| 双星定姿技术试验研究 |
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| 引用本文： | 郑伟,吴杰,胡小平,赵健康.双星定姿技术试验研究[J].空间科学学报,2000,20(3):257-261. |
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| 作者姓名： | 郑伟 吴杰 胡小平 赵健康 |
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| 作者单位： | 国防科学技术大学航天技术系, 长沙 410073 |
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| 摘 要： | 本文深入探讨了双星定姿方法,仅利用2颗GPS卫星进行了实际的双星定姿试验.文中综合应用长短基线法和序列优化法求解整周模糊度.试验结果表明,当基线长约1m时,该方法定姿成功率达90%以上,定姿均方差优于0.5°
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| 关 键 词： | 姿态传感器 卫星导航 GPS |
| 收稿时间： | 1999-11-08 |
| 修稿时间： | 1999年11月8日 |
AN EXPERIMENT RESEARCH ON TECHNIQUE OF ATTITUDE DETERMINATION WITH DOUBLE SATELLITES |
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| ZHENG Wei,WU Jie,HUXiaoping,Zhao Jiankang.AN EXPERIMENT RESEARCH ON TECHNIQUE OF ATTITUDE DETERMINATION WITH DOUBLE SATELLITES[J].Chinese Journal of Space Science,2000,20(3):257-261. |
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| Authors: | ZHENG Wei WU Jie HUXiaoping Zhao Jiankang |
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| Institution: | Department of Aerospace Technology, National University of Defense Technologe, Changsha 410073 |
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| Abstract: | The method of attitude determination with doublesatellites is discussed in detail in the paper, and the actualexperiment of attitude determination with only two GPS satellites isconducted. The long-short baseline method and sequence optimizationmethod are synthetically used to estimate carrier phase ambiguity. Theexperiment results indicate that the success rate of attitudedetermination exceeds 90% and the mean square error of attitude can beless than 0.5, when baseline length be 1 m around. |
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| Keywords: | Attitude sensor Satellite navigation Global Positioning System |
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