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

摘要

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