航空发动机疲劳载荷分散性及其对应的疲劳分散系数研究
Study on Fatigue Load Dispersion and Relevant Fatigue Dispersion Coefficients of Aircraft Engines

为了科学评价航空发动机疲劳载荷分散性,假设任务混频固定,考虑飞行员技术差异的影响,构建了基于飞行剖面的矩阵式载荷库,建立了航空发动机载荷分散性对应的疲劳分散系数的计算模型,并通过算例分析和Monte Carlo仿真验证了模型的有效性。研究表明:航空发动机全寿命期累积疲劳载荷强度服从正态分布,累积疲劳载荷分散性随载荷库载荷强度分散性的增大而增大,随发动机寿命周期的增大而减小;航空发动机载荷分散性对应的疲劳分散系数随载荷库载荷强度变异系数的增大而增大,随发动机寿命周期的增大而减小,随载荷强度可靠度要求的提高而增大。
In order to evaluate the fatigue load dispersion of aircraft engines, assuming the mixing and fixed frequency task, and considering the influence of technique differences among aviators, we construct a matrix aggregate of loads based on the flight profiles, and build a model for fatigue dispersion coefficients to correlate fatigue load dispersion of aircraft engines. The validity of the present model was validated with the example analysis and computer simulation via Monte Carlo method. It was shown that accumulative fatigue loads of aircraft engines in life period submit to normal distribution. Fatigue load dispersion increases with the increasing of load dispersion of load aggregate, whereas if decreases with the increasing of lifetime. Fatigue dispersion coefficients correlating fatigue load dispersion of aircraft engines increases with the increasing of load dispersion of load aggregate and the requirement of reliability, whereas if decreases with increasing of lifetime