Full Text:   <366>

Summary:  <116>

CLC number: TP39; V19

On-line Access: 2019-07-08

Received: 2018-05-19

Revision Accepted: 2018-12-02

Crosschecked: 2019-06-11

Cited: 0

Clicked: 1008

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Qiao Wang

http://orcid.org/0000-0002-0678-047X

Xiao-Jun Jin

http://orcid.org/0000-0002-8804-9890

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Frontiers of Information Technology & Electronic Engineering  2019 Vol.20 No.6 P.829-841

http://doi.org/10.1631/FITEE.1800308


An online error calibration method for spaceflight TT&C systems based on LEO-ground DDGPS


Author(s):  Qiao Wang, Xiao-Jun Jin, Wei Zhang, Shi-Ming Mo, Zhao-Bin Xu, Zhong-He Jin

Affiliation(s):  Micro-Satellite Research Center, Zhejiang University, Hangzhou 310027, China

Corresponding email(s):   wqiao2010@zju.edu.cn, axemaster@zju.edu.cn

Key Words:  Spaceflight, low Earth orbit (LEO), Filter, Optimization, Calibration


Qiao Wang, Xiao-Jun Jin, Wei Zhang, Shi-Ming Mo, Zhao-Bin Xu, Zhong-He Jin. An online error calibration method for spaceflight TT&C systems based on LEO-ground DDGPS[J]. Frontiers of Information Technology & Electronic Engineering, 2019, 20(6): 829-841.

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journal="Frontiers of Information Technology & Electronic Engineering",
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publisher="Zhejiang University Press & Springer",
doi="10.1631/FITEE.1800308"
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A1 - Zhao-Bin Xu
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Abstract: 
To overcome the shortcomings of the traditional measurement error calibration methods for spaceflight telemetry, tracking and command (TT&C) systems, an online error calibration method based on low Earth orbit satellite-to-ground double- differential GPS (LEO-ground DDGPS) is proposed in this study. A fixed-interval smoother combined with a pair of forward and backward adaptive robust Kalman filters (ARKFs) is adopted to solve the LEO-ground baseline, and the ant colony optimization (ACO) algorithm is used to deal with the ambiguity resolution problem. The precise baseline solution of DDGPS is then used as a comparative reference to calibrate the systematic errors in the TT&C measurements, in which the parameters of the range error model are solved by a batch least squares algorithm. To validate the performance of the new online error calibration method, a hardware-in-the-loop simulation platform is constructed with independently developed spaceborne dual-frequency GPS receivers and a Spirent GPS signal generator. The simulation results show that with the fixed-interval smoother, a baseline estimation accuracy (RMS, single axis) of better than 10 cm is achieved. Using this DDGPS solution as the reference, the systematic error of the TT&C ranging system is effectively calibrated, and the residual systematic error is less than 5 cm.

基于星地差分GPS的航天测控系统在线误差标校方法研究

摘要:为克服传统误差标校方法的缺点,提出一种基于星地差分GPS的航天测控系统在线误差标校方法。该方法采用固定区间平滑算法,平滑前向、后向抗差自适应卡尔曼滤波结果,同时基于蚁群最优化算法固定星地差分GPS载波相位模糊度,以获取高精度星地基线测量结果。将该结果作为航天测控系统比较标准,并用最小二乘批处理算法求解测距误差模型。利用Spirent导航信号模拟器和自主研制的星载GPS双频接收机,构建半实物仿真平台对该误差标校方法进行仿真验证。结果表明,固定区间平滑算法平滑后,星地基线解算精度(RMS,单轴)优于10 cm。测距系统误差标定后,残差优于5 cm。

关键词:航天测控系统;低轨卫星;滤波;优化算法;标校

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

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