WFD WFD WFD WFD WFD WFD WFD WFD WFD WFD WFD A V Aloha WFD. Widespread Fatigue Damage WFD WFD. 25.

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1 Journal of Northwestern Polytechnical University Feb. Vol No. 1 WFD WFD WFD WFD WFD WFD WFD WFD V WFD WFD A Aloha 1 FAA WFD Widespread Fatigue Damage WFD WFD b 1 Stagg WFD WFD 50% 5 Moukawsher WFD WFD Miner's Neuber Linclon Melliere AC LOV LOV 8-10 WFD WFD WFD WFD WFD WFD MATLAB AN- SYS 1986

2 WFD δ j j 0 1 N rand j j D init j = D init j N min 2 WFD D init j < 1 1 WFD MSD / D init j = 1 MED D init 10 = 1 10 j N rand j j j Monte Carlo j mm 2. 2 D 1 N min N rand j dn D j = D init j + 3 WFD N max j D j j 2. 1 D init j j N max j j dn μ m σ m WFD j Swift μ m σ m 0 1 δ R p a + R p b = R ab 4 N rand j = μ m f σ m δ j j = 1 2 n 1 R p a R p b 2 j = 1 Walker 12 Willenborg- Change 12 Miner j

3 1 WFD 105 R ab Irwin Dug- dale WFD WFD 2 1 K = K C a j = a jf K C a jf j 2 σ = Wt - Wt ( ) σ c = σ ys 5 D + a j W t D a j j σ ys σ c 2 3 σ 3 σ ys K C K C 1 = σ κ init ( ) 6 σnet κ K C 2 = ( t hole K t ) 7 ellipse Multiple κ K C 3 = Site Damage MSD ( t hole K t ) 8 crackhole σ init σ net K t hole Multiple Element Damage MED 2 K t ellipse 3 K t crackhole κ 9 WFD 10 WFD 2 N D j = D init j N max j C 1 C 2 C 3 9 da dn = f ΔK C 1 C 2 C WFD WFD Structure Modification Point SMP WFD Inspection Structure Point ISP WFD 1 3 SMP WFD

4 WFD 1 σ /MPa μ m σ m WFD WFD T T3 E /MPa μ σ s /MPa K c /MPa 槡 m C n p q

5 1 WFD 107 MATLAB WFD ANSYS MAT- LAB ANSYS MATLAB MATLAB 500 WFD N init N link N fail 2. 1 P = N init P = 0. 5 N wfd P = WFD WFD 6 2 WFD WFD WFD WFD SMP ISP LOV WFD WFD 1 Federal Aviation Administration. Part 25-Airworthiness Standards Transport Category Airplane Li Yazhi Li Qiang Shen Peiliang. An Overview of Airworthiness Requirements for Transport Category Airplanes to Prevent Widespread Fatigue Damage. Advances in Aeronautical Science and Engineering in Chinese 3 Federal Aviation Administration. Aging Aircraft Program Widespread Fatigue Damage Final Rule. Federal Register Federal Aviation Administration. Advisory Circular Establishing and Implementing Limit of Validity to Prevent Widespread Fatigue Damage Stagg A M. An Investigation of the Scatter in Constant Amplitude Fatigue Test Results of Aluminum Alloys 2024 and H M Stationery off Moukawsher E J Grand Jr A F Neussl M A. Fatigue Life of Panels with Multiple Site Damage. Journal of Aircraft

6 Lincoln J W Melliere R A. Economic Life Determination for a Military Aircraft. Journal of Aircraft Swift T. Damage Tolerance Capability. International Journal of Fatigue Buhler K Grand Jr A F Moukawsher E J. Fatigue Analysis of Multiple Site Damage at a Row of Holes in a Wide Panel. FAA / NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance Silva L F M Goncalves J P M Oliveira F M F de Castro PMST. Multiple-Site Damage in Riveted Lap-Joints Experimental Simulation and Finite Element Prediction. International Journal of Fatigue Feng Zhenyu Li Kai Du Hongzeng. Progress of Research on Widespread Fatigue Damage of Aging Aircrafts. Journal of Civil Aviation University of China in Chinese Zheng Xiaolin Zhang Minfu. Structure Durability and Damage Tolerance Design Manual of Civil Aircraft book 2 Damage Tolerance Design and Analysis. Beijing Aviation Industry Press 2003 in Chinese Wang Chuansheng Zhang Jianyu Bao Rui et al. Reliability Analysis on Structure with Multiple Site Damage. Journal of Beijing University of Aeronautics and Astronautics in Chinese A Method for Determining WFD Average Behavior of Aircraft Fleet Zhan Fuyu 1 2 Yang Wei 1 2 Wang Shengnan 1 Zhao Zhongqing 1 ( ) 1. College of Aeronautics Northwestern Polytechnical University Xi'an China 2. AVIC Chengdu Aircraft Design & Research Institute Chengdu China Abstract Widespread Fatigue Damage WFD issue is a major threat to the continuing airworthiness of transport aircraft particularly the aging aircraft. So WFD evaluation is key measure and necessary task for ensuring the continuing airworthiness. A new method using probabilistic and deterministic theory to simulate and evaluate WFD was introduced in this paper. The method and process of WFD evaluation were expounded at first then how to consider crack interactions was explained. Finally a specific example was given we obtained the statistical data of WFD average behavior and monitoring period and analyzed the convergence of the Monte Carlo simulation. Our method simulated the WFD process of aircraft structure and got the relevant statistical data thus providing we believe an effective engineering method for WFD evaluation. Key words aircraft computer simulation convergence of numerical methods fatigue crack propagation fatigue damage Monte Carlo methods statistics link-up criterion widespread fatigue damage WFD WFD average behavior

THE PISA CODE. Roberta Lazzeri Department of Aerospace Engineering Pisa University Via G. Caruso, Pisa, Italy

THE PISA CODE. Roberta Lazzeri Department of Aerospace Engineering Pisa University Via G. Caruso, Pisa, Italy 3/2 THE PISA CODE Roberta Lazzeri Department of Aerospace Engineering Pisa University Via G. Caruso, 56122 Pisa, Italy Abstract. A numerical model to simulate the fatigue behaviour of typical aeronautical