High-Fidelity Structural Design and Optimization of Blended-Wing-Body Transports

摘要

This paper focuses on the use of high-fidelity methods to determine the structural feasibility of blended-wing-body aircraft as a next-generation airliner. It also attempts to assess the feasibility of primary structural weight predictions using geometrically-accurate finite element models for potential use in conceptual design environments. Whereas previous studies have used low- to medium-fidelity FEA studies to determine the primary structural weight, this study uses more detailed finite element models (with explicit shell meshes of the major structural components) to provide a better estimate. The test configurations used were the Boeing BWB-450-1L and the NASA ERA HWB. Using the Nastran SOL 200 optimizer, the total primary structural weight and breakdown were determined for the two aircraft. It was found that both primary structural weights accounted for approximately 16% of the MTOW, indicating that the primary does not take an excessive weight ratio and allows for a feasible structure. A further multi-disciplinary aero-structural optimization on the HWB found that the range can also be optimized slightly with a more triangular lift, resulting in a 12% lower structural weight compared to the standalone structural optimization.