首页 | 本学科首页   官方微博 | 高级检索  
     检索      


Satellite pitch and roll attitude maneuvers through very short tethers
Institution:1. Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, India;1. Harbin Institute of Technology, Harbin 150001, People''s Republic of China;2. Yonsei University Observatory, Yonsei University, Seoul 120-749, Republic of Korea;3. Astrodynamics and Control Laboratory, Department of Astronomy & Yonsei University Observatory, Yonsei University, Seoul 120-749, Republic of Korea;1. Department of Orthopaedics and Traumatology, Gazi University Faculty of Medicine, Ankara, Turkey;2. Sungurlu State Hospital, Turkey;1. Dorodnicyn Computing Center of the Russian Academy of Sciences & Higher School of Economics, Russian Federation;2. Moscow State Technical University of Radio Engineering, Electronics, and Automation, Russian Federation;1. Saint Petersburg State University, 7-9 Universitetskaya nab., Saint Petersburg 199034, Russia;2. ITMO University, 49 Kronverksky Ave., Saint Petersburg 197101, Russia;3. Saint Petersburg Mining University, 2, 21st Line, Saint Petersburg 199106, Russia;1. Department of Mechanical Engineering, Sharif University of Technology, P.O. Box 11155-9567, Tehran, Iran;2. Department of Mechanical Engineering, Shiraz University, Shiraz, Iran
Abstract:Explored here is the feasibility of achieving satellite pitch and roll attitude maneuvers through tethers. The proposed tethered satellite system (TSS) comprises of four identical tethers connecting the auxiliary mass to the satellite at its four distinct off-centered and equiangularly spaced points. The open-loop tether length control laws have been developed in order to achieve arbitrary pitch and roll attitude slewing maneuvers. Numerical simulation of the nonlinear governing equations of motion for these tether length variations establishes the feasibility of executing fixed as well as chase-slewing maneuvers. Nearly passive nature of the proposed mechanism using very short tethers along with small auxiliary mass needed makes the concept particularly attractive for future space missions.
Keywords:
本文献已被 ScienceDirect 等数据库收录!
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号