A perturbation solution of the main problem in artificial satellite theory
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Authors
Sagovac, Christopher Patrick
Subjects
Main problem
artificial satellite
restricted two body oblateness
orbital mechanics
perturbation
artificial satellite
restricted two body oblateness
orbital mechanics
perturbation
Advisors
Danielson, Donald A.
Date of Issue
1990-06
Date
June 1990
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
The main problem of artificial satellite theory is a restricted two body problem in which the Legendre Polynomial representation of the cylindrically symmetric potential contains only the first two terms. A generalized asymptotic expansion is used to obtain a first order approximation. The solution at the critical inclination is seen to be of a different type than at other inclinations. The solution is finite for all eccentricities and inclinations when suitably restricted in time.
Type
Thesis
Description
Series/Report No
Department
Applied Mathematics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
vii, 27 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.