Modifying the atlas of low lunar orbits using inert tethers |
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| Institution: | 1. Real Observatorio de la Armada, ES-11110 San Fernando, Spain;2. Space Dynamics Group (UPM), ETSI Aeronáuticos, ES-28040 Madrid, Spain;1. National Time Service Center, Chinese Academy of Sciences, Shu Yuan Road, 710600 Xi’an, China;2. Key Laboratory of Precision Navigation Positioning and Timing Technology, Chinese Academy of Sciences, Shu Yuan Road, 710600 Xi’an, China;3. University of Chinese Academy of Sciences, Yu Quan Road, 100049 Beijing, China;1. Department of Physics, Tai Solarin University of Education, Ijagun, Ijebu-Ode, Nigeria;2. Cardiff School of Education & Social Policy, Cardiff Metropolitan University, Cyncoed Campus, Cardiff, UK;3. Federal College of Forestry, P.M.B. 5087, Jericho, Ibadan, Oyo State, Nigeria;4. Department of Physics, Olabisi Onabanjo University, Ago-Iwoye, Ogun State, Nigeria;1. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China;2. Beijing Institute of Tracking and Telecommunication Technology, Beijing 100094, China;3. China Satellite Maritime Tracking and Control Department, Jiangyin 214431, China |
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| Abstract: | For long enough tethers, the coupling of the attitude and orbital dynamics may show non-negligible effects in the orbital motion of a tethered satellite about a central body. In the case of fast rotating tethers the attitude remains constant, on average, up to second order effects. Besides, for a tether rotating in a plane parallel to the equatorial plane of the central body, the attitude–orbit coupling effect is formally equal to the perturbation of the Keplerian motion produced by the oblateness of the central body and, therefore, may have a stabilizing effect in the orbital dynamics. In the case of a tethered satellite in a low lunar orbit, it is demonstrated that feasible tether lengths can help in modifying the actual map of lunar frozen orbits. |
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