Abstract
dc:description.abstractA universal time of flight equation for any orbit is developed as a function of the initial and final radius, the change in true anomaly and the initial flight path angle. Lambert's theorem, a new corollary to this theorem, a trigonometric variable substitution and a continuing fraction expression are used in this development. The resulting equation is not explicitly dependent upon eccentricity and is determinate for -2n < (change in true anomaly) < 2n. A method to make the continuing fraction converge rapidly is evaluated using a top down algorithm. Finally, the accuracy of the universal time of flight equation is examined for a representative set of orbits including near parabolic and near rectilinear orbits.
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
- 1988
Author and committee
dc:creator, dc:contributor.*- Author dc:creator
-
- Halter, Ronald Vaughn
- Chair dc:contributor.committeechair
-
- Lutze, Frederick H. Jr.
- Committee members dc:contributor.committeemember
-
- Cliff, Eugene M.
- Stalford, Harold L.
Rights
dc:rights- Statement dc:rights
-
- In Copyright
- Licence dc:rights.uri
Identifiers
dc:identifier.*- Dc Identifier Other
- etd-06222010-020301
- OAI identifier oai:identifier
- oai:vtechworks.lib.vt.edu:10919/43406