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Prometheus Asteroid Redirection Mission: Mission Design, Spacecraft Design, Orbital Dynamics Code Development
LuleƄ University of Technology, Department of Computer Science, Electrical and Space Engineering.
2016 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

This report will design a mission and spacecraft to redirect the first Near-Earth Object (NEO) to a stable orbit in the Earth-Moon system. The mission profile includes a soon-as-possible launch, spiral-out escape from the Earth-Moon system, rendezvous, ion beam redirection method, and decommissioning phases, each with accompanying orbital dynamics code written in Matlab. The spacecraft design will include power and mass budgets for each of the subsystems including power, thermal, communications, GNC, fuel, and thrusters. The orbital dynamics code is detailed in the final section of the report.

Place, publisher, year, edition, pages
2016.
National Category
Engineering and Technology
Identifiers
URN: urn:nbn:se:ltu:diva-174OAI: oai:DiVA.org:ltu-174DiVA: diva2:972110
Educational program
Space Engineering, master's level
Supervisors
Examiners
Available from: 2016-09-21 Created: 2016-09-20 Last updated: 2016-09-21Bibliographically approved

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