TY - JOUR
T1 - Dynamics and control during spinning deployment for hub-and-spoke configured multi-tethered satellite formation
AU - Su, Fei
AU - Zhai, Guang
AU - Zhang, Jingrui
AU - Zhang, Yao
N1 - Publisher Copyright:
© 2016, Press of Chinese Journal of Aeronautics. All right reserved.
PY - 2016/9/25
Y1 - 2016/9/25
N2 - The deployment strategies for “hub-and-spoke” configured tethered satellite formation are investigated in circular orbit. Firstly, the deployment dynamics model is established based on Lagrangian method under some reasonable assumptions. The dynamical coupling between the attitude of central body and the tether length is analyzed, and then the deployment strategies for the cases with and without gravity gradient compensation are developed. By planning the deployment rate and angular velocity of central body, the successful deployments are achieved. Finally, some mathematical simulations for the proposed strategies are implemented. The simulation results indicate that using the proposed deployment strategies, the configuration can be maintained effectively and steadily.
AB - The deployment strategies for “hub-and-spoke” configured tethered satellite formation are investigated in circular orbit. Firstly, the deployment dynamics model is established based on Lagrangian method under some reasonable assumptions. The dynamical coupling between the attitude of central body and the tether length is analyzed, and then the deployment strategies for the cases with and without gravity gradient compensation are developed. By planning the deployment rate and angular velocity of central body, the successful deployments are achieved. Finally, some mathematical simulations for the proposed strategies are implemented. The simulation results indicate that using the proposed deployment strategies, the configuration can be maintained effectively and steadily.
KW - Attitude of central body
KW - Configuration stability
KW - Gravity gradient force
KW - Spinning deployment
KW - Tethered satellite formation
UR - http://www.scopus.com/inward/record.url?scp=84988504114&partnerID=8YFLogxK
U2 - 10.7527/S1000-6893.2016.0021
DO - 10.7527/S1000-6893.2016.0021
M3 - Article
AN - SCOPUS:84988504114
SN - 1000-6893
VL - 37
SP - 2809
EP - 2819
JO - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
JF - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
IS - 9
ER -