Multi Constraints Optimization Method And Application Research Of Wing Structure

In view of the current single constraint topology optimization model,this paper put forward a combination of volume constraints and manufacturing constraints(such as structural member size constraints,symmetry constraint,draft constraint etc.).By introducing the variable density topology optimization method with SIMP as interpolation model,the multi constraints topology optimization model was established.Taking into account that forces and constraints of the wing are very complicated,the extraction of the wing constraints are completed,and the extracted constraints are classified and simplified.Finite element model of wing structure is established,meanwhile the mesh is decomposed and the forces and boundary conditions of the wing are determined.Topology optimization of wing structure using multi constraints topology optimization,combined with the results of the obtained wing topology optimization and design experience,the structure of the wing beam,wing wall and ribs are designed.The finite element model is established base on the wing structure layout,the failure criterion of the skin and the overall buckling of the wing structure are restricted.The plies thickness of the composite skin of the wing is optimized.At the same time,the thickness of the ribs is optimized.Successful convergence of the conceptual design in the topology optimization and detailed design optimization.It provides a new idea for the aircraft designers to design the structure of the wing.The multi constraints topology optimization is carried out for the NO.2 rib in the wing structure.By changing the topology optimization constraints parameters in the model,to get the optimization results of different rib structures.The topology optimization results are analyzed,and the influence of the change of the constraint parameters on the topology optimization results is obtained.