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Virginia Polytechnic Institute
Effect of aerodynamics on the perturbations of a space vehicle orbit
Abstract
dc:description.abstractThe present study was undertaken to determine the effects of the aerodynamics on a close earth orbit and reentry trajectory. The aerodynamic influence is compared to the effects of the earth’s oblateness, the sun, and the moon. In order to obtain maximum accuracy and computational speed Encke’s perturbative procedures were used during orbital periods and Cowell’s integration procedures during thrust and reentry periods.
Degree
thesis:*- Name thesis:degree_name
- M.S.
- Level thesis:degree_level
- masters
- Discipline thesis:degree_discipline
- Aeronautical Engineering
- Department dc:contributor.department
- Aeronautical Engineering
- Grantor dc:publisher
- Virginia Polytechnic Institute
- Year dc:date.issued
- 1961
Author and committee
dc:creator, dc:contributor.*- Author dc:creator
-
- Mayo, Alton Parker
Rights
dc:rights- Statement dc:rights
-
- In Copyright
- Licence dc:rights.uri
- Language dc:language.iso
- en
Identifiers
dc:identifier.*- Handle dc:identifier.uri
- http://hdl.handle.net/10919/110993
- OAI identifier oai:identifier
- oai:vtechworks.lib.vt.edu:10919/110993