduced by 6%, and the efficiency can be improved by 30% based on the safe reliability requirements.The optional types of power source and actuator in the aircraft are more and more diverse due to fast development in more electric technology, which makes the combinations of different power sources and actuators become extremely complex in the architecture optimization process of airborne actuation system. The traditional ＂trial and error＂ method cannot satisfy the design demands. In this paper, firstly, the composition of more electric aircraft （MEA） flight control actuation system （FCAS） is introduced, and the possible architecture quantity is calculated. Secondly, the evaluation criteria of FCAS architecture with respect to safe reliability, weight and efficiency are proposed, and the evaluation criteria values are calculated in the case that each control surface adopts the same actuator configuration. Finally, the optimization results of MEA FCAS architecture are obtained by applying genetic algorithm （GA）. Compared to the traditional actuation system architecture, which only adopts servo valve controlled hydraulic actuators, the weight of the optimized more electric actuation system architecture can be reduced by 6%, and the efficiency can be improved by 30% based on the safe reliability requirements.

关 键 词：more electric aircraft power-by-wire actuation system ARCHITECTURE multiobjective optimization genetic algorithms 

分 类 号：TU751[建筑科学—建筑技术科学] TN873.91[电子电信—信息与通信工程]