Approximate State Transition Matrix and Secular Orbit Model
Author
Source
International Journal of Aerospace Engineering
Issue
Vol. 2015, Issue 2015 (31 Dec. 2015), pp.1-6, 6 p.
Publisher
Hindawi Publishing Corporation
Publication Date
2015-03-10
Country of Publication
Egypt
No. of Pages
6
Abstract EN
The state transition matrix (STM) is a part of the onboard orbit determination system.
It is used to control the satellite’s orbital motion to a predefined reference orbit.
Firstly in this paper a simple orbit model that captures the secular behavior of the orbital motion in the presence of all perturbation forces is derived.
Next, an approximate STM to match the secular effects in the orbit due to oblate earth effect and later in the presence of all perturbation forces is derived.
Numerical experiments are provided for illustration.
American Psychological Association (APA)
Ramachandran, M. P.. 2015. Approximate State Transition Matrix and Secular Orbit Model. International Journal of Aerospace Engineering،Vol. 2015, no. 2015, pp.1-6.
https://search.emarefa.net/detail/BIM-1064520
Modern Language Association (MLA)
Ramachandran, M. P.. Approximate State Transition Matrix and Secular Orbit Model. International Journal of Aerospace Engineering No. 2015 (2015), pp.1-6.
https://search.emarefa.net/detail/BIM-1064520
American Medical Association (AMA)
Ramachandran, M. P.. Approximate State Transition Matrix and Secular Orbit Model. International Journal of Aerospace Engineering. 2015. Vol. 2015, no. 2015, pp.1-6.
https://search.emarefa.net/detail/BIM-1064520
Data Type
Journal Articles
Language
English
Notes
Includes bibliographical references
Record ID
BIM-1064520