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Aerodynamic optimization of a Martian drone integrating propulsive effects and neural-network viscous corrections.

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Title: Aerodynamic optimization of a Martian drone integrating propulsive effects and neural-network viscous corrections.
Authors: Aprovitola, Andrea1 (AUTHOR) andrea.aprovitola@unicampania.it, Iuspa, Luigi1 (AUTHOR), Pezzella, Giuseppe1 (AUTHOR), Viviani, Antonio1 (AUTHOR)
Source: Advances in Space Research. Jul2026, Vol. 78 Issue 2, p1592-1609. 18p.
Subjects: Vortex lattice method, Drone aircraft, Lift (Aerodynamics), Vertically rising aircraft, Computational aerodynamics
Abstract: • Optimization framework for a VTOL fixed-wing Mars drone using coupled airfoil–planform parameterization and surrogate-based aerodynamics. • Hybrid aerodynamic model combining Vortex Lattice Method with Physics-Informed Neural Network viscous corrections for low-Reynolds-number flight on Mars. • Blended-wing–body configuration achieving a maximum lift-to-drag ratio of about 15 at the design operating point while satisfying mass and stability constraints. • Conceptual VTOL integration with dual axial counter-rotating rotors and preliminary hover power requirement of approximately 6 kW in Martian conditions. • Methodology enabling efficient exploration of a large design space at reduced computational cost, supporting early-phase design of future Martian aerial explorers. This work presents an optimization procedure for the conceptual design of a fixed-wing Martian exploration drone, combining low-fidelity aerodynamic computation with viscous corrections assisted by neural-network. The aircraft geometry is described through a dual aligned parameterization of airfoil sections and wing planform, enabling synchronized updates of airfoil shape and wing planform within the optimization loop. The methodology is assessed for a 1 km low-altitude mission in the Martian atmosphere and an estimated free-stream Mach number of M ∞ = 0.2. The optimization maximizes the lift-to-drag ratio under mass and geometric constraints, while enforcing a preliminary longitudinal static-stability requirement. Aerodynamic performance is evaluated through a fast hybrid framework in which a Vortex Lattice method predicts the three-dimensional aerodynamic loads, while a Physics-Informed Neural Network provides viscous and profile-drag corrections guiding the objective-function. The optimized configuration achieves a lift-to-drag ratio of approximately (L / D) max = 15 , with a total mass of M TOM = 26 kg at the design operating point, showing a 15% efficiency improvement over the baseline configuration, while satisfying the longitudinal static-stability constraint with C My α = - 0.35 rad - 1 . A preliminary propulsive assessment of the hovering phase, indicates a power demand of approximately 6 kW. The optimized architecture preserves the baseline mission constraints while achieving an efficiency-oriented configuration, offering promising potential for future Vertical Take-Off and Landing applications. [ABSTRACT FROM AUTHOR]
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Database: Engineering Source
Description
Abstract:• Optimization framework for a VTOL fixed-wing Mars drone using coupled airfoil–planform parameterization and surrogate-based aerodynamics. • Hybrid aerodynamic model combining Vortex Lattice Method with Physics-Informed Neural Network viscous corrections for low-Reynolds-number flight on Mars. • Blended-wing–body configuration achieving a maximum lift-to-drag ratio of about 15 at the design operating point while satisfying mass and stability constraints. • Conceptual VTOL integration with dual axial counter-rotating rotors and preliminary hover power requirement of approximately 6 kW in Martian conditions. • Methodology enabling efficient exploration of a large design space at reduced computational cost, supporting early-phase design of future Martian aerial explorers. This work presents an optimization procedure for the conceptual design of a fixed-wing Martian exploration drone, combining low-fidelity aerodynamic computation with viscous corrections assisted by neural-network. The aircraft geometry is described through a dual aligned parameterization of airfoil sections and wing planform, enabling synchronized updates of airfoil shape and wing planform within the optimization loop. The methodology is assessed for a 1 km low-altitude mission in the Martian atmosphere and an estimated free-stream Mach number of M ∞ = 0.2. The optimization maximizes the lift-to-drag ratio under mass and geometric constraints, while enforcing a preliminary longitudinal static-stability requirement. Aerodynamic performance is evaluated through a fast hybrid framework in which a Vortex Lattice method predicts the three-dimensional aerodynamic loads, while a Physics-Informed Neural Network provides viscous and profile-drag corrections guiding the objective-function. The optimized configuration achieves a lift-to-drag ratio of approximately (L / D) max = 15 , with a total mass of M TOM = 26 kg at the design operating point, showing a 15% efficiency improvement over the baseline configuration, while satisfying the longitudinal static-stability constraint with C My α = - 0.35 rad - 1 . A preliminary propulsive assessment of the hovering phase, indicates a power demand of approximately 6 kW. The optimized architecture preserves the baseline mission constraints while achieving an efficiency-oriented configuration, offering promising potential for future Vertical Take-Off and Landing applications. [ABSTRACT FROM AUTHOR]
ISSN:02731177
DOI:10.1016/j.asr.2026.04.092