期刊
JOURNAL OF AIRCRAFT
卷 46, 期 3, 页码 791-799出版社
AMER INST AERONAUT ASTRONAUT
DOI: 10.2514/1.34685
关键词
-
Studies are presented that characterize the dynamic aeroelastic aspects of a morphing aircraft design concept. The notion of interest is a folding wing design resulting in large-scale wing area changes. A finite element approach is used to investigate the sensitivity of natural frequencies and flutter instabilities to the wing position (e.g., fold angle), actuator stiffness, and vehicle weight. Sensitivities in these areas drive design requirements and raise flight envelope awareness issues. The study is presented in two parts as a comparison between two models of varying complexity. A simple folding wing model, based on the Goland wing, is analyzed and result's are compared with a built-up structural model of the proposed full scale morphing vehicle.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据