Stacking sequence optimisation of an aircraft wing skin

Abstract This paper demonstrates a stacking sequence optimisation process of composite aircraft wing skin. A two-stage approach is employed to satisfy all sizing requirements this industrial sized, medium altitude, long endurance drone. In the first stage optimisation, generic stacks are used describe thickness and stiffness properties structure while considering both structural discrete guidelines such as blending. second mathematical programming solve Mixed Integer Linear Programming formulation optimisation. The proposed suitable for real-world thick structures comprised multiple patches. Different discretisation strategies examined retrieval sequences, with each one having different influence on satisfaction constraints across various sub-components wing. weight penalty introduced between continuous final design negligible.