Abstract: For a Mars aircraft exploration mission, a coaxial Mars rotorcraft is proposed. The structural parameters, such as the blade airfoil, planform, and twist angle, are optimized based on the computational fluid dynamics methods. The aerodynamic model of the rotor is established based on the blade element theory and momentum theory. The flight parameters such as rotor speed, rotor spacing, and blade installation angle are selected based on the numerical simulation methods, which prompt the design of the structure and control system of the prototype “MarsBird I”. A Martian atmosphere simulator and a combined device for gravity compensation and motion constraint are constructed to carry out the ground flight test of the Mars rotorcraft under a simulated Mars environment, which verifies the propulsion performance of the coaxial Mars rotorcraft. Besides, we prospect the research directions of the Mars rotorcraft technology. The research results provide an important reference for China’s Mars exploration project.

Key words: Mars rotorcraft, Coaxial rotor, Hover characteristics, Mars atmosphere simulation, Experimental verification