Journal Article

Numerical Prediction of Fatigue Life for Landing Gear Considering the Shock Absorber Travel

Jiang, Yiyao, Tang, Haihong, Ding, Jianbin, Cheng, Jinsong, Liu, Panglun, Jiang, Bingyan

2025

Overview

Due to the complexity of the landing gear’s (LG) structural integrity and its loads under various static or dynamic working conditions, the fatigue life assessment for LG is a highly challenging task. On the basis of the whole geometric model of a large passenger aircraft’s main landing gear (MLG), the quasi-static finite element model (FEM) of the whole MLG is established, and the high-cycle fatigue issue of the Main Fitting (MF) is studied by considering the variation in shock absorber travel (SAT). Firstly, the ground loads under actual fatigue conditions are equivalently converted into the forces acting on the center of the left and right axles of the MLG, and based on these spatial force decompositions, the magnitude and direction of the load for 12 different basic unit load cases (ULC) are obtained. That is, the stress of the MLG under actual fatigue conditions can be obtained by superimposing these ULCs. Then, considering that the SAT of the MLG varies under different fatigue conditions, and to reduce the number of finite element (FE) simulations, this article simplifies all the SAT experienced by the MLG into seven specific values, so as to establish seven quasi-static FEMs of the MLG with the specified stroke of the shock absorber. In this way, the fatigue stress of the MLG with any actual SAT can be obtained by interpolating the stress components of the seven FEMs. Only 84 FE simulations are needed to efficiently obtain the fatigue stress spectra from the ground load spectra. Finally, according to the material S-N curve and Miner’s damage accumulation criterion, evaluate the fatigue life of the Main Fitting. The results of the stress component interpolation and superposition method show that at least five different SATs of the whole MLG’s FEM are needed to effectively convert the fatigue loads into a stress spectrum. The fatigue life prediction results indicate that the minimum lifespan of the MF is 53164 landings, which means that the fatigue life meets the requirement design.

• Publisher: MDPI AG
• Subject: Aircraft / Basic converters / Crack propagation / Curve fitting / Damage accumulation / Damage assessment / Decomposition / Fatigue failure / fatigue life / Fatigue life assessment / Finite element method / High cycle fatigue / Interpolation / Landing gear / Life assessment / Life prediction / main landing gear / Mathematical models / Numerical prediction / Passenger aircraft / S N diagrams / shock absorber travel / Shock absorbers / Spectra / stress component superposition / Structural integrity / unit load split / Unit loads / Wheels / Working conditions