An Improved Algorithm for Autonomous Orbit Determination of Navigation Satellite Constellation

Survey Review ◽  
2011 ◽  
Vol 43 (322) ◽  
pp. 361-369 ◽  
Author(s):  
Jikun Ou ◽  
Wenwu Ding ◽  
Jihua Liu ◽  
Shiming Zhong
Keyword(s):  
Orbit Determination ◽  
Navigation Satellite ◽  
Satellite Constellation ◽  
Autonomous Orbit Determination ◽  
Improved Algorithm

scholarly journals Accurate and Rapid Broadcast Ephemerides for Beidou-Maneuvered Satellites

2019 ◽  
Vol 11 (7) ◽  
pp. 787 ◽  
Author(s):  
Jing Qiao ◽  
Wu Chen ◽  
Shengyue Ji ◽  
Duojie Weng
Keyword(s):  
Orbit Determination ◽  
Piecewise Linear ◽  
Precise Orbit Determination ◽  
Satellite System ◽  
Navigation Satellite ◽  
Beidou Navigation Satellite System ◽  
German Research ◽  
Global Navigation Satellite ◽  
Ranging Errors

The geostationary earth orbit (GEO) and inclined geosynchronous orbit (IGSO) satellites of the Beidou navigation satellite system are maneuvered frequently. The broadcast ephemeris can be interrupted for several hours after the maneuver. The orbit-only signal-in-space ranging errors (SISREs) of broadcast ephemerides available after the interruption are over two times larger than the errors during normal periods. To shorten the interruption period and improve the ephemeris accuracy, we propose a two-step orbit recovery strategy based on a piecewise linear thrust model. The turning points of the thrust model are firstly determined by comparison of the kinematic orbit with an integrated orbit free from maneuver; afterward, precise orbit determination (POD) is conducted for the maneuvered satellite by estimating satellite orbital and thrust parameters simultaneously. The observations from the IGS Multi-Global Navigation Satellite System (GNSS) Experiment (MGEX) network and ultra-rapid products of the German Research Center for Geosciences (GFZ) are used for orbit determination of maneuvered satellites from Sep to Nov 2017. The results show that for the rapidly recovered ephemerides, the average orbit-only SISREs are 1.15 and 1.0 m 1 h after maneuvering for GEO and IGSO respectively, which is comparable to the accuracy of Beidou broadcast ephemerides in normal cases.

scholarly journals Experimental Study on the Precise Orbit Determination of the BeiDou Navigation Satellite System

Sensors ◽  
2013 ◽  
Vol 13 (3) ◽  
pp. 2911-2928 ◽  
Author(s):  
Lina He ◽  
Maorong Ge ◽  
Jiexian Wang ◽  
Jens Wickert ◽  
Harald Schuh
Keyword(s):  
Experimental Study ◽  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Satellite System ◽  
Navigation Satellite ◽  
Beidou Navigation Satellite System ◽  
Precise Orbit

A Universe Light House — Candidate Architectures of the Libration Point Satellite Navigation System

2014 ◽  
Vol 67 (5) ◽  
pp. 737-752 ◽  
Author(s):  
Lei Zhang ◽  
Bo Xu
Keyword(s):  
Navigation System ◽  
Orbit Determination ◽  
Libration Point ◽  
Satellite Navigation ◽  
Navigation Systems ◽  
Satellite Navigation System ◽  
Libration Point Orbits ◽  
Satellite Constellation ◽  
The Earth ◽  
Autonomous Orbit Determination

In view of the shortcomings of existing satellite navigation systems in deep-space performance, candidate architectures which utilise libration point orbits in the Earth-Moon system are proposed to create an autonomous satellite navigation system for lunar missions. Three candidate constellations are systematically studied in order to achieve continuous global coverage for lunar orbits: the Earth-Moon L1,2 two-satellite constellation, the Earth-Moon L2,4,5 three-satellite constellation and the Earth-Moon L1,2,4,5 four-satellite constellation. After a thorough search for possible configurations, the latter two constellations are found to be the simplest feasible architectures for lunar navigation. Finally, an autonomous orbit determination simulation is performed to verify the autonomy of the system and two optimal configurations are obtained in a comprehensive consideration of coverage and autonomous orbit determination performance.

scholarly journals Autonomous Orbit Determination for Lagrangian Navigation Satellite Based on Neural Network Based State Observer

2017 ◽  
Vol 2017 ◽  
pp. 1-10 ◽  
Author(s):  
Youtao Gao ◽  
Tanran Zhao ◽  
Bingyu Jin ◽  
Junkang Chen ◽  
Bo Xu
Keyword(s):  
Neural Network ◽  
Orbit Determination ◽  
Transition Matrix ◽  
State Observer ◽  
Nonlinear Perturbations ◽  
The Neural Network ◽  
Autonomous Orbit Determination ◽  
Simulation Results ◽  
Libration Orbits

In order to improve the accuracy of the dynamical model used in the orbit determination of the Lagrangian navigation satellites, the nonlinear perturbations acting on Lagrangian navigation satellites are estimated by a neural network. A neural network based state observer is applied to autonomously determine the orbits of Lagrangian navigation satellites using only satellite-to-satellite range. This autonomous orbit determination method does not require linearizing the dynamical mode. There is no need to calculate the transition matrix. It is proved that three satellite-to-satellite ranges are needed using this method; therefore, the navigation constellation should include four Lagrangian navigation satellites at least. Four satellites orbiting on the collinear libration orbits are chosen to construct a constellation which is used to demonstrate the utility of this method. Simulation results illustrate that the stable error of autonomous orbit determination is about 10 m. The perturbation can be estimated by the neural network.

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