Prometheus Asteroid Redirection Mission: Mission Design, Spacecraft Design, Orbital Dynamics Code Development
Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
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
Engineering and Technology
IdentifiersURN: urn:nbn:se:ltu:diva-174OAI: oai:DiVA.org:ltu-174DiVA: diva2:972110
Space Engineering, master's level