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  • An Analysis and Selection of Launch Windows and Orbital Trajectories for the JESSE OWENS Thermonuclear Propulsion Interplanetary Spaceflight Mission

    Paper number

    IAC-18,D2,8-A5.4,4,x46366

    Author

    Mr. Taylor Huneycutt, United States, The Ohio State University College of Engineering

    Coauthor

    Dr. John M. Horack, United States, The Ohio State University College of Engineering

    Coauthor

    Dr. Elizabeth Newton, United States, The Ohio State University

    Coauthor

    Mr. Stephen Ioas, United States, The Ohio State University College of Engineering

    Coauthor

    Mr. Ryan Howard, United States, The Ohio State University College of Engineering

    Coauthor

    Mr. Skylar Dierker, United States, The Ohio State University College of Engineering

    Coauthor

    Mr. Craig Heim, United States, The Ohio State University College of Engineering

    Coauthor

    Mr. Zachary Allen, United States, The Ohio State University College of Engineering

    Year

    2018

    Abstract
    A time-based Simulink model is used to optimize the numerous orbital mechanics parameters associated with interplanetary spaceflight. More specifically, the thrust magnitude, duration, location, and frequency are all optimized with respect to the relative distance between a spacecraft’s origin and its destination in order to dramatically reduce the time on transit between these two points. In this paper, a round-trip between Earth and Jupiter is considered, with comparisons being drawn between launch windows based on conventional propulsion and those based on this nuclear thermal propulsion (NTP). Based on the “optimal” combination of these parameters, it is demonstrated that this example of NTP (A reactor-nozzle combination characterized by 111 kN of thrust and Isp of 850 seconds) is a vastly superior approach to spacecraft propulsion in comparison to conventional chemical means. In employing nuclear thermal propulsive methods, the consequential reduction in time on transit would improve the accessibility of deep space destinations and enable future manned missions beyond the Earth’s immediate neighborhood.
    Abstract document

    IAC-18,D2,8-A5.4,4,x46366.brief.pdf

    Manuscript document

    IAC-18,D2,8-A5.4,4,x46366.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.