Wing aerostructural optimization under uncertain payload weight and aircraft range

Jacome, L.B. and Elham, A. (2016) Wing aerostructural optimization under uncertain payload weight and aircraft range. In 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics.. (doi:10.2514/6.2016-1660).

Abstract

An uncertainty-based approach is undertaken to deal with the multi-point wing aerostructural optimization. The flight points are determined by the quadruple set of parameters: Mach number, cruise altitude, carried payload and flight range. From this set the payload and range are modeled as probabilistically uncertain based on U.S. flight data for the operations of an A320 aircraft with CFM engines. The fuel burn is selected as the performance metric to optimize. Failure criteria, aileron efficiency and field performance considerations where formulated as constraints. The wing is parametrized through its planform, airfoil sections and structural thickness. The analyses disciplines consist of an aerostructural solver and a surrogate-based mission analysis. For such an optimization task, a gradient-based algorithm was used in conjunction with coupled adjoint methods and a fuel burn sensitivity analytical formula. Another key enabler was a cost-effective non-intrusive uncertainty propagator that allowed to optimize an aircraft with legacy analysis code within a computational budget.

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