Orbit improvement for Chang'E-5T lunar returning probe with GNSS technique
文献类型：期刊论文
| 作者 | Fan, Min1,2,3; Hu, XiaoGong1 ; Dong, Guangliang3; Huang, Yong1; Cao, Jianfeng4; Tang, ChengPan1; Li, Peijia1; Chang, Shengqi1; Yu, Yang1
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| 刊名 | ADVANCES IN SPACE RESEARCH
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| 出版日期 | 2015-12-01 |
| 卷号 | 56期号:11页码:2473-2482 |
| 关键词 | Chinese lunar exploration program Global navigation satellite system Weak signal acquisition and tracking performance Fusion processing of space- and ground-based data Accuracy of orbit determination and prediction |
| 英文摘要 | A global navigation satellite system (GNSS) receiver with high sensitivity is embarked by the Chang'E-5T spacecraft for a trial in the Chinese lunar exploration program. The GNSS flight experiment was activated twice on October 23 and 31, 2014. The measurement data of this experiment are analyzed here. When the distance between the Earth center and Chang'E-5T probe ranges from approximately 10,000-60,000 km, the mean number of tracked GNSS satellites by the receiver onboard Chang'E-5T is 8-9, and the range of Position Dilution of Precision (PDOP) is 1-40. The noise of single-differencing C/A code pseudorange data is 5.7-8.1 m (1 sigma). The ratio of carrier to noise spectral density (C/N0) is approximately 35 dB-Hz when the distance between the spacecraft and GPS satellites was close to 60,000 km. The post-processed orbit solution using terrestrial-based radiometric measurement in the 22 h arc is used as the reference orbit for accuracy analysis of orbit determination and prediction. Based on this approach, the position error in the one-hour prediction from the orbit determination using GNSS single-difference pseudorange in the 1.5 h arc is less than 109 m, while that from the result using range and Doppler data in the 3 h arc is 369 m. The residual Root Mean Squares (RMS) divergence of GNSS single differential pseudorange and range in the prediction arc relative to the orbit determination arc are reduced by 65% and 90%, respectively, using GNSS data to estimate the orbit compared to using ground-based data. Furthermore, the strategy of orbit determination by combining GNSS and ground-based data is examined in the paper. The position error in the one-hour prediction using this strategy is less than 47 m using the 1.5 h data to determine the orbit, and the residual RMS divergences of GNSS and range measurement are reduced by 96% and 67%, respectively. Therefore, the validity of GNSS supporting orbit determination for sampling and returning from lunar explorations is verified. (C) 2015 COSPAR. Published by Elsevier Ltd. All rights reserved. |
| WOS标题词 | Science & Technology ; Physical Sciences |
| 类目[WOS] | Astronomy & Astrophysics ; Geosciences, Multidisciplinary ; Meteorology & Atmospheric Sciences |
| 研究领域[WOS] | Astronomy & Astrophysics ; Geology ; Meteorology & Atmospheric Sciences |
| 关键词[WOS] | MISSION |
| 收录类别 | SCI |
| 语种 | 英语 |
| WOS记录号 | WOS:000365367900015 |
| 源URL | [http://119.78.226.72/handle/331011/28402]  |
| 专题 | 上海天文台_行星科学重点实验室 上海天文台_天文地球动力学研究中心 |
| 作者单位 | 1.Chinese Acad Sci, Shanghai Astron Observ, Shanghai 200030, Peoples R China 2.Univ Chinese Acad Sci, Beijing 100049, Peoples R China 3.Beijing Inst Tracking & Telecommun Technol, Beijing 100094, Peoples R China 4.Beijing Aerosp Control Ctr, Beijing 100094, Peoples R China |
| 推荐引用方式 GB/T 7714 | Fan, Min,Hu, XiaoGong,Dong, Guangliang,et al. Orbit improvement for Chang'E-5T lunar returning probe with GNSS technique[J]. ADVANCES IN SPACE RESEARCH,2015,56(11):2473-2482. |
| APA | Fan, Min.,Hu, XiaoGong.,Dong, Guangliang.,Huang, Yong.,Cao, Jianfeng.,...&Yu, Yang.(2015).Orbit improvement for Chang'E-5T lunar returning probe with GNSS technique.ADVANCES IN SPACE RESEARCH,56(11),2473-2482. |
| MLA | Fan, Min,et al."Orbit improvement for Chang'E-5T lunar returning probe with GNSS technique".ADVANCES IN SPACE RESEARCH 56.11(2015):2473-2482. |
入库方式： OAI收割
来源：上海天文台
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