A passive load alleviation aircraft wing: topology optimization for maximizing nonlinear bending–torsion coupling

Abstract Aircraft wings with passive load alleviation morph their shape to a configuration where the aerodynamic forces are reduced without use of an actuator. In our research, we exploit geometric nonlinearities inner wing structure maximize alleviation. order find designs desired properties, propose topology optimization approach. Passive is achieved through bending–torsion coupling. The twist will reduce angle attack, thus lowering forces. Consequently, objective function torsion angle. Since morphing should only affect loads that exceed normal maneuvering loads, displacement constraint enforced, preventing at lower force levels. Maximizing lead topologies for which finite element solver cannot solution. To circumvent this, adding compliance value function. This term has weighting function, controls how much influence has: after set number iterations, initially high level drop. We used nonlinear formulation linear elastic material model. addition energy interpolation scheme reduces mesh distortion. successfully applied proposed methodology two different test cases resembling aircraft box section. These illustrate methodology’s potential designing new geometries behavior. discuss what design features can be deduced and they achieve structural response.