Abstract: To address the high propellant consumption during Mars orbit insertion for sample return missions, this study investigates the feasibility of utilizing Martian atmosphere through aeroassist technologies. A comprehensive review of international engineering applications and research status of aerobraking and aerocapture technologies is conducted, with in-depth analysis of key technologies including orbit strategy design, aerodynamic and aerothermodynamic environment analysis, atmospheric modeling, in-flight measurement, control strategies, as well as capture corridor design and deployable thermal protection systems. The study reveals that aerobraking is a mature technology (validated in four NASA missions), capable of saving approximately 1.2 km/s of ΔV, with drag coefficients ranging from 1.9 to 2.0 and surface heat flux not exceeding 8.21 kW/m². Aerocapture presents challenges, particularly in deployable heatshield technology. For upcoming Mars sample return missions, aerobraking is identified as the most technically viable aeroassist approach currently, requiring emphasis on deceleration efficiency, stability, and aerothermal management with in-flight monitoring during implementation. Aerocapture necessitates dedicated efforts in optimizing capture corridors, designing specialized aerodynamic configurations, and validating deployable structures. This research provides a crucial technical reference for mission engineering.