Identification and orbit determination of a tethered satellite system |
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| Affiliation: | 1. Department of Aeronautics and Astronautics, The University of Tokyo, Bunkyo-ku, Tokyo, 113-8656, Japan;2. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa, 252-5210, Japan;1. Research Center for Intelligent Robotics, School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China;2. National Key Laboratory of Aerospace Flight Dynamics, Northwestern Polytechnical University, Xi’an 710072, China;1. Udaipur Solar Observatory/Physical Research Laboratory, Udaipur 313001, India;2. Departmentof Electronics and Communication Engineering, Tripura University, Agartala 799022, India;3. Department of Physics, Institute of Science, Banaras Hindu University, Varanasi 221005, India;1. School of Mechanical Engineering, Pusan National University, 609-735 Busan, Republic of Korea;2. Department of Petroleum Engineering, Faculty of Engineering, Sirte University, Sirte, Libya;3. Oil and Gas Engineering Centre, Cranfield University, Bedfordshire MK43 0AL, United Kingdom;1. Shaanxi Key Laboratory of Space Solar Power Station System, Xidian University, Xi''an 710071, China;2. Qian Xuesen Laboratory of Space Technology, China Academy of Space Technology, Beijing 100094, China;3. Key Laboratory of Electronic Equipment Structure Design of Ministry of Education, Xidian University, Xi''an 710071, China |
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| Abstract: | Orbital motion of a tethered satellite system, composed of two satellites and an inextensible tether, is considered by using a perturbed two-body model. This approach is adopted so that the determination of the orbit of one of the satellites can be attempted without using observations of the motion of the other satellite in the system. The identification of the tethered condition of the system using observations of only one of the satellites in the tethered satellite system is considered. The characteristics of the `tether perturbed' motion of the observed satellite are investigated. Estimation of the state of the system using near perfect data is also illustrated. Observations of one satellite provide the entire state of the system and a parameter involving the ratio of the masses of satellites and the tether length. |
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