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本文以Matsuoka模型、何庆芝模型及黄玉珊模型为根据,以航空上常见的短周期加载为条件,导出了计算构件裂纹扩展寿命的以下解析式:可以证明,与它们相应的线性累积损伤公式为式中,α和β、γ分别为Walker公式中的系数和指数,n=β+γ,φ_i为取决于过载迟滞模型的小于1的系数。 全尺寸起落架的疲劳试验表明,由本文导出的第一个解析式计算的裂纹扩展寿命与试验结果相当接近。
Based on the Matsuoka model, Heqingzhi model and Huang Yushan model, the following analytical formulas for calculating the crack propagation life of a component are derived on the condition of common short-period loading in aviation: It can be proved that the corresponding linear cumulative damage formula is: , Α and β and γ are the coefficients and exponents of the Walker formula, respectively, and n = β + γ and φ_i are coefficients less than 1 depending on the overload hysteresis model. Full-scale landing gear fatigue tests show that the crack propagation life calculated by the first analytical method derived from this paper is quite close to the experimental results.