Inter-agency comparison of TanDEM-X baseline solutions

Jäggi, Adrian; Montenbruck, Oliver; Moon, Y.; Wermuth, Martin; König, Rolf; Michalak, Grzegorz; Bock, Heike; Bodenmann, Dominik

doi:10.1016/j.asr.2012.03.027

Cited by 46 publications

(22 citation statements)

References 24 publications

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“…Satellite missions devoted to the observation of the Earth and its climate such as those studying gravity, atmosphere, and altimetry commonly use RGT orbits [10,8]. RGT configuration is useful for Earth observation missions, because satellite flies over a site on the surface of the Earth periodically.…”

Section: Introductionmentioning

confidence: 99%

Repeat ground track orbit design with desired revisit time and optimal tilt

Nadoushan

Assadian

2015

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 99%

Repeat ground track orbit design with desired revisit time and optimal tilt

Nadoushan

Assadian

2015

Aerospace Science and Technology

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“…The use of GPS tracking data and reduced-dynamic technique (Wu et al 1991) have allowed single-satellite POD of some LEOs to reach the centimeter level, such as CHAMP (Visser and van den Ijssel 2003), Jason-1 (Haines et al 2004), GRACE (Jäggi et al 2007), Jason-2 (Zelensky et al 2010) and GOCE (Bock et al 2014). The precision of intersatellite PBD can even reach the millimeter level, such is the case for GRACE and TanDEM-X (Jäggi et al 2012) formations.…”

Section: Introductionmentioning

confidence: 99%

“…These maneuvers must be replicated by the TDX satellite synchronously to avoid breaking up of the formation. Additional formation-keeping maneuvers must be performed on the TDX satellite twice per day to maintain a helix flying configuration (Jäggi et al 2012). Similar and even more frequent maneuvers arise in the Prototype Research Instruments and Space Mission technology Advancement (PRISMA) mission, which is a Swedish-led autonomous formation-flying experiment (Gill et al 2007).…”

Section: Introductionmentioning

confidence: 99%

“…For the EPOS and the BERNESE software packages used at the Germany Research Center for Geosciences (GFZ) and the Astronomical Institute of the University of Bern (AIUB), respectively, maneuvers are modeled as a series of velocity impulses at predefined epochs based on the execution time of each maneuver. These instantaneous velocity changes are estimated along with other parameters, e.g., dynamic parameters, pseudo-stochastic parameters, ambiguity parameters, in the least squares adjustment in both POD processing and PBD processing Jäggi et al 2012). For the GHOST software package used at the German Space Operations Center (DLR), maneuvers are treated as constant thrusts over specified intervals according to the burn start time and duration.…”

Section: Introductionmentioning

confidence: 99%

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Precise orbit and baseline determination for maneuvering low earth orbiters

Herring

et al. 2015

GPS Solut

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Orbital maneuvers are usually performed as needed for low earth orbiters to maintain a predefined trajectory or formation-flying configuration. To avoid unexpected discontinuities and to connect pre-and postmaneuver arcs with a minimal set of parameters, a maneuver has to be considered in the routine GPS-based orbit determinations. We propose a maneuver handling method in a reduced-dynamic scheme. With the proper thrust modeling and numerical integration strategy, the effects caused by orbital maneuver can be largely eliminated. The performance for both single-satellite precise orbit determination (POD) and inter-satellite precise baseline determination (PBD) is demonstrated using selected data sets from the Gravity Recovery and Climate Experiment (GRACE) mission. For the POD results, the orbit determination residuals indicate that the orbit with maneuver modeling is well fit to the GPS observations. The external orbit validation shows that the GRACE-B orbits obtained from our approach match the DLR reference orbits better than 3 cm (3D RMS), which is comparable to the result of the maneuver-free GRACE-A satellite. For the PBD results, on average 87 % of double-difference phase ambiguities can be resolved to integers and an RMS of the K-band ranging system residuals of better than 0.7 mm can be achieved, even though the orbital maneuver was performed on the spacecraft. Furthermore, the actual maneuver performance derived from the POD and PBD results provides rigorous feedback on the thruster system, which is not only beneficial for current maneuver assessment but also for future maneuver plans.

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“…It is planned to use microwave ranging as the primary instrument for inter-satellite distance measurements, however laser interferometry has been proposed as an alternative system, able to achieve improved inter-satellite ranging precision. Another mission known as PRISMA also benefits from use of a radio frequency (RF) ) TanDEM-X Dual-frequency GPS 20 km Post processing * 1 mm 3D std dev (Jäggi et al, 2012) PRISMA Single-frequency GPS 0 * 30 km Real-time 5 cm 3D rms 438…”

Section: Introductionmentioning

confidence: 99%

Inter-satellite Ranging Augmented GPS Relative Navigation for Satellite Formation Flying

Yang

Rizos

et al. 2013

J. Navigation

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An Augmented Relative Navigation System (ARNS) is proposed for autonomous satellite formation flying in low-Earth-orbit (LEO). Inter-satellite ranging systems such as those based on radio frequency transmissions can provide additional observation information, e.g. inter-satellite distance measurement, which can be used to increase the Global Positioning System (GPS) stand-alone observation dimension, or treated as a non-linear equality constraint within a smoothly-constrained Kalman filter. Both approaches are implemented in the proposed ARNS described in this paper. An innovative phase integer ambiguity fixing and feedback scheme is implemented to increase the ambiguity fix rate of the GPS carrier phase measurements. A set of Gravity Recovery and Climate Experiment (GRACE) flight data is used to test and validate the relative navigation performance of the proposed methods. Results indicate that the augmented system can improve relative positioning accuracy by an order of magnitude. I N T R O D U C T I O N .Satellite formation flying is one of the typical forms of a so-called Distributed Space System, in which more than two spacecraft are flying in a coordinated manner to fulfil a particular space mission. The formation flying of spacecraft to replace a single large satellite will provide opportunities for a number of future applications, including synthetic apertures for high-resolution interferometry missions. Such missions require precise relative satellite state (position and velocity) information. Hence relative navigation is one of the primary tasks in a satellite formation flying mission.

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Inter-agency comparison of TanDEM-X baseline solutions

Cited by 46 publications

References 24 publications

Repeat ground track orbit design with desired revisit time and optimal tilt

Repeat ground track orbit design with desired revisit time and optimal tilt

Precise orbit and baseline determination for maneuvering low earth orbiters

Inter-satellite Ranging Augmented GPS Relative Navigation for Satellite Formation Flying

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