Fast satellite selection algorithm for GNSS multi-system based on Sherman–Morrison formula

Shi, Junpeng; Li, Kezhao; Chai, Lu; Liang, Lingfeng; Tian, Chendong; Xu, Ke

doi:10.1007/s10291-022-01384-3

Cited by 5 publications

(2 citation statements)

References 13 publications

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“…Combined with the results of the "Analysis of the SVOP Values" subsection, it can be concluded that the deployment of 4 satellites in each orbit cannot meet the real-time positioning requirements. In order to achieve the real-time positioning effect of the 3-orbit lunar GNSS constellation, combining the constellation composition of GNSS with the theory of satellite selection 18 , and considering the satellite launch and operation cost, let each orbit has 5 satellites, a total of 15 satellites. The satellites of one orbit are evenly distributed in the orbit, and the phase difference of the adjacent satellites is 10  in the different Halo orbits.…”

Section: Resultsmentioning

confidence: 99%

Multi-orbit Lunar GNSS Constellation Design with Distant Retrograde Orbit and Halo Orbit Combination

Wang

et al. 2023

Preprint

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The Moon is the closest natural planet to mankind, with valuable resources on it, and is an important base station for mankind to enter deep space. How to establish a reasonable lunar Global Navigation Satellite System (GNSS) to provide real-time positioning, navigation, and timing (PNT) services for moon exploration and development has become a hot spot for many international scholars. Based on the special spatial configuration characteristics of Libration point orbits (LPOs), the coverage capability of Halo orbits and Distant Retrograde Orbit (DRO) in LPOs is discussed and analyzed in detail. It is concluded that the Halo orbit with a period of 8 days has a better coverage effect on the lunar polar regions and the DRO has a more stable coverage effect on the lunar equatorial regions, and the multi-orbital lunar GNSS constellation with the optimized combination of DRO and Halo orbits is proposed by combining the advantages of both. This multi-orbital constellation can make up for the fact that a single type of orbit requires a larger number of satellites to fully cover the Moon, using a smaller number of satellites for the purpose of providing PNT services to the entire lunar surface. The design of the multi-orbital lunar GNSS constellation meeting the requirements of real-time positioning on the whole moon surface in two sets is given in combination with simulation calculations. The simulation experiment results show that the multi-orbital lunar GNSS constellation n combining DRO and Halo orbit can cover 100% of the moon surface, and there are more than 4 visible satellites at any time on the moon surface, which meets the navigation and positioning requirements, and the PDOP value is stable within 2.0, which can meet the demand for higher precision moon surface navigation and positioning.

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Section: Resultsmentioning

confidence: 99%

Multi-orbit Lunar GNSS Constellation Design with Distant Retrograde Orbit and Halo Orbit Combination

Wang

et al. 2023

Preprint

Self Cite

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“…The initial approach involves determining the optimal satellite combination by assessing the influence of currently observable satellites on the overall GDOP. Subsequently, a recursive strategy is employed to finalize the optimal satellite constellation [1][2][3][4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Signal Occlusion-Resistant Satellite Selection for Global Navigation Applications Using Large-Scale LEO Constellations

Guo,

Wang,

Sun

2023

Remote Sensing

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With the continuous construction of large-scale Low Earth Orbit (LEO) constellations, their potential for Global Navigation Satellite System (GNSS) applications has been emphasized. This study aims to derive an optimal positioning configuration formula based on the ratio of high-elevation and low-elevation satellites, which can improve the positioning accuracy and overcome the accuracy loss due to signal occlusion. A genetic algorithm is used to solve the optimal positioning configuration problem for large-scale satellite selection. Through a simulation using Starlink satellites currently in orbit, it is verified that the traditional recursive algorithm cannot be applied to satellite selection for large-scale constellations. The proposed formula has a similar accuracy to the Quasi-Optimal algorithm when there is no signal occlusion and the satellites are uniformly selected. However, the accuracy of the latter deteriorates significantly under signal occlusion. Our algorithm can effectively overcome this problem. Moreover, we discuss the effect of different types of obstructions on the accuracy loss. We find that the Quasi-Optimal algorithm is more sensitive to a single large-angle obstruction than multiple small-angle obstructions. Our proposed formula can reduce the localization accuracy degradation caused by signal occlusions in both scenarios.

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Multi-orbit lunar GNSS constellation design with distant retrograde orbit and Halo orbit combination

Wang

et al. 2023

Sci Rep

View full text Add to dashboard Cite

The Moon is the closest natural satellite to mankind, with valuable resources on it, and is an important base station for mankind to enter deep space. How to establish a reasonable lunar Global Navigation Satellite System (GNSS) to provide real-time positioning, navigation, and timing (PNT) services for Moon exploration and development has become a hot topic for many international scholars. Based on the special spatial configuration characteristics of Libration point orbits (LPOs), the coverage capability of Halo orbits and Distant Retrograde Orbit (DRO) in LPOs is discussed and analyzed in detail. It is concluded that the Halo orbit with a period of 8 days has a better coverage effect on the lunar polar regions and the DRO has a more stable coverage effect on the lunar equatorial regions, and the multi-orbital lunar GNSS constellation with the optimized combination of DRO and Halo orbits is proposed by combining the advantages of both. This multi-orbital constellation can make up for the fact that a single type of orbit requires a larger number of satellites to fully cover the Moon, using a smaller number of satellites for the purpose of providing PNT services to the entire lunar surface. We designed simulation experiments to test whether the multi-orbital constellations meet the full lunar surface positioning requirements, and compare the coverage, positioning, and occultation effects of the four constellation designs that pass the test, and finally obtain a set of well-performing lunar GNSS constellations. The results indicate that the multi-orbital lunar GNSS constellation combining DRO and Halo orbits can cover 100% of the Moon surface, provides there are more than 4 visible satellites at any time on the Moon surface, which meets the navigation and positioning requirements, and the Position Dilution of Precision (PDOP) value is stable within 2.0, which can meet the demand for higher precision Moon surface navigation and positioning.

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Fast satellite selection algorithm for GNSS multi-system based on Sherman–Morrison formula

Cited by 5 publications

References 13 publications

Multi-orbit Lunar GNSS Constellation Design with Distant Retrograde Orbit and Halo Orbit Combination

Multi-orbit Lunar GNSS Constellation Design with Distant Retrograde Orbit and Halo Orbit Combination

Signal Occlusion-Resistant Satellite Selection for Global Navigation Applications Using Large-Scale LEO Constellations

Multi-orbit lunar GNSS constellation design with distant retrograde orbit and Halo orbit combination

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