Beschreibung
The purpose of this book is to investigate the effect of a varying moment on the rotation angle of a large tethered satellite that is orbiting a planet. Two different types of orbits were investigated: a simple circular orbit and an elliptical orbit. Cases with zero and non-zero initial angular rotation velocity were investigated as well. This investigation will assist satellite docking missions. The large rigid tethered satellite is a futuristic concept, and this investigation is meant to assist possible docking missions to the satellite. To simplify the problem, the rotation is constrained to the orbital plane.
Autorenporträt
In December 2016, I graduated from Purdue University in USA for Aeronautical and Astronautical Engineering. I am highly passionate about flight and have continually pursued knowledge and experience in this field. I currently work for a large aerospace company in USA as a Systems Engineer, and I hold a private pilot license.
Herstellerkennzeichnung:
OmniScriptum SRL
Str. Armeneasca 28/1, office 1
2012 Chisinau
MD
E-Mail: info@omniscriptum.com
