Within the context of both manned and robotic spaceflight activities, orbits near the Earth-Moon L1 and L2 libration points could support lunar surface operations and serve as staging areas for future missions to near-Earth asteroids as well as Mars. In fact, an Earth-Moon L2 libration point orbit has been proposed as a potential hub for excursions to Mars as well as activities in support of planetary exploration. Yet, the dynamical environment within the Earth-Moon system is complex and, consequently, trajectory design in the vicinity of Earth-Moon L1 and L2 is nontrivial. Routine transfers between an Earth-Moon L1/L2 facility and Mars also requires design strategies to deliver trajectory arcs that are characterized by a coupling between different multi-body gravitational environments across two-, three- and four body systems. This investigation employs an approach to solve the general problem for transfers from the Earth-Moon libration point orbits to a destination object. Mars, Jupiter, and a near-Earth asteroid (2006RH120) are incorporated as sample destination objects, and general trajectory design procedures for multiple transfer scenarios including manifold and non-manifold options are developed by utilizing simplified models based on the knowledge of the circular restricted three-body problem. Then, the solutions are transitioned to higher-fidelity models; results for multiple departure/arrival scenarios are compared.
","abstract_html":"<p>Within the context of both manned and robotic spaceflight activities, orbits near the Earth-Moon L1 and L2 libration points could support lunar surface operations and serve as staging areas for future missions to near-Earth asteroids as well as Mars. In fact, an Earth-Moon L2 libration point orbit has been proposed as a potential hub for excursions to Mars as well as activities in support of planetary exploration. Yet, the dynamical environment within the Earth-Moon system is complex and, consequently, trajectory design in the vicinity of Earth-Moon L1 and L2 is nontrivial. Routine transfers between an Earth-Moon L1/L2 facility and Mars also requires design strategies to deliver trajectory arcs that are characterized by a coupling between different multi-body gravitational environments across two-, three- and four body systems. This investigation employs an approach to solve the general problem for transfers from the Earth-Moon libration point orbits to a destination object. Mars, Jupiter, and a near-Earth asteroid (2006RH120) are incorporated as sample destination objects, and general trajectory design procedures for multiple transfer scenarios including manifold and non-manifold options are developed by utilizing simplified models based on the knowledge of the circular restricted three-body problem. Then, the solutions are transitioned to higher-fidelity models; results for multiple departure/arrival scenarios are compared.</p>","abstract_has_math":false,"creators":["Kakoi, Masaki"],"institution":null,"degree_name":"Doctor of Philosophy (PhD)","degree_level":"Dissertation","degree_discipline":"Aeronautics and Astronautics","degree_department":null,"school":null,"contributors":["Kathleen C. Howell","James M. Longuski","M. Corless","Anil Bajaj"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2015,"date_issued":"2015-04-01T07:00:00Z","date_published":"2015-04-01T07:00:00Z","updated_at":"2026-07-24T03:53:28Z","subjects":["Aerospace Engineering"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://docs.lib.purdue.edu/open_access_dissertations/482","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Kathleen C. Howell","James M. Longuski","M. Corless","Anil Bajaj"]},{"key":"dc:creator","label":"Author","values":["Kakoi, Masaki"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aeronautics and Astronautics"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Dissertation"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Doctor of Philosophy (PhD)"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Aerospace Engineering"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://docs.lib.purdue.edu/open_access_dissertations/482"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Within the context of both manned and robotic spaceflight activities, orbits near the Earth-Moon L1 and L2 libration points could support lunar surface operations and serve as staging areas for future missions to near-Earth asteroids as well as Mars. In fact, an Earth-Moon L2 libration point orbit has been proposed as a potential hub for excursions to Mars as well as activities in support of planetary exploration. Yet, the dynamical environment within the Earth-Moon system is complex and, consequently, trajectory design in the vicinity of Earth-Moon L1 and L2 is nontrivial. Routine transfers between an Earth-Moon L1/L2 facility and Mars also requires design strategies to deliver trajectory arcs that are characterized by a coupling between different multi-body gravitational environments across two-, three- and four body systems. This investigation employs an approach to solve the general problem for transfers from the Earth-Moon libration point orbits to a destination object. Mars, Jupiter, and a near-Earth asteroid (2006RH120) are incorporated as sample destination objects, and general trajectory design procedures for multiple transfer scenarios including manifold and non-manifold options are developed by utilizing simplified models based on the knowledge of the circular restricted three-body problem. Then, the solutions are transitioned to higher-fidelity models; results for multiple departure/arrival scenarios are compared.
"]},{"key":"dc:title","label":"Title","values":["Design of transfers from Earth-Moon L 1/L2 libration point orbits to a destination object"]}]}],"canonical_facts":{"dc:contributor":["Kathleen C. Howell","James M. Longuski","M. Corless","Anil Bajaj"],"dc:creator":["Kakoi, Masaki"],"dc:description.abstract":["Within the context of both manned and robotic spaceflight activities, orbits near the Earth-Moon L1 and L2 libration points could support lunar surface operations and serve as staging areas for future missions to near-Earth asteroids as well as Mars. In fact, an Earth-Moon L2 libration point orbit has been proposed as a potential hub for excursions to Mars as well as activities in support of planetary exploration. Yet, the dynamical environment within the Earth-Moon system is complex and, consequently, trajectory design in the vicinity of Earth-Moon L1 and L2 is nontrivial. Routine transfers between an Earth-Moon L1/L2 facility and Mars also requires design strategies to deliver trajectory arcs that are characterized by a coupling between different multi-body gravitational environments across two-, three- and four body systems. This investigation employs an approach to solve the general problem for transfers from the Earth-Moon libration point orbits to a destination object. Mars, Jupiter, and a near-Earth asteroid (2006RH120) are incorporated as sample destination objects, and general trajectory design procedures for multiple transfer scenarios including manifold and non-manifold options are developed by utilizing simplified models based on the knowledge of the circular restricted three-body problem. Then, the solutions are transitioned to higher-fidelity models; results for multiple departure/arrival scenarios are compared.
"],"dc:identifier":["https://docs.lib.purdue.edu/open_access_dissertations/482"],"dc:subject":["Aerospace Engineering"],"dc:title":["Design of transfers from Earth-Moon L 1/L2 libration point orbits to a destination object"],"thesis:degree_discipline":["Aeronautics and Astronautics"],"thesis:degree_level":["Dissertation"],"thesis:degree_name":["Doctor of Philosophy (PhD)"]},"updated_at":"2026-07-24T03:53:28Z"}