Conceptual modeling and analysis of drag-augmented supersonic retropropulsion for application in Mars entry, descent, and landing vehicles

The development of new decelerator technologies will be required as the payload mass for future Mars landing missions increases beyond the current state-of-the-art capability. This thesis examines the potential for supersonic retropropulsion applied on entry, descent, and landing vehicles to increase the landed payload mass. This thesis describes the development of a model characterizing the drag augmentation capabilities of supersonic retropropulsion flow interactions. The model captures the dominant flow physics of pressure conservation through shock cascade structures. A study of drag-augmented supersonic retropropulsion operation concepts for use in Mars entry, descent, and landing is also presented. A range of operation intervals are examined to illustrate the flight regimes where supersonic retropropulsion is most effective. The feasibility of two concepts combining supersonic decelerator concepts is also investigated. The potential for these hybrid solutions to substantially increase the payload mass capability by using each technology in the appropriate flight regime is demonstrated.