Departure Phase Aborts for Manned Mars Missions

dc.contributor.advisorLewis, Mark Jen_US
dc.contributor.authorDissel, Adam Frederiken_US
dc.contributor.departmentAerospace Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.description.abstractNASA goals are set on resumption of human activity on the Moon and extending manned missions to Mars. Abort options are key elements of any system designed to safeguard human lives and stated requirements stipulate the provision of an abort capability throughout the mission. The present investigation will focus on the formulation and analysis of possible abort modes during the Earth departure phase of manned Mars interplanetary transfers. Though of short duration, the departure phase encompasses a mission timeline where failures have frequently become manifest in historical manned spacecraft necessitating the inclusion of a departure phase abort capability. Investigated abort modes included aborts to atmospheric entry, and to Earth or Moon orbit. Considered interplanetary trajectory types included conjunction, opposition, and free-return trajectory classes. All abort modes were analyzed for aborts initiated at multiple points along each of these possible departure trajectories across all launch opportunities of the fifteen-year Earth-Mars inertial period. The consistently low departure velocities of the conjunction trajectories facilitated the greatest abort capability. An analysis of Mars transportation architectures was performed to determine the amount of available delta V inherent in each candidate architecture for executing departure aborts. Results indicate that a delta V of at least 4 km/s is required to achieve a continuous departure phase entry abort capability with abort flights less than three weeks duration for all transfer opportunity years. Less demanding transfer years have a corresponding increase in capability. The Earth orbit abort mode does not become widely achievable until more than 6 km/s delta V is provided; a capacity not manifest in any considered architecture. Optimization of the Moon abort mode resulted in slight departure date shifts to achieve improved lunar alignments. The Moon abort mode is only widely achievable for conjunction transfers during the optimum transfer years and delta V values greater than 4 km/s. A lesser delta V potential of 3 km/s is sufficient to enable entry aborts during the least demanding transfer opportunity years. Extensive abort capability is achievable for high delta V capable Mars architectures. Less propulsively capable architectures achieve moderate abort capability during favorable opportunity years.en_US
dc.format.extent15890479 bytes
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledMars abortsen_US
dc.subject.pquncontrolledMars architecturesen_US
dc.subject.pquncontrolledfree returnen_US
dc.subject.pquncontrolleddeparture phaseen_US
dc.subject.pquncontrolledmanned spacecraften_US
dc.titleDeparture Phase Aborts for Manned Mars Missionsen_US


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