Orbit improvement for Chang’E-5T lunar returning probe with GNSS technique

Mo, Fan; Hu, Xiaogong; Dong, Guangliang; Huang, Yong; Cao, Jianfeng; Tang, Chengpan; Li, Peijia; Chang, Shenghai; Yu, Yang

doi:10.1016/j.asr.2015.09.010

Cited by 24 publications

(10 citation statements)

References 7 publications

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“…The kinematic orbit precision is roughly at 90 m level on average and can reach 50 m when the altitude reaches 20,000 km. This precision is consistent with the results from [ 28 ], which were obtained by OD using C1 code ranges combined with ground-tracking measurements.…”

Section: Chang’e-5t Orbit Determinationsupporting

confidence: 91%

“…The objective of Arc 2 was to evaluate the prediction accuracy of the separation point between the service module and the return vehicle. Unfortunately, there was a data slip in the middle of Arc 1 that lasted approximately 3 min [ 28 ]. As a result, the Arc 2 is chosen to be analyzed here.…”

Section: Chang’e-5t Onboard Gps Data Analysismentioning

confidence: 99%

“…This receiver is capable of tracking up to 24 satellites simultaneously with 24 channels. Since the GLONASS tracking data are much less and the accuracies are poorer than that of GPS [ 28 ], we didn’t introduce the contribution of GLONASS in Chang’E-5T OD. The data collected by the receiver include the carrier phase, pseudo-range, Doppler and C/N0 measurement of L1 band in Receiver Independent Exchange Format (RINEX) 2.0 format.…”

Section: Chang’e-5t Onboard Gps Data Analysismentioning

confidence: 99%

“…Fang et al [ 27 ] firstly proved the idea of using rocket GPS measurements to determine the injected transfer orbit of Chang’E-5T. Fan et al [ 28 ] conducted Chang’E-5T OD using onboard GPS pseudo-range measurements by dynamic method, and results showed that the position error in the one-h prediction from the OD of 1.5 h arc is less than 109 m. However, the higher accuracy carrier phase measurements were not used in Fang et al [ 27 ] or Fan et al [ 28 ]. For the combined use of pseudo-range and carrier phase measurements in SSV, weighting approach needs to be investigated because of the lack of a priori measurement precision information compared to TSV users.…”

Section: Introductionmentioning

confidence: 99%

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Chang’E-5T Orbit Determination Using Onboard GPS Observations

Su¹,

Geng²,

Li³

et al. 2017

Sensors

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In recent years, Global Navigation Satellite System (GNSS) has played an important role in Space Service Volume, the region enclosing the altitudes above 3000 km up to 36,000 km. As an in-flight test for the feasibility as well as for the performance of GNSS-based satellite orbit determination (OD), the Chinese experimental lunar mission Chang’E-5T had been equipped with an onboard high-sensitivity GNSS receiver with GPS and GLONASS tracking capability. In this contribution, the 2-h onboard GPS data are evaluated in terms of tracking performance as well as observation quality. It is indicated that the onboard receiver can track 7–8 GPS satellites per epoch on average and the ratio of carrier to noise spectral density (C/N0) values are higher than 28 dB-Hz for 90% of all the observables. The C1 code errors are generally about 4.15 m but can be better than 2 m with C/N0 values over 36 dB-Hz. GPS-based Chang’E-5T OD is performed and the Helmert variance component estimation method is investigated to determine the weights of code and carrier phase observations. The results reveal that the orbit consistency is about 20 m. OD is furthermore analyzed with GPS data screened out according to different C/N0 thresholds. It is indicated that for the Chang’E-5T, the precision of OD is dominated by the number of observed satellite. Although increased C/N0 thresholds can improve the overall data quality, the available number of GPS observations is greatly reduced and the resulting orbit solution is poor.

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Section: Chang’e-5t Orbit Determinationsupporting

confidence: 91%

Section: Chang’e-5t Onboard Gps Data Analysismentioning

confidence: 99%

Section: Chang’e-5t Onboard Gps Data Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Chang’E-5T Orbit Determination Using Onboard GPS Observations

Su¹,

Geng²,

Li³

et al. 2017

Sensors

View full text Add to dashboard Cite

show abstract

“…事后统计定轨技术已经相当成熟, 对月球的动力学建模以及相关定轨软件研发都取得了很好的进展. 国内Huang等人 [1][2][3] 、Li等人 [4][5][6] 、曹建峰等人 [7][8][9] 、张宇等人 [10] 、董光亮等人 [11] 对"嫦娥一号"、 "嫦娥二号"、"嫦娥三号"探测器的事后统计定轨工作 Fan等人 [12] 、Cao等人 [13] 、Liu等人 [14]…”

Section: 李培佳等中国科学: 物理学力学天文学 2017年第47卷第12期unclassified