Multidisciplinary Design Optimization of a blended wing body Mars explorer

Abstract

An optimization procedure of a non-conventional VTOL drone for Martian operations is proposed. A Multidisciplinary Design Optimization framework is implemented within an automated ANSYS APDL environment, integrating OpenVSP for geometry generation and low-fidelity aerodynamic analysis. The optimization aims to maximize aerodynamic efficiency while ensuring longitudinal stability and trimmability under nominal cruise conditions (M = 0.2 and Re = 9.7 × 104 ). The optimization is constrained by mass and aeroshell-compatibility requirements. The results indicate that the investigated configuration leads to a constraint-dominated design space, where performance is strongly influenced by trim-related requirements. Within this framework, the paper highlights the effectiveness of low-fidelity methods in assessing aerodynamic efficiency trends, while remaining limited under low-Reynolds-number conditions where flow separation effects become significant. A maximum lift-to-drag ratio improvement of approximately 17% is achieved with respect to a benchmark configuration. Finally, off-design validation is performed through RANS CFD analyses using the DLR-TAU code to assess aerodynamic performance and static stability characteristics.