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通常结构件的重量与所用材料的比强度或比刚度成反比,因此比强度、比刚度就成为材料选择的主要参数。本文分析了板材、型材在拉伸、弯曲作用下以及受压杆件、内压圆筒件的构件重量和材料强度、弹性模量之间的关系,求得合理的有效比强度、有效比刚度的表达式。根据计算,这两个参数可以分别表示为o~x/ρ或E~y/ρ(x,y≤1)。作者建议采用这两个参数代替常用的o/ρ和E/p,作为优化材料选择的准则。 基于以上表达式,对于重量成为设计的严重问题来说,降低材料的密度比提高材料的强度或弹性模量更为有效。从这个意义上说,宇航材料的发展史也就是材料密度不断降低的历史。
Usually the weight of the structure is inversely proportional to the specific strength or specific rigidity of the material used. Therefore, the specific strength and specific stiffness have become the main parameters of material selection. This paper analyzes the relationship between tensile strength and elastic modulus of plate and profile under tension and bending, as well as the weight of the rod member and internal pressure cylinder, and the relationship between material strength and elastic modulus. The reasonable effective specific strength, effective specific stiffness Expression. According to calculation, these two parameters can be expressed as o ~ x / ρ or E ~ y / ρ (x, y≤1) respectively. The authors suggest that these two parameters should be used instead of the usual o / ρ and E / p criteria for optimizing material selection. Based on the above expression, it is more effective to reduce the density of the material than to increase the strength or elastic modulus of the material, for serious problems where weight becomes a design. In this sense, the history of the development of aerospace materials is also the history of the continuous decline in material density.