The Fatigue Constraint Topology Optimization Of The Wing Structural Components

Topology optimization is widely used in aerospace plane structure design, to lighten the weight ofthe aircraft structure and improve the performance. But at the same time due to the stress level rise italso led to much more fatigue problems. For most metallic materials, fatigue strength is much lowerthan the ultimate strength, although structure to meet the requirements of the static strength underLimit load, but structure may not satisfy the fatigue life of the design requirements under fatigue load,so the research on topological optimization under fatigue life constraint has important significance.In this paper，a new method which can translate the fatigue life constraint into stress constraint isput forward based on structure fatigue life analysis. Calculate the maximum stress under design lifeby structural fatigue life analysis method based on fatigue load spectrum combined with thecomponent life. Then do the topology optimization with this maximum stress as constraint. With twoexamples, the validity of the method is proposed in this paper.Finally, established the finite element models of a transport aircraft wing rib and a unmannedaircraft wing joint with the Commercial software HyperMesh, Then Completed finite element analysisof the models; To reach the minimum weight as the goal, OptiStruct combining withcommon-substructure approach under multiple loading cases for topology optimization design is usedto obtain the topology structure under the maximum stress constraint. And based on this, engineeringtreatment is done to the rib and the joint. Structure weight loss is realized at the same time meet thefatigue life requirements. This method provide a reference to this certain kind of structure design.