Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element
Orbital perturbations caused by the space environment will induce deviations compared with the prescribed motion trajectory or dynamic performance of the tethered satellite system (TSS). To comprehensively investigate the effects of the orbital perturbations on the TSS, a precise variable-length ele...
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| Format: | Article |
| Language: | English |
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IEEE
2021-01-01
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| Series: | IEEE Access |
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| Online Access: | https://ieeexplore.ieee.org/document/9344599/ |
| _version_ | 1828908227260055552 |
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| author | Zhengfeng Bai Xin Jiang |
| author_facet | Zhengfeng Bai Xin Jiang |
| author_sort | Zhengfeng Bai |
| collection | DOAJ |
| description | Orbital perturbations caused by the space environment will induce deviations compared with the prescribed motion trajectory or dynamic performance of the tethered satellite system (TSS). To comprehensively investigate the effects of the orbital perturbations on the TSS, a precise variable-length element that can describe the large deformation and flexibility of the tether is adopted in this paper to predict the deployment dynamics considering orbital perturbations, including atmospheric drag, solar pressure, lunisolar gravitation, and J<sub>2</sub> perturbation. To this end, the variable-length element using arbitrary LagrangianEulerian (ALE) description in the frame work of absolute nodal coordinate formulation (ANCF) is developed firstly. Subsequently, the dynamic governing equations for the TSS are established in the context of ANCF with the employment of ANCF reference node (ANCF-RN). Effects of orbital perturbations including atmospheric drag, solar pressure, lunisolar gravity and J<sub>2</sub> perturbation on the dynamics of an optimal deployment are analyzed numerically. It is shown that the orbital perturbations except the J<sub>2</sub> perturbation will induce the out-of-plane motion of the TSS. Additionally, the tether tension is less affected by the orbital perturbations. By contrast, the lunisolar gravitation will induce a deviation on the motion path of satellite, which should be considered in the design phase of the TSS. |
| first_indexed | 2024-12-13T18:07:43Z |
| format | Article |
| id | doaj.art-99a3fae43db349e09bf3b7c2ecf8f9f5 |
| institution | Directory Open Access Journal |
| issn | 2169-3536 |
| language | English |
| last_indexed | 2024-12-13T18:07:43Z |
| publishDate | 2021-01-01 |
| publisher | IEEE |
| record_format | Article |
| series | IEEE Access |
| spelling | doaj.art-99a3fae43db349e09bf3b7c2ecf8f9f52022-12-21T23:36:02ZengIEEEIEEE Access2169-35362021-01-019223992240710.1109/ACCESS.2021.30564589344599Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length ElementZhengfeng Bai0https://orcid.org/0000-0001-5694-8317Xin Jiang1Department of Mechanical Engineering, Harbin Institute of Technology, Weihai, ChinaDepartment of Astronautic Engineering, Harbin Institute of Technology, Harbin, ChinaOrbital perturbations caused by the space environment will induce deviations compared with the prescribed motion trajectory or dynamic performance of the tethered satellite system (TSS). To comprehensively investigate the effects of the orbital perturbations on the TSS, a precise variable-length element that can describe the large deformation and flexibility of the tether is adopted in this paper to predict the deployment dynamics considering orbital perturbations, including atmospheric drag, solar pressure, lunisolar gravitation, and J<sub>2</sub> perturbation. To this end, the variable-length element using arbitrary LagrangianEulerian (ALE) description in the frame work of absolute nodal coordinate formulation (ANCF) is developed firstly. Subsequently, the dynamic governing equations for the TSS are established in the context of ANCF with the employment of ANCF reference node (ANCF-RN). Effects of orbital perturbations including atmospheric drag, solar pressure, lunisolar gravity and J<sub>2</sub> perturbation on the dynamics of an optimal deployment are analyzed numerically. It is shown that the orbital perturbations except the J<sub>2</sub> perturbation will induce the out-of-plane motion of the TSS. Additionally, the tether tension is less affected by the orbital perturbations. By contrast, the lunisolar gravitation will induce a deviation on the motion path of satellite, which should be considered in the design phase of the TSS.https://ieeexplore.ieee.org/document/9344599/Tethered satellite systemorbital perturbationsANCF-ALEGauss pseudo-spectral method |
| spellingShingle | Zhengfeng Bai Xin Jiang Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element IEEE Access Tethered satellite system orbital perturbations ANCF-ALE Gauss pseudo-spectral method |
| title | Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element |
| title_full | Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element |
| title_fullStr | Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element |
| title_full_unstemmed | Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element |
| title_short | Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element |
| title_sort | effects of orbital perturbations on deployment dynamics of tethered satellite system using variable length element |
| topic | Tethered satellite system orbital perturbations ANCF-ALE Gauss pseudo-spectral method |
| url | https://ieeexplore.ieee.org/document/9344599/ |
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