Results and Analyses of BDS Precise Orbit Determination with the Enhancement of Fengyun-3C

doi:10.11947/j.JGGS.2019.0307

Abstract

Abstract:

Global navigation satellite system occultation sounder (GNOS) Fengyun-3C was launched successfully on September 23, 2013, which carried GPS/BDS receiver for the first time. This provides the convenience to study the enhancement results of low earth orbiter satellite (LEO) to BDS precise orbit determination (POD). First the data characteristic and code observation noise of GNOS are analyzed. Then the enhancement experiments in the case of global and regional ground observation stations layout are processed with four POD schemes: BDS single system, GPS/BDS double system, BDS single system with GNOS observations, GPS/BDS double system with GNOS observations. The precision of BDS orbits and clocks are compared via overlapping arcs. Results show that in the case of global station layout the along directional precision of GEO satellite has the biggest improvement, with the improvement percentage 60%. Then the precision of cross direction and the along direction of remaining satellites shows the second biggest improvement. The orbit precision of BDS-only POD in part of observation arcs some satellite even suffers a slight decline. The root mean square (RMS) of overlapping clock difference of visible arcs in GPS/BDS POD experiments improves by 0.1ns level. As to the experiments of regional station layout with 7 ground stations, the orbit and clock overlapping precision and orbit predicting precision are analyzed. Results show that the predicting precision of BDS GEO satellites in the along direction improves by 85%. The remaining also has a substantial improvement, with the average percentage 21.7%. RMS of overlapping clock difference of visible arcs improves by 0.5ns level.

Key words: BeiDou satellite navigation system; LEO; precise orbit determination; GEO; orbit enhancement

Tian ZENG,Lifen SUI,Xiaolin JIA,Guofeng JI,Qinghua ZHANG. Results and Analyses of BDS Precise Orbit Determination with the Enhancement of Fengyun-3C[J]. Journal of Geodesy and Geoinformation Science, 2019, 2(3): 68-78.

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References 26

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	GPS						BDS
Visible satellite number	Number	0	1	2	3	>3	0	1	2	3	>3
	GNOS	0.2	0.0	0.0	0.0	99.7	11.7	12.4	12.2	14.1	49.6
	HY2A	0.0	0.0	0.1	0.5	99.4	—	—	—	—	—
Valid satellite number	GNOS	0.7	1.7	4.9	12.7	80.0	27.1	25.1	21.6	14.7	11.5
Valid satellite number	HY2A	0.6	0.0	0.1	0.4	99.0	—	—	—	—	—
Loss rate of observation code	Code	C1	P1	L1	P2	L2	P(B1)	L(B1)	P(B2)	L(B2)
	GNOS	99.5	—	90.0	87.9	64.7	90.7	66.1	88.3	66.4	—
	HY2A	100	96.6	99.8	94.2	94.0	—	—	—	—	—

		GEO	IGSO	MEO	All>10°	All>40°
CUT0	B1	0.27	0.49	0.52	0.39	0.28
CUT0	B2	0.22	0.35	0.37	0.29	0.22
GMSD	B1	0.19	0.25	0.29	0.23	0.19
GMSD	B2	0.17	0.23	0.26	0.21	0.17
REUN	B1	0.24	0.36	0.30	0.30	0.20
REUN	B2	0.20	0.37	0.41	0.32	0.22
GNOS	B1	0.38	0.41	0.36	0.38	0.23
GNOS	B2	0.29	0.32	0.24	0.29	0.20

Observation models	Information
Observation data		Un-differenced dual-frequency pseudorange and carrier phase data (sampling rate 30s for ground and 10s for LEO)
Phase center		GPS and ground: IGS ATX model; BDS: ESA; LEO: nominal PCO
Elevation cutoff angle		Ground 7°, LEO 0°
Tropospheric delay		Ground: SAAS model, 2-h ZTD and 1-day gradients; LEO: not needed
Ambiguity parameter		Partial fixed for ground and float for LEO
Satellite clock error		White noise (selecting a ground station as reference clock)
POD sampling rate		300s
Station coordinate		PPP network-solution, coordinate precision in millimeter level
Gravitational force models
Earth gravity		EIGEN_GL04 up to 10×10 for GPS and 120×120 for LEO
N-body gravitation Tide displacement Relativity effect		JPL DE405 IERS conventions 2003 IERS conventions 2003
Non-gravitational force models
Atmospheric drag Solar radiation pressure Empirical acceleration Earth radiation pressure		GPS: Not considered; LEO: DTM94, piecewise drag coefficients GPS: ECOM 5 parameters; LEO: Box-Wing GPS: No; LEO: Piecewise periodical terms in A, C and R directions Not considered

Test	orbit overlapping comparison/cm				clock overlapping comparison in visible arc/ns
Test	A	C	R	1D	STD (G I M)	RMS (G I M)
Test 1	196.9	39.3	10.3	118.7	0.40 (0.40 0.24 0.47)	0.59 (0.72 0.29 0.62)
Test 2	92.4	38.6	10.4	59.0	0.38 (0.40 0.22 0.45)	0.56 (0.68 0.27 0.58)
Test 3	135.7	5.0	3.5	79.0	0.19 (0.10 0.09 0.33)	0.44 (0.66 0.11 0.38)
Test 4	22.3	3.0	3.3	13.6	0.16 (0.12 0.07 0.25)	0.21 (0.19 0.10 0.28)

Test	Orbit overlapping comparison/cm				Clock overlapping comparison in visible arc/ns
Test	A	C	R	1D	STD (I M)	RMS (I M)
Test 3	7.8	3.7	3.1	5.5	0.22 (0.08 0.29)	0.25 (0.10 0.32)
Test 4	6.7	3.2	2.9	4.9	0.21 (0.07 0.29)	0.24 (0.09 0.31)