Design of a Micro-Compressor for Deflected Slipstream CoFlow Jet Airfoils in Martian Conditions

This study presents the design and analysis of a micro-compressor system tailored for ultra-low air density conditions, specifically to match the Martian atmosphere. The micro-compressor is a critical component for the Deflected Slipstream CoFlow Jet (DS-CFJ) airfoil aircraft, intended to enable sustained vertical takeoff/landing flight in the conditions of Mars. The Martian atmosphere, with its extremely low density, poses significant challenges for generating sufficient lift and maintaining efficient propulsion. The micro-compressor is designed to enhance the performance of the DS-CFJ system by providing the necessary airflow to increase lift and remove flow separation, with a design target of a total pressure ratio (Ptr = 1.6) and a mass flow rate of 2.9 g/s, thus enabling efficient aerodynamic performance. The micro-compressor performance is based on the requirement of the MAGGIE (Mars Aerial and Ground Global Intelligent Explorer) aircraft design. Using computational fluid dynamics (CFD) simulations, the micro-compressor is designed for minimal power consumption while achieving the target total pressure ratio and mass flow rate under Martian conditions. The results demonstrate that the micro-compressor can obtain the requirements of the MAGGIE CFJ electric VTOL aircraft. This research lays the foundation for future development of Martian aircraft, highlighting the potential of integrating micro-compressor technology with CFJ airfoils to overcome the limitations posed by the low-density Martian environment.