Feasibility Study of a Carbon Dioxide Breathing, Solid-Fueled Ramjet for Martian Descent and Landing of Human Class Payloads

This study analyzes the cross-range capabilities of solid-fueled ramjets in a Martian atmosphere
for applications in entry, descent, and landing. Trajectories and engine operability are
characterized using Mach and dynamic pressure operational points. It is predicted that use of
atmosphere-breathing propulsion will enable access to additional surface latitudes without the
need for orbital plane changes. Development of an integrated design environment facilitates
preliminary ramjet design and analysis, and enables sensitivity studies to identify high impact
areas of technology development. In addition, additive manufacturing supports prototyping,
rapid ground testing, and allows for utilization of complex geometries.