LAUSR

Abstract Mars rotorcraft, as an aerial auxiliary platform can assist Mars rover to complete exploration missions, is of great significance in the field of planetary exploration. The complex terrain on Mars limits the working range of the Mars rover, whereas a rotorcraft can acquire high detection speed and efficiency, even fixed-point sample using the ability of vertical takeoff and landing. Very little work has been done to analyze the Mars rotorcraft hovering process and there is also limited experimental data exist on the unique Mars flight conditions. A proper understanding of the hovering process is necessary to design a Mars rotorcraft and verify whether it is appropriate or not. In this work, a modified BEMT-CFD model is developed to analyze inflow distribution in the wingspan direction and to predict the aerodynamic performance of the rotor system. Based on the developed model, a suitable airfoil is selected and the operational parameters are investigated to design a suitable rotor configuration for the Mars rotorcraft. Hover experiments demonstrate that the modified model can effectively predict the rotor hover performance. Using the suitable blade pitch angle and rotational speed, the rotor can generate enough thrust to support a 500 g rotorcraft to fly in the simulated Mars environment.