{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/59696"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/59696","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"An application of linear covariance analysis to the design of responsive near-rendezvous missions","abstract":"This thesis investigates a new class of launch vehicles capable of being released from an aircraft which ultimately have the goal of achieving near-rendezvous conditions at orbital altitudes up to 800 km. These launch vehicles would be capable of carrying small payloads, on the order of two to six kilograms, and would be much more responsive to a customer's needs than the current space launch infrastructure, in which it may take months of preparation for a launch. To fully describe the mission in this thesis, it is broken up into three phases: atmospheric launch, orbit raising, and near-rendezvous operations. An analysis method known as Linear Covariance analysis is introduced to provide a platform of estimating the navigation covariance and dispersion of the spacecraft during the second and third phases, while the first phase, up to main-engine-cutoff, is examined using a three degree-of-freedom simulation. The goal of this thesis is to demonstrate the utility of Linear Covariance analysis to responsive space mission planning. This is accomplished by first explaining the mathematics that underlie the method. Next the software used for the analysis, Lincov Tools, is explained in detail, the mission is examined more closely, and the hardware for both the payload and launch vehicle are briefly discussed. Finally, the combination of the three degree-of-freedom simulation and Lincov Tools are employed to the space mission and the results are presented.","abstract_html":"This thesis investigates a new class of launch vehicles capable of being released from an aircraft which ultimately have the goal of achieving near-rendezvous conditions at orbital altitudes up to 800 km. These launch vehicles would be capable of carrying small payloads, on the order of two to six kilograms, and would be much more responsive to a customer's needs than the current space launch infrastructure, in which it may take months of preparation for a launch. To fully describe the mission in this thesis, it is broken up into three phases: atmospheric launch, orbit raising, and near-rendezvous operations. An analysis method known as Linear Covariance analysis is introduced to provide a platform of estimating the navigation covariance and dispersion of the spacecraft during the second and third phases, while the first phase, up to main-engine-cutoff, is examined using a three degree-of-freedom simulation. The goal of this thesis is to demonstrate the utility of Linear Covariance analysis to responsive space mission planning. This is accomplished by first explaining the mathematics that underlie the method. Next the software used for the analysis, Lincov Tools, is explained in detail, the mission is examined more closely, and the hardware for both the payload and launch vehicle are briefly discussed. Finally, the combination of the three degree-of-freedom simulation and Lincov Tools are employed to the space mission and the results are presented.","abstract_has_math":false,"creators":["Visser, Benjamin Lee"],"institution":"Massachusetts Institute of Technology","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.","school":null,"contributors":[],"advisors":["Piero Miotto."],"committee_chairs":[],"committee_members":[],"year":2007,"date_issued":"2007","date_published":"2007","updated_at":"2026-07-22T22:21:00Z","subjects":["Aeronautics and Astronautics."],"languages":["eng"],"rights":["M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission."],"rights_urls":["http://dspace.mit.edu/handle/1721.1/7582"],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/1721.1/59696","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Piero Miotto."]},{"key":"dc:contributor.department","label":"Department","values":["Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics."]},{"key":"dc:contributor.other","label":"Dc Contributor Other","values":["Massachusetts Institute of Technology. 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To fully describe the mission in this thesis, it is broken up into three phases: atmospheric launch, orbit raising, and near-rendezvous operations. An analysis method known as Linear Covariance analysis is introduced to provide a platform of estimating the navigation covariance and dispersion of the spacecraft during the second and third phases, while the first phase, up to main-engine-cutoff, is examined using a three degree-of-freedom simulation. The goal of this thesis is to demonstrate the utility of Linear Covariance analysis to responsive space mission planning. This is accomplished by first explaining the mathematics that underlie the method. Next the software used for the analysis, Lincov Tools, is explained in detail, the mission is examined more closely, and the hardware for both the payload and launch vehicle are briefly discussed. 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