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在固体推进剂火箭喷管产生的多向应力区域内,最大应力理论未能准确地描述层压复合部件的真实层间强度。利用适当的假设,简化了的张量多项式破坏准则,就可用来描述复合材料的层裂。这种简化便是Tsai—Wu表面与层间法向一剪切平面间的一个应力空间椭圆交面。此椭圆的破坏边界与垂直层应力,以及层间剪切应力轴的截距是由单向拉伸、压缩和剪切强度的特性试验来确定的。本文提出的层裂破坏准则是用试验和破坏理论加以验证的。
The maximum stress theory fails to accurately describe the true interlaminar strength of laminated composite components in a multi-directional stress region created by a solid propellant rocket nozzle. Using appropriate assumptions, simplified tensor polynomial failure criteria can be used to describe the delamination of the composite. This simplification is a stress-space elliptical intersection between the Tsai-Wu surface and the normal-shear plane in the layer. The failure boundary and vertical stress of this ellipse, as well as the intercept of the interlaminar shear stress axis are determined by the characteristic tests of uniaxial tension, compression and shear strength. The failure criterion proposed in this paper is verified by the theory of test and failure.