Show/Hide Menu
Hide/Show Apps
anonymousUser
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Açık Bilim Politikası
Açık Bilim Politikası
Frequently Asked Questions
Frequently Asked Questions
Browse
Browse
By Issue Date
By Issue Date
Authors
Authors
Titles
Titles
Subjects
Subjects
Communities & Collections
Communities & Collections
ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT
Date
2017-02-09
Author
Atas, Omer
Tekinalp, Ozan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
0
views
0
downloads
Propelling a spacecraft by using solar radiation pressure is examined in the context of orbital maneuvers. A locally optimal steering law to progressively change number of selected orbital elements together is addressed. An Earth centered cubesat satellite with solar sail is used as an example. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for Earth orbiting satellites. The satellite attitude control is realized using to-go quaternion feedback control. And the effectiveness of the approach to progressively changing the orbital parameters is demonstrated.
URI
https://hdl.handle.net/11511/53547
Collections
Department of Aerospace Engineering, Conference / Seminar