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UDC 629.5
Technical mechanics, 2024, 1, 26 - 39
DEPLOYMENT OF A SPACE TETHER IN A CENTRIFUGAL FORCE FIELD WITH ALIGNMENT TO THE LOCAL VERTICAL
DOI:
https://doi.org/10.15407/itm2024.01.026
Wang Changqing, Zakrzhevskyi O. E.
Wang Changqing
Northwestern Polytechnical University
Zakrzhevskyi O. E.
Space Research Institute of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine
This study is concerned with a small orbital tether of two bodies to be deployed from a spacecraft so that upon
completion of the deployment it turns out to be aligned along the local vertical. The bodies of the tether
have equal masses, and the thread connecting the bodies is supposed to be massless. The objective of the study
is to build a program law of tether length control taking into account the variation of the angular momentum
of the tether under the action of the gravitational torque from the central Newtonian field of forces. The
deployment mode of the space tether in a centrifugal force field with its alignment at the conclusion of the
deployment along the local vertical is studied. To produce centrifugal forces, the tether is pre-spinned about
the orbit binormal. The study consists of two steps. The first step involves the construction of a tether
length control law that would provide the planned deployment. At this step, use is made of the tether motion
equations written in spherical coordinates for the special case of the tether motion in the orbital plane.
A numerical simulation of the tether deployment dynamics is carried out at the second step using the
constructed program law of tether length control. Hill-Clohessy-Wiltshire’s equations are used as a
mathematical model of the tether. They describe the spatial motion of the tether bodies. These equations do
not contain the tether length as a variable in explicit form. Therefore, these equations are modified. The
tether tension force appearing in these equations is expressed in terms of the program law of tether length
change and its two first time derivatives. The novelty of the study consists in the construction of a program
control law that allows the tether to be deployed along the local vertical in a single stage. The study used
methods of analytical mechanics, numerical methods, and methods developed by the authors. The obtained
results make it possible to find the ranges of values of the deployment system parameters allowing a
deployment of this type. The errors of the numerical simulation are estimated. The practical significance
of the obtained results consists in the possibility of deploying small tethers in orbit with their alignment
at the conclusion of the deployment along the local vertical in a single stage with controlling the tether
length without the need for further dumping of libratory oscillations.
Control, space tether; deployment, local vertical, one stage
1. Alpatov A. P., Wang Changqing, Zakrzhevskii A. E. Feed-forward control of total retrieval of the space tether from vertical position. Space Sci. & Technol. 2021. V 27. No. 5. Pp. 71-85.
https://doi.org/10.15407/knit2021.05.071
2. Alpatov A. P., Zakrzhevskii A. E. Deployment of a tether of three bodies in the field of centrifugal forces. Teh. Meh. 2002. No. 2, Pp. 3-12.
3. Alpatov A. P., Zakrzhevskii A. E. Passive deployment of a tether between two bodies in orbit. International Applied Mechanics. 1999. V.35. No. 10. Pp. 1053-1058.
https://doi.org/10.1007/BF02682318
4. Barkow B., Steindl A., Troger H., Wiedermann G. Various methods of controlling the deployment of a tethered satellite. Journal of Vibration and Control. 2003. No. 9. Pp. 187-208.
https://doi.org/10.1177/1077546303009001747
5. Bekey I. Tethers open new space options. Astronautics and Aeronautics. 1983. V. 21. No. 4. Pp. 32- 40.
6. Bekey I., Penzo P. A. Tether propulsion. Aerospace America. 1986. V. 24. No. 7. Pp. 40-43.
7. Beletsky V. V. Motion of an artificial satellite about its center of mass. Israel Program for Scientific Translations. Jerusalem, 1966.
8. Beletsky V. V., Levin E. M. Dynamics of space tether systems. Adv. Astronaut. Sci. 1993. Pp. 1-83.
9. Cantafio L. J., Chobotov V. A., Wolfe M. G. Photovoltaic gravitationaly stabilized, solid-state satellite solar power station. J. of Energy. 1977. V.1. No. 6. Pp. 352-363.
https://doi.org/10.2514/3.62346
10. Hoyt R. P., Uphoff Ch. Cislunar Tether Transport System. Journal of Spacecraft and Rockets. 2000. V. 37. No. 2. Pp. 177-186.
https://doi.org/10.2514/2.3564
11. Levin E. M. About deployment of the extended tether in the orbit. Space Researches. 1983. V. 71. No.1. Pp. 678-688.
12. Levin E. M. Dynamic Analysis of Space Tether Missions Univelt. 2007. 454 p.
13. Lorenzini E. C. et al. Acceleration levels on board the space station and a tethered elevator for micro- and variable-gravity applications. In: Proc. 2-nd Int. Conf. on Space Tethers for Science in the Space Station Era. 1987. Venice. Pp. 4-8.
14. Lur'e A. Analytical Mechanics. Springer, 2002. 864 pp.
15. Modi V., Misra A. Deployment dynamics of tethered satellite systems. AIAA Paper. 1978. No. 1398. 10 pp.
https://doi.org/10.2514/6.1978-1398
16. Napolitano L., Bevilacqua F. Tethered constellations, their utilization as microgravity platforms and relevant features. 1984. Lausanne, Switzerland. IAF-84-439.
17. Padgett, D. A., Mazzoleni, A. P. Analysis and design for nospin tethered satellite retrieval. J. Guidance Control and Dyn. 2007. V. 30. No. 5. Pp. 1516-1519.
https://doi.org/10.2514/1.25390
18. Pearson J. Anchored lunar satellites for cislunar transportation and communication. J. of the Astronautical Sciences. 1979. V. 17. No. 1. Pp. 39-62.
19. Rupp C. C., Laue J. H. Shuttle/tethered satellite system. Journal of Astronautical Sciences. 1978. V. 24. No .1. Pp. 1-17.
20. Swet C. J. Method for deployment and stabilizing orbiting structures. U.S. Patent Office N 3532298, Oct. 6, 1970, Int. Cl. B 64 G 1/00, U.S. Cl. 244-1.
21.Wang Changqing, Wang Panbing, Li Aijun. Deployment of tethered satellites in low-eccentricity orbits using adaptive sliding mode control. Journal of Aerospace Engineering. 2017. V. 30. No. 6. Pp. 1-10.
https://doi.org/10.1061/(ASCE)AS.1943-5525.0000793
22. Wang Changqing, Zabolotnov Y. M. Control of the deployment of a long-distance orbital tether system. Vestnik of Samara University. Aerospace and Mechanical Engineering. 2017. V. 16. No. 2. Pp. 7-17.
https://doi.org/10.18287/2541-7533-2017-16-2-7-17
23. Zakrzhevskii A. E. Method of deployment of a space tethered system aligned to the local vertical. J. of Astronaut Sci. 2016. V. 63. Pp. 221-236.
https://doi.org/10.1007/s40295-016-0087-z
Copyright (©) 2024 Wang Changqing, Zakrzhevskyi O. E.
Copyright © 2014-2024 Technical mechanics
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