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Virginia Tech
An arbitrarily shaped satellite in the restricted problem of three bodies
Abstract
dc:description.abstractIt is proposed to place a space station in a short period orbit about the L₄ triangular point in the earth moon system for the purpose of communication and possibly astronomical observations. Within limits of a linear analysis, an exhaustive and general approach to the dynamical problem is presented. The equations of motion for a finite sized body of arbitrary shape and internal mass distribution are derived. The phenomenon of resonance and stability are discussed. Stability boundaries for such a space station are established. Initial conditions and pointing errors are analyzed.
Degree
thesis:*- Name thesis:degree_name
- Master of Science
- Level thesis:degree_level
- masters
- Discipline thesis:degree_discipline
- Aerospace Engineering
- Department dc:contributor.department
- Aerospace Engineering
- Grantor dc:publisher
- Virginia Tech
- Year dc:date.issued
- 1974
Author and committee
dc:creator, dc:contributor.*- Author dc:creator
-
- Saxena, Ashok Kumar
Rights
dc:rights- Statement dc:rights
-
- In Copyright
- Licence dc:rights.uri
Identifiers
dc:identifier.*- Dc Identifier Other
- etd-06122010-020059
- OAI identifier oai:identifier
- oai:vtechworks.lib.vt.edu:10919/43220