Nonlinear optimal feedback control for lunar module soft landing
In this paper, the optimal control problem to achieve lunar module soft landing with least fuel consumption is considered. The precise three dimensional dynamics is employed to describe the motion of the lunar module. By introducing two new state equations, a closed loop optimal control law is desig...
| Main Authors: | , , , |
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| Format: | Conference Paper |
| Published: |
2009
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| Online Access: | http://hdl.handle.net/20.500.11937/7420 |
| _version_ | 1848745362992398336 |
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| author | Zhou, Jingyang Zhou, D. Teo, Kok Lay Zhao, G. |
| author_facet | Zhou, Jingyang Zhou, D. Teo, Kok Lay Zhao, G. |
| author_sort | Zhou, Jingyang |
| building | Curtin Institutional Repository |
| collection | Online Access |
| description | In this paper, the optimal control problem to achieve lunar module soft landing with least fuel consumption is considered. The precise three dimensional dynamics is employed to describe the motion of the lunar module. By introducing two new state equations, a closed loop optimal control law is designed with a parameter matrix K to be determined which is the solution of a riccati like differential equation. We present a practical method to calculate the matrix K, such that it is avoided to solve the complex riccati like differential equation. Simulation results show the efficiency of the proposed method. © 2009 IEEE. |
| first_indexed | 2025-11-14T06:16:10Z |
| format | Conference Paper |
| id | curtin-20.500.11937-7420 |
| institution | Curtin University Malaysia |
| institution_category | Local University |
| last_indexed | 2025-11-14T06:16:10Z |
| publishDate | 2009 |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | curtin-20.500.11937-74202017-09-13T14:36:24Z Nonlinear optimal feedback control for lunar module soft landing Zhou, Jingyang Zhou, D. Teo, Kok Lay Zhao, G. In this paper, the optimal control problem to achieve lunar module soft landing with least fuel consumption is considered. The precise three dimensional dynamics is employed to describe the motion of the lunar module. By introducing two new state equations, a closed loop optimal control law is designed with a parameter matrix K to be determined which is the solution of a riccati like differential equation. We present a practical method to calculate the matrix K, such that it is avoided to solve the complex riccati like differential equation. Simulation results show the efficiency of the proposed method. © 2009 IEEE. 2009 Conference Paper http://hdl.handle.net/20.500.11937/7420 10.1109/ICAL.2009.5262838 restricted |
| spellingShingle | Zhou, Jingyang Zhou, D. Teo, Kok Lay Zhao, G. Nonlinear optimal feedback control for lunar module soft landing |
| title | Nonlinear optimal feedback control for lunar module soft landing |
| title_full | Nonlinear optimal feedback control for lunar module soft landing |
| title_fullStr | Nonlinear optimal feedback control for lunar module soft landing |
| title_full_unstemmed | Nonlinear optimal feedback control for lunar module soft landing |
| title_short | Nonlinear optimal feedback control for lunar module soft landing |
| title_sort | nonlinear optimal feedback control for lunar module soft landing |
| url | http://hdl.handle.net/20.500.11937/7420 |