Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics
The integrated 6-DOF orbit-attitude dynamical modeling and control have shown great importance in various missions, for example, formation flying and proximity operations. The integrated approach yields better performances than the separate one in terms of accuracy, efficiency, and agility. One chal...
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| Format: | Article |
| Language: | English |
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Wiley
2017-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2017/4034328 |
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| author | Ling Jiang Yue Wang Shijie Xu |
| author_facet | Ling Jiang Yue Wang Shijie Xu |
| author_sort | Ling Jiang |
| collection | DOAJ |
| description | The integrated 6-DOF orbit-attitude dynamical modeling and control have shown great importance in various missions, for example, formation flying and proximity operations. The integrated approach yields better performances than the separate one in terms of accuracy, efficiency, and agility. One challenge in the integrated approach is to find a unified representation for the 6-DOF motion with configuration space SE(3). Recently, exponential coordinates of SE(3) have been used in dynamics and control of the 6-DOF motion, however, only on the kinematical level. In this paper, we will improve the current method by adopting exponential coordinates on the dynamical level, by giving the relation between the second-order derivative of exponential coordinates and spacecraft’s accelerations. In this way, the 6-DOF motion in terms of exponential coordinates can be written as a second-order system with a quite compact form, to which a broader range of control theories, such as higher-order sliding modes, can be applied. For a demonstration purpose, a simple asymptotic tracking control law with almost global convergence is designed. Finally, the integrated modeling and control are applied to the body-fixed hovering over an asteroid and verified by a simulation, in which absolute motions of the spacecraft and asteroid are simulated separately. |
| format | Article |
| id | doaj-art-2ca178f472c44aeea78f33691410c898 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2017-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-2ca178f472c44aeea78f33691410c8982025-02-03T05:57:39ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742017-01-01201710.1155/2017/40343284034328Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric MechanicsLing Jiang0Yue Wang1Shijie Xu2School of Astronautics, Beihang University, Beijing 100191, ChinaSchool of Astronautics, Beihang University, Beijing 100191, ChinaSchool of Astronautics, Beihang University, Beijing 100191, ChinaThe integrated 6-DOF orbit-attitude dynamical modeling and control have shown great importance in various missions, for example, formation flying and proximity operations. The integrated approach yields better performances than the separate one in terms of accuracy, efficiency, and agility. One challenge in the integrated approach is to find a unified representation for the 6-DOF motion with configuration space SE(3). Recently, exponential coordinates of SE(3) have been used in dynamics and control of the 6-DOF motion, however, only on the kinematical level. In this paper, we will improve the current method by adopting exponential coordinates on the dynamical level, by giving the relation between the second-order derivative of exponential coordinates and spacecraft’s accelerations. In this way, the 6-DOF motion in terms of exponential coordinates can be written as a second-order system with a quite compact form, to which a broader range of control theories, such as higher-order sliding modes, can be applied. For a demonstration purpose, a simple asymptotic tracking control law with almost global convergence is designed. Finally, the integrated modeling and control are applied to the body-fixed hovering over an asteroid and verified by a simulation, in which absolute motions of the spacecraft and asteroid are simulated separately.http://dx.doi.org/10.1155/2017/4034328 |
| spellingShingle | Ling Jiang Yue Wang Shijie Xu Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics International Journal of Aerospace Engineering |
| title | Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics |
| title_full | Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics |
| title_fullStr | Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics |
| title_full_unstemmed | Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics |
| title_short | Integrated 6-DOF Orbit-Attitude Dynamical Modeling and Control Using Geometric Mechanics |
| title_sort | integrated 6 dof orbit attitude dynamical modeling and control using geometric mechanics |
| url | http://dx.doi.org/10.1155/2017/4034328 |
| work_keys_str_mv | AT lingjiang integrated6doforbitattitudedynamicalmodelingandcontrolusinggeometricmechanics AT yuewang integrated6doforbitattitudedynamicalmodelingandcontrolusinggeometricmechanics AT shijiexu integrated6doforbitattitudedynamicalmodelingandcontrolusinggeometricmechanics |