As part of a project INTES has performed the topology optimization for an aircraft fuselage in order to demonstrate the use of the method for aircraft structures. The flexibility of the structure was used as a target function to maximize the stiffness. The weight target was halving the weight of the starting model. Loads and kinematic boundary conditions were given. Another object of the calculation was to show that fully converged optimization results show a clear separation of the model in full and empty elements (degree of filling).

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