摘要
首先设计一种基于SMA驱动的可变体机翼后缘分段结构,通过相邻后缘段之间安装的偏转驱动结构,使结构的整体偏转通过后缘段累积效应实现,在此基础上制作该可变体机翼后缘的结构模型。其次,对SMA驱动元件在此机翼结构中的布局进行理论计算与仿真,验证设计驱动系统的可行性,并通过空载与加载不同状态下结构运动实验研究与仿真对比分析,近一步研究设计的SMA驱动可变体机翼后缘结构的承载能力与结构合理性。最终,设计的机翼后缘结构模型能够实现快速、稳定、连续的变形目的。
Morphing wing of trailing edge segment structure based on the SMA-driving was designed firstly. Deflection driven configuration fixed between adjacent segments created cumulative effect which achieved the overall deflection of structure. According to that, model of the structures was manufactured. The theoretical calculation and simulation of the arrangement of SMA-driving in this airfoil structures were finished, and the feasibility of the designed driven system was verified. Furthermore, the load-bearing capability and rationality of designed structure through comparative analysis between movement experiment and simulation results under different loading conditions were studied. In the end, the designed trailing edge wing structure can achieve the purpose of fast, stable, continuous deformation.
出处
《兵器材料科学与工程》
CAS
CSCD
2010年第1期25-30,共6页
Ordnance Material Science and Engineering
基金
国家自然科学基金重大研究计划(90716003)资助
国家自然科学基金重点项目(50830210)资助
关键词
机翼后缘结构
SMA驱动
关节转动
载荷实验
trailing edge wing structure
shape-memory alloy driving
joint rotation
loading experiment
