Orbit Determination of Spacecraft Using Global Positioning System Single-Frequency Measurement

Yoon, Jae-Cheol; Roh, Kyoung-Min; Park, Eun-Seo; Moon, Bo-Yeon; Choi, Kyu-Hong; Lee, Jeong-Sook; Lee, Byoung-Sun; Kim, Jae-Hoon; Chang, Young-Keun

doi:10.2514/2.3881

Cited by 13 publications

(6 citation statements)

References 12 publications

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“…As an alternative to model‐based corrections, a rigorous elimination of ionospheric errors can be achieved through the Group and Phase Ionospheric Correction (GRAPHIC) [ Yunck , 1996] combination of single‐frequency code carrier measurements. Recent works that have successfully applied this technique for dynamic and kinematic orbit determination include Berthias et al [2001], Yoon et al [2002], and Montenbruck [2003].…”

Section: Introductionmentioning

confidence: 99%

Low Earth orbit satellite navigation errors and vertical total electron content in single‐frequency GPS tracking

García-Fernández

Montenbruck

2006

Radio Science

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[1] In the context of space applications, the GPS system is presently a well-established and accepted tracking system. To meet the basic navigation requirements, most satellites in a low Earth orbit are equipped with single-frequency GPS receivers that measure the coarse acquisition code as well as the L1 phase. However, the resulting kinematic navigation solutions exhibit systematic position errors caused by elevation-dependent ionospheric path delays. In this study a simple analytical model is established, which quantitatively relates the position error to the vertical electron content and the mapping function. This model substantiates the empirical evidence of a mean radial offset that increases in proportion to the total electron content above the satellite. It is furthermore shown that the ratio between this offset and the vertical ionospheric path delay depends on the applied elevation mask angle. Representative ratios of 3-5 are obtained for the mapping function of the Lear ionosphere model and elevation cutoff angles of 10°, 5°, and 0°. This analytical result has further been confirmed by signal simulator tests as well as flight data of the CHAMP satellite.Citation: Garcia-Fernàndez, M., and O. Montenbruck (2006), Low Earth orbit satellite navigation errors and vertical total electron content in single-frequency GPS tracking, Radio Sci., 41, RS5001,

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Section: Introductionmentioning

confidence: 99%

Low Earth orbit satellite navigation errors and vertical total electron content in single‐frequency GPS tracking

García-Fernández

Montenbruck

2006

Radio Science

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“…GPS time is used for all measurement time-tagging. The equation of motion and variation equations are integrated using Adams-Cowell 11 th -order predictor-corrector method 9 . Macromodel of satellite flat plate arranged in the shape of a box and connected solar array for KOMPSAT-2 is used for nongravitational model such as drag and solar radiation flux pressure.…”

Section: Figure 6 Igs Stations For Kompsat-2 Podmentioning

confidence: 99%

“…Thus, a direct calibration that combines phase and pseudorange data using range delay and phase advance and ionosphere model such as Global Ionosphere Model (GIM 2 ) can be used for single frequency GPS data to eliminate the ionosphere delay. To reduce the ionospheric error, a method based on ionosphere models or the use of Group and Phase Ionospheric Calibration (GRAPHIC 3 ) technique that averages carrier phase and pseudorange has been tried for single frequency GPS users [4][5][6][7][8][9][10] .…”

Section: Introductionmentioning

confidence: 99%

KOMPSAT-2 Precise Orbit Determination Using GPS Data

Hwang

Lee

Kim

et al. 2007

25th AIAA International Communications Satellite Systems Conference (Organized by APSCC)

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A Precise Orbit Determination (POD) has been developed for Korea multipurpose satellite-2 (KOMPSAT-2) to fulfill the requirement for 1 m positioning accuracy. The POD is resolved using single-frequency Global Positioning System (GPS) data in a dynamic filter. To compensate for the ionospheric delay by single-frequency GPS receiver, we use following techniques such as the group and phase ionosphere calibration (GRAPHIC) and scale factor estimate for international reference ionosphere-2000 (IRI-2000). Also, time drifting error of GPS receiver is estimated during the data preprocessing. The POD produced 4-hour overlapping arc position error approximately 1 m Root-Sum-Square (RMS) for 30-hour data arc, which satisfies the design requirement for KOMSAT-2. The implemented method and achieved results for the KOMPSAT-2 POD are presented. Nomenclature N = integer ambiguity 1 P = pseudorange observable on GPS L1 frequency 1 Φ = carrier phase range observable on GPS L1 frequency 0 ,t t k = tagging time of measurement for arbitrary epoch, k and minimum range epoch, 0 during the phase lock, respectively, sec ion ρ Δ = ionospheric range delay, m S R ρ = geometric range from GPS satellite transmitter to the LEO satellite receiver antenna, m ph gr ε ε , = measurement error for group delay and pseudorange except ionosphere error, respectively α = scale factor

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“…Rapid Science Orbit (RSO) for GOCE satellite proved that orbit error is less than 10 cm Root-Sum-Squares (RSS) using kinematic method [4]. Ionosphere-free precise orbit determination (POD) was also studied for CHAMP satellite and KOMPSAT-2 [3,5]. The POD using single-frequency GPS data mostly showed at least 1 m positioning error.…”

Section: Introductionmentioning

confidence: 99%

Design and Implementation for KOMPSAT-5 Orbit Determination Operations

Hwang¹,

Lee²,

Kim³

et al. 2012

SpaceOps 2012 Conference

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KOrea-Multi-Purpose-SATellite (KOMPSAT)-5 is the first Korean satellite to perform synthetic aperture radar (SAR) mission and support radio occultation. In order to process SAR and radio occultation data, precise position and velocity are required. KOMPSAT-5 orbit determination system consists of Operational orbit determination (OOD) and precise orbit determination (POD). The satellite operational orbit supporting satellite operation is adjusted using satellite on-board global-positioning-system (GPS) navigation solutions data as well as ground-based satellite tracking and ranging data. KOMPSAT-5 carries two GPS receivers, TOPSTAR 3000 and IGOR, to perform orbit determination (OD) based on GPS data. IGOR dual-frequency GPS receiver is mainly operated for a primary mission support and TOPSTAR 3000 is a backup single-frequency GPS receiver. The POD result is validated using satellite lager ranging (SLR) data and the daily precise satellite position data are transferred to the international laser raging service (ILRS) site. KOMPSAT-5 POD and OOD are designed to meet the requirements of 20 cm and 5 m (one-sigma) positioning accuracy in three-dimension, respectively. However, KOMPSAT-5 OD using ranging and antenna pointing data is normally operated when GPS data is not available or before GPS receiver is activated on. The position error based on the range, azimuth, and elevation data should be satisfied within ±1000m (three-sigma) for processing three-day measurement data. The requirement of OD performance is fully validated showing all OD requirements are satisfied for normal operation.

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Orbit Determination of Spacecraft Using Global Positioning System Single-Frequency Measurement

Cited by 13 publications

References 12 publications

Low Earth orbit satellite navigation errors and vertical total electron content in single‐frequency GPS tracking

Low Earth orbit satellite navigation errors and vertical total electron content in single‐frequency GPS tracking

KOMPSAT-2 Precise Orbit Determination Using GPS Data

Design and Implementation for KOMPSAT-5 Orbit Determination Operations

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