Fully-Propulsive Mars Atmospheric Transit Strategies for High-Mass Missions

Abstract

A systems analysis focused on the use of propulsion throughout the entry, descent, and landing sequence at Mars for high-payload missions is presented. Trajectory simulation and mass sizing are performed to analyze the feasibility of a fully-propulsive descent. A heat rate boundary and associated control law are developed in an effort to limit the heat rate encountered by the vehicle. Analysis is performed to explore the full-propulsive entry, descent, and landing strategy's sensitivity to the vehicle's propulsive capabilities and aeropropulsive and vehicle models. The strategy is examined across a range of initial masses and heat rate constraints, outlining an envelope of feasibility. The proposed architecture is compared against traditional Mars entry, descent, and landing systems in which significant aeroassist technology is employed. With this information, a systematic overview of the impact of a fully-propulsive system on spacecraft design and functionality is offered.

Additional details