基于多重置信度优化的尾座式无人机共轴双旋翼气动设计OA

The aerodynamic optimization design of coaxial rotor for tailsitter UAV faces challenges in balancing mul-tiple flight modes and addressing complex aerodynamic interference between rotors.To address these challenges,this study establishes a high-fidelity aerodynamic model based on a hybrid Viscous Vortex Particle Method(VVPM)and Vortex-In-Cell(VIC)approach.A multi-fidelity Bayesian optimization strategy is designed to balance computa-tional costs and accuracy for rotor aerodynamic performance.By treating rotor hover power and forward-flight power as dual optimization objectives,a Pareto optimal solution set for the coaxial rotor design is derived.Flow-field analysis reveals that the hover-optimized design employing mid-span wide chord and gradient twist configurations effectively suppresses blade tip vortex development and enhances hover efficiency.The forward-flight optimized design utilizes inner-span increasing chord and high-gradient twist designs to mitigate forward-flight blade tip vortices and profile drag power and improve propulsive efficiency,yet induces premature vortex roll-up and reduces performance in hover.A balanced optimization design,harmonizing chord gradient and twist angle distributions,synergistically balances hover/forward-flight aerodynamic performance,overcoming limitations of single-condition optimization.