Enviar artigo por via de e-mail Influence of initial conditions during separation of a descent capsule from the circumlunar tethered system on the possibility of its landing on the surface of the moon
- Autores: Ledkova T.A.1
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Afiliações:
- Samara National Research University
- Edição: Volume 89, Nº 3 (2025)
- Páginas: 406-417
- Seção: Articles
- URL: https://cardiosomatics.ru/0032-8235/article/view/688544
- DOI: https://doi.org/10.31857/S0032823525030048
- EDN: https://elibrary.ru/JKEKWV
- ID: 688544
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Resumo
The motion of the lunar tether system, which includes the space station equipment and small space elements attached to it by tethers, is considered. The Lagrange equations of the second kind were used to construct a mathematical model of the motion of the circumlunar tether system. The paper studies the influence of the initial conditions of the descent capsule separation from the tether connecting it to the lunar space station on the area of its landing on the lunar surface.
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Sobre autores
T. Ledkova
Samara National Research University
Autor responsável pela correspondência
Email: ta_ledkova@bk.ru
Rússia, Samara
Bibliografia
- Beletsky V.V., Levin E.M. Dynamics of Space Tether Systems. Moscow: Nauka, 1990. 329 p. (in Russian)
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- Zabolotnov Yu.M. Control of deployment of an orbital tether system into a vertical position with a small load // JAMM, 2015, vol. 79, no. 1, pp. 37–47. (in Russian)
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- Akim E.L., Bazhinov I.K., Pavlov V.P., Pochukaev V.N. The Gravitational Field of the Moon and the Motion of Its Artificial Satellites. Moscow: Mashinostroenie, 1984. (in Russian)
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- Egorov V.A., Gusev L.I. Dynamics of Flights between the Earth and the Moon. Moscow: Nauka, 1980. 544 p. (in Russian)
- Ledkova T.A., Zabolotnov Yu.M. Deployment and stabilization of the space tether system in lunar orbit // Vestn. of Samara Univ. Aerospace Technol., Technol.&Mech. Engng., 2021, vol. 20, no. 2, pp. 63–73. (in Russian)
- Haws T.D., Zimmerman J.S., Fuller M.E. SLS, the Gateway, and a Lunar outpost in the early 2030s // IEEE Aerospace Conf. Proc., 2019.
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- Markeev A.P. Theoretical Mechanics. Moscow;Izhevsk: R&C Dyn., 2007. (in Russian)
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Fig. 1. Mechanical system
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Fig. 2. Coordinate systems
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Fig. 3. Changing the length of the cables during deployment of the KTS
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Fig. 4. Deployment of the cable system
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Rice. 5. Orbit of the descent small spacecraft
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Fig. 6. Determination of the orbital radius of the landing spacecraft
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Fig. 7. Deployment of cables and the angle of deviation of the station’s symmetry axis from the local vertical at la max = lb max = 42 km
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