Novel Swing Arm Mechanism Design for Trailing Edge Flaps on Commercial Airliner
This paper applies the idea of swing arm mechanism trailing edge flap and modeled the mechanism on CATIA software to yield a kinematic simulation for the purpose of check motion trail and force transfer in this mechanism. Relevant works such as actuation, mass and stress analysis are also involved. A spanwise constraint is added to eliminate spanwise displacement of the trailing edge flap while deploying. A four-row ball monorail guidance system is introduced into the outside swing arm assembly to provide spanwise slide motion for the support bracket. As the result of this research project, it is found that swing arm mechanism trends to require relatively small fairings for supports and attachments due to its high stowed space utilizing efficiency. Initial mass estimation carried out in this paper also indicates that the new design takes advantage in terms of weight comparing with traditional trailing edge flap mechanisms. Thus, swing arm mechanism is supposed to show great competitive potential for commercial airliners trailing edge flaps after further analysis has been done in the detail design phase.
high lift devices trailing edge flap swing arm mechanism design kinematic simulation
Yujie
Department of Flight Control and Hydraulic Design, AVIC The First Aircraft Institute, Xian 710089,China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
108-110
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）