The successful flight demonstration of Ingenuity in the Martian atmosphere offers novel insights for Mars exploration, where the rotor, as a core component of Mars drones, critically determines mission success. This study presents a surrogate model-based optimization method for rotor design, employing the clf5605 airfoil as a baseline for parametric modeling. To achieve efficient optimization, a sensitivity analysis was first conducted to identify high-impact design variables. A radial basis function neural network surrogate model was then constructed, coupled with a non-dominated sorting genetic algorithm to derive optimal airfoil configurations. Results indicate that five key parameter categories—twist angle distribution, chord length distribution, thickness distribution, maximum curvature position, and maximum curvature (totaling 14 control parameters)—dominate rotor performance, with sensitivity coefficients of 0.914 (Earth) and 0.947 (Mars). The optimized airfoils outperformed the clf5605 baseline across all objectives: a 16.4% increase in the A1 figure of merit, a 10.03% boost in the A2 lift coefficient, a 10.00% reduction in A3 rotor mass, and an 8.62% decrease in A4 energy consumption. Aerodynamic tests of an A1 prototype under Earth conditions further validated the method's efficacy. This work systematically analyzes the influence of rotor parameters on aerodynamic performance and provides a practical framework for future rotor optimization in extraterrestrial environments.

This study investigates the impact of rotor spacing on the aerodynamic performance of a coaxialcopter and promotes an innovative regulated control strategy for the coaxial drone. The present research introduces a coaxialcopter with variable rotor spacing, and employing finite element numerical simulations, we assess the aerodynamic behavior of this novel configuration. Through comprehensive measurements and analysis of its aerodynamic performance across varying rotor spacings from 0.1 R to 1 R, we validate the effectiveness of a rotor-spacing control strategy for enhancing takeoff maneuvers. The numerical simulation and experiment results reveal that the performance characteristics of both the upper and lower rotors converge toward that of a single rotor as the space ratio increases, along with a reduction in their thrust fluctuations and aerodynamic performance periodicity. Considering stable power consumption patterns and endurance performance, we analyzed the interrelations binding the pitch distance of the rotors, rotational speed, and pitch angle, vis à vis the thrust coefficient and power coefficient. Through the parameter optimization method, we demonstrate that adjusting rotor spacing offers a practical means to enhance payload capacity without increasing the power input, thereby improving efficiency, which validates the practicality and efficacy of the parameter optimization approach. Furthermore, optimizing rotor spacing for specific operational scenarios enhances overall aerodynamic performance, suggesting a viable flight control strategy for takeoff and landing conditions for coaxial drones.

This study investigates the impact of rotor spacing on the aerodynamic performance of a coaxialcopter. It has been observed that a small distance between two rotors can result in significant interaction between the propellers, consequently affecting the rotor's aerodynamic efficiency. Exploiting this characteristic, the present research introduces a coaxialcopter with variable rotor spacing. Employing finite element numerical simulations, we assess the aerodynamic behavior of this novel configuration. Through comprehensive measurements and analysis of its aerodynamic performance across varying rotor spacings from 0.1R to 1R, we validate the effectiveness of a rotor spacing control strategy for enhancing takeoff maneuvers. Our numerical simulation results reveal that the performance characteristics of both upper and lower rotor converges toward that of a single rotor as pitch ratio increases, along with the reduce of their thrust fluctuations and aerodynamic performance periodicity. Considering stable power consumption patterns and endurance performance, we analysis the interrelations binding of pitch distance of the rotors, rotational speed, and pitch angle, vis-à-vis the thrust coefficient and power coefficient. Through parameter optimization method, we demonstrate that adjusting rotor spacing offers a practical means to enhance payload capacity without increasing power input, thereby improving the efficiency, which validates the practicality and efficacy of the parameter optimization approach. Furthermore, optimizing rotor spacing for specific operational scenarios enhances overall aerodynamic performance, suggesting a viable flight control strategy for takeoff and landing conditions.