Approximate State Transition Matrix and Secular Orbit Model

Author

Ramachandran, M. P.

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