Structural Optimization Framework for Aircraft subject to Transient Maneuver and Gust Loads

摘要

This paper describes a framework for the modeling and sizing of flexible aircraft subject to static and transient maneuver loads, control inputs and external disturbances due to atmospheric turbulence. An integrated coupled model of the flexible aircraft comprising a nonlinear rigid body flight dynamics model and a linear aeroelastic model is used to obtain the equivalent static loads on the structure for a given set of flight cases. These are used in a subsequent structural optimization step to update the structure to obtain a minimum mass design while fulfilling requirements on strength and stability. The updated structural model is fed back to the maneuver simulation in an automated process enabling a rapid search for a consistent design. In the paper, this process is applied to a blended wing body configuration developed within the ACFA 2020 research project. The structural loads resulting from a given set of flight inputs are examined and used to obtain a mass optimized structure.