| Zenith Pass Problem of Inter-satellite Linkage Antenna Based on Program Guidance Method |
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| 作者姓名： | Zhai Kun Yang Di |
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| 作者单位： | School of Aeronautics, Harbin Institute of Technology, Harbin 150001, China |
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| 基金项目： | Foundation item： ＇Tenth Five＇ Pre-research Item |
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| 摘 要： | While adopting an elevation-over-azimuth architecture by an inter-satellite linkage antenna of a user satellite, a zenith pass problem always occurs when the antenna is tracing the tracking and data relay satellite （TDRS）. This paper deals with this problem by way of, firstly, introducing movement laws of the inter-satellite linkage to predict the movement of the user satellite antenna followed by analyzing the potential pass moment and the actual one of the zenith pass in detail. A number of specific orbit altitudes for the user satellite that can remove the blindness zone are obtained. Finally, on the base of the predicted results from the movement laws of the inter-satellite linkage, the zenith pass tracing strategies for the user satellite antenna are designed under the program guidance using a trajectory preprocessor. Simulations have confirmed the reasonability and feasibility of the strategies in dealing with the zenith pass problem.
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| 关 键 词： | 卫星 天线 跟踪系统 程序控制 |
| 收稿时间： | 2007-05-29 |
| 修稿时间： | 2007-11-30 |
Zenith Pass Problem of Inter-satellite Linkage Antenna Based on Program Guidance Method |
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| Zhai Kun Yang Di.Zenith Pass Problem of Inter-satellite Linkage Antenna Based on Program Guidance Method[J].Chinese Journal of Aeronautics,2008,21(1):53-60. |
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| Authors: | Zhai Kun Yang Di |
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| Institution: | School of Aeronautics, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: | While adopting an elevation-over-azimuth architecture by an inter-satellite linkage antenna of a user satellite, a zenith pass problem always occurs when the antenna is tracing the tracking and data relay satellite (TDRS). This paper deals with this problem by way of,firstly, introducing movement laws of the inter-satellite linkage to predict the movement of the user satellite antenna followed by analyzing the potential pass moment and the actual one of the zenith pass in detail. A number of specific orbit altitudes for the user satellite that can remove the blindness zone are obtained. Finally, on the base of the predicted results from the movement laws of the inter-satellite linkage, the zenith pass tracing strategies for the user satellite antenna are designed under the program guidance using a trajectory preprocessor. Simulations have confirmed the reasonability and feasibility of the strategies in dealing with the zenith pass problem. |
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| Keywords: | satellite antenna tracking and data relay satellite zenith pass program guidance |
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