Tool for preliminary structural sizing, weight estimation, and aeroelastic optimization of lifting surfaces

摘要: This paper presents the development and implementation of a tool for wing structural sizing aeroelastic optimization in early design steps, where amount available data about structure is not enough to allow high-fidelity finite element analysis optimization. The proposed consists two levels. first level quasi-analytical method weight estimation initially box structure. second an that uses vortex lattice beam compute stress distribution Newton used solve coupled system. adjoint sensitivity any function interest with respect variables. was series optimizations minimize constraints on failure modes aileron effectiveness. Another also find jig shape predefined cruise shape. outputs showed varies quadratically required value