| Improved uncertainty propagation method of dynamic model for Mars entry spacecraft |
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| 作者姓名： | FU Hui-min XIAO Qiang WU Yun-zhang |
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| 作者单位： | Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| 基金项目： | National Basic Research Program of China (2012CB720000) |
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| 摘 要： | In order to research the uncertainty propagation laws of Mars entry dynamic equations for the Mars entry phase,an improved method was presented for analyzing the effect of the initial state uncertainties and uncertainty factor on the system state in the state trajectories.When applying the method to the entry phase of one of the NASA Mars exploration missions,the simulation results agreed well with the Monte Carlo method,especially the flight path angle simulation at least reaching 92%.It is found that the improved method can not only predict the uncertainty propagation laws with high accuracy of at least 92%in flight path angle simulation and large application scope from-0.1degree to 0.1degree,compared with local linearization method,but also save several hours relative to Monte Carlo method.
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| 关 键 词： | uncertainty propagation laws Mars entry dynamic equations improved method high accuracy |
| 收稿时间： | 2/1/2013 12:00:00 AM |
Improved uncertainty propagation method of dynamic model for Mars entry spacecraft |
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| FU Hui-min,XIAO Qiang,WU Yun-zhang.Improved uncertainty propagation method of dynamic model for Mars entry spacecraft[J].Journal of Aerospace Power,2014,29(5):1223-1233. |
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| Authors: | FU Hui-min XIAO Qiang and WU Yun-zhang |
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| Institution: | Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | In order to research the uncertainty propagation laws of Mars entry dynamic equations for the Mars entry phase, an improved method was presented for analyzing the effect of the initial state uncertainties and uncertainty factor on the system state in the state trajectories. When applying the method to the entry phase of one of the NASA Mars exploration missions, the simulation results agreed well with the Monte Carlo method, especially the flight path angle simulation at least reaching 92%. It is found that the improved method can not only predict the uncertainty propagation laws with high accuracy of at least 92% in flight path angle simulation and large application scope from -0.1 degree to 0.1 degree, compared with local linearization method, but also save several hours relative to Monte Carlo method. |
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| Keywords: | uncertainty propagation laws Mars entry dynamic equations improved method high accuracy |
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