Graphical Abstract
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The deployment of a long tether to operate as a partial space elevator, starting from a nucleus in geostationary orbit, is studied. Uncontrolled deployment is an inherently unstable process because the center of orbit gradually decreases from the geostationary altitude when deployment progresses. It is also observed that the elasticity of the tether has an important effect on deployment stability. It is shown that the application of a transverse force on the main spacecraft, determined by using linear state feedback and appropriate gains, can stabilize the deployment. An LQR controller is developed. Simulations of the dynamics of the system are carried out using this controller for various parametric values of tether elasticity, deployment rates, etc., to evaluate the efficacy of the controller.
Okino, T., Yamagiwa, Y., Arita, S., Ishikawa, Y., Otsuka, K. Three-dimensional analysis of a counterweight type space elevator. Acta Astronautica, 2021, 185: 132–139.
Woo, P., Misra, A. K. Dynamics of a partial space elevator with multiple climbers. Acta Astronautica, 2010, 67(7–8): 753–763.
Misra, A. K. Dynamics and control of tethered satellite systems. Acta Astronautica, 2008, 63(11–12): 1169–1177.
Wang, C. Q., Zakrzhevskyi, O. E. Deployment of a space tether in a centrifugal force field with alignment to the local vertical. Technical Mechanics, 2024, 2024(1): 26–39.
Takeichi, N. Geostationary station keeping control of a space elevator during initial cable deployment. Acta Astronautica, 2012, 70: 85–94.
Lorenzini, E. C., Bettanini, C., Colombatti, G., Valmorbida, A. Energy and orbital stability in a partially-deployed Earth space elevator. Acta Astronautica, 2020, 177: 828–833.
Shi, G. F., Zhu, Z. H., Li, G. Q. Stable cargo transportation of partial space elevator with multiple actuators. Advances in Space Research, 2021, 68(7): 2999–3011.
Shi, G. F., Zhu, Z. H. Prescribed performance based dual-loop control strategy for configuration keeping of partial space elevator in cargo transportation. Acta Astronautica, 2021, 189: 241–249.
Shi, G. F., Zhu, Z. H. Libration-free cargo transfer of floating space elevator. Nonlinear Dynamics, 2022, 110(3): 2263–2281.
Cohen, S. S., Misra, A. K. Elastic oscillations of the space elevator ribbon. Journal of Guidance, Control, and Dynamics, 2007, 30(6): 1711–1717.
Keshmiri, M., Misra, A. K. Near optimal deployment of a space elevator system. Advances in the Astronautical Sciences, 2013, 146: 243–249.