求飞机结构真实腐蚀容限的原理和方法

Principle and method of calculating real corrosion tolerance value of aircraft struture

本文通过静强度、疲劳强度和腐蚀3个学科的综合研究,分别给出飞机结构(下称机件)在静载荷作用下的应力与腐蚀损伤D的分布曲线和机件在疲劳载荷作用下的寿命与腐蚀损伤D的分布曲线。根据这两条曲线和机件使用的容限应力值及总疲劳寿命值,便可分别求出机件在静载荷作用下的腐蚀损伤容限值和机件在疲劳载荷作用下的腐蚀损伤容限值以及同一机件同时受静载荷和疲劳载荷作用的腐蚀损伤容限值。此外,本文提出了用一个腐蚀损伤容限值保证同一机件的总疲劳寿命和总日历寿命皆安全的方法,以及总疲劳寿命和总日历寿命的匹配设计和匹配使用等问题。研究结论适用于大气、海洋、土壤等环境的腐蚀机件,解决了国际机械和腐蚀领域一直未解决的一些难题。

Through the comprehensive study of static strength,fatigue strength and corrosion,the distribution curve of stress and corrosion damage D of aircraft structure(subscript parts)under static load and the distribution curve of life and corrosion damage D of parts under fatigue load are studied respectively in this paper.According to these two curves and the tolerance,stress value and total fatigue life value of the parts,the tolerance values of the corrosion damage of the parts under static load,the tolerance values of the corrosion damage of the parts under fatigue load and the tolerance values of the corrosion damage of the same parts under static load and fatigue load can be calculated respectively.In addition,the method of using a corrosion damage tolerance value to ensure the safety of the total fatigue life and the total calendar life of the same part,and the matching design and matching use of the total fatigue life and the total calendar life are also studied.These conclusions are applicable to the corrosive parts in atmosphere,ocean,soil and other environments,and solve some unsolved problems in the field of international machinery and corrosion.