Kinematic Orbit Determination of LEOs Based on Zero or Double-difference Algorithms Using Simulated and Real SST GPS Data

The dynamic precise orbit determination of a Low Earth Orbit satellite using triple differenced GPS phases is presented in this study. The atmospheric drag parameters are estimated to compensate the incomplete atmosphere model for better precision of the orbit solution. In addition, the empirical force parameters, especially once- and twice-per-revolution components, along with the new IERS Conventions and models to compute the perturbing forces are introduced to absorb the remaining unmodelled forces. The optimal arc length for the parameterization and the data processing strategy are also tested and analyzed for the best orbit solutions. The triple differencing technique enables fast and efficient orbit estimation, because no ambiguity resolution and cycle slip detection are required. With the triple differenced ion-free GPS phase observables, the orbit and the velocity solutions for 24 hours of CHAMP are calculated; they compare with the published Rapid Science Orbit with the accuracy of 8 cm and 0·12 mm/s in 3D RMS for the orbit and the velocity, respectively, and are statistically consistent with the RSO when it is not better than 4 cm in terms of an absolute accuracy. The approach presented here provides an efficient and simple, but robust, alternative approach, while the solution's accuracy is still comparable to the double-difference results.

Download Full-text

Precise orbit determination of low Earth orbiters using undifferenced GPS data

10.1117/12.712607 ◽

2006 ◽

Author(s):

Cui-lin Kuang ◽

Fen Hou

Keyword(s):

Orbit Determination ◽

Precise Orbit Determination ◽

Gps Data ◽

Precise Orbit

Download Full-text

Improved GPS receiver clock modeling for kinematic orbit determination of the GRACE satellites

2012 European Frequency and Time Forum ◽

10.1109/eftf.2012.6502356 ◽

2012 ◽

Cited By ~ 1

Author(s):

Ulrich Weinbach ◽

Steffen Schon

Keyword(s):

Orbit Determination ◽

Gps Receiver ◽

Kinematic Orbit ◽

Receiver Clock ◽

Grace Satellites

Download Full-text

Kinematic and reduced-dynamic precise orbit determination of low earth orbiters

Advances in Geosciences ◽

10.5194/adgeo-1-47-2003 ◽

2003 ◽

Vol 1 ◽

pp. 47-56 ◽

Cited By ~ 92

Author(s):

D. Švehla ◽

M. Rothacher

Keyword(s):

Ambiguity Resolution ◽

Orbit Determination ◽

Precise Orbit Determination ◽

Double Difference ◽

Phase Measurements ◽

Precise Orbit ◽

First Results ◽

Orbit Dynamic ◽

Reduced Dynamic

Abstract. Various methods for kinematic and reduced-dynamic precise orbit determination (POD) of Low Earth Orbiters (LEO) were developed based on zero- and double-differencing of GPS carrier-phase measurements with and without ambiguity resolution. In this paper we present the following approaches in LEO precise orbit determination: – zero-difference kinematic POD, – zero-difference dynamic POD, – double-difference kinematic POD with and without ambiguity resolution, – double-difference dynamic POD with and without ambiguity resolution, – combined GPS/SLR reduced-dynamic POD. All developed POD approaches except the combination of GPS/SLR were tested using real CHAMP data (May 20-30, 2001) and independently validated with Satellite Laser Ranging (SLR) data over the same 11 days. With SLR measurements, additional combinations are possible and in that case one can speak of combined kinematic or combined reduced-dynamic POD. First results of such a combined GPS/SLR POD will be presented, too. This paper shows what LEO orbit accuracy may be achieved with GPS using different strategies including zerodifference and double-difference approaches. Kinematic versus dynamic orbit determination is presently an interesting issue that will also be discussed in this article.Key words. POD, kinematic orbit, dynamic orbit, LEO, CHAMP, ambiguity resolution, GPS, SLR

Download Full-text