The Mechanism Analysis of Bi-stable Asymmetric Composite Laminates
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摘要: 不对称铺层的复合材料层合板在存在热残余应力的情况下,具有双稳态性质。此性质能够使飞机结构布局具有两种稳态形式,且实现两者之间转换不需要有持续的能量激励,只需要一个适当的激励即可。叙述了复合材料层合板内部热致残余应力的产生原理,建立了基于经典层合板理论、存在残余应力时的复合材料层合板的能量泛函,详细阐述了复合材料层合板的位移场函数的建立方法,分析了复合材料层合板具有双稳态特性的机理。同时利用有限元分析软件ANSYS,对两种不对称铺层顺序的复合材料层合板进行了双稳态特性的数值模拟验证。Abstract: The symmetric composite laminates with thermal residual stress possess bi-stable property.This property makes structures have two stable configurations.The benefit of bi-stable structure is that the stable shapes are operational shapes,and power is needed only to transform the structure from one to another shape.In this paper,the reason of thermal stress formation was simply demonstrated.And the potential energy function with thermal residual stress was established based on the classic laminate theory.Thus,the methodical expression of interpolation function was given,and the bi-stable mechanism of composite laminates was demonstrated in detail.Therefore the numerical simulation of two asymmetric bi-stable composite laminates was carried out using the finite-element package ANSYS.So the mechanism demonstrated was proved to be accredited.
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Key words:
- composite /
- bi- stable /
- residual- stress /
- morphing aircraft /
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