High-precision dynamic orbit integration for spaceborne gravimetry

Matthias Ellmer, Torsten Mayer-Gürr

Research output: Contribution to conferencePosterResearch

Abstract

Future gravity missions like GRACE Follow-On and beyond will deliver low-low satellite-to-satellite ranging measurements of much increased precision. To prepare for the new challenges and opportunities involved in processing this new data, it is necessary to perform a systematic review and re-evaluation of current algorithms and assumptions used in gravity field determination from GRACE data.
In this context, this study investigates the computation of dynamic orbits from GRACE accelerometer measurements and background models, which are used at multiple steps in gravity recovery. They are, for example, used in computing linearised observation equations for the low-low satellite-to-satellite tracking instruments, or to evaluate potential models like static fields or dealiasing products. It is thus desirable for the precision at which the dynamic orbits are determined to surpass the precision of the ranging observations.

We computed dynamic orbits for GRACE, both in a simple simulation and for real observational data. We observed the differences between successive iterations of orbit determination and used these as a benchmark for the quality of the orbit solution. We implemented a numerically stable orbit determination algorithm employing Encke's method, in which we use a novel reference trajectory determined through rigorous optimization. This reference trajectory was parameterised and computed using equinoctial elements to minimize orbit errors resulting from imprecision in the reference motion. We present the effects of these two optimizations on the dynamic orbits, and show that the resulting orbits are self-consistent to below the expected precision of the GRACE Follow-On ranging instruments.
Original languageEnglish
Publication statusPublished - 12 Dec 2016
Event2016 AGU Fall Meeting - San Francisco, United States
Duration: 12 Dec 201616 Dec 2016

Conference

Conference2016 AGU Fall Meeting
CountryUnited States
CitySan Francisco
Period12/12/1616/12/16

Fingerprint

gravimetry
orbits
orbit determination
gravitation
Encke method
satellite-to-satellite tracking
GRACE mission
trajectories
static models
optimization
accelerometers
iteration
recovery
evaluation
products

Keywords

  • GRACE
  • Dynamic orbit

Cite this

Ellmer, M., & Mayer-Gürr, T. (2016). High-precision dynamic orbit integration for spaceborne gravimetry. Poster session presented at 2016 AGU Fall Meeting, San Francisco, United States.

High-precision dynamic orbit integration for spaceborne gravimetry. / Ellmer, Matthias; Mayer-Gürr, Torsten.

2016. Poster session presented at 2016 AGU Fall Meeting, San Francisco, United States.

Research output: Contribution to conferencePosterResearch

Ellmer, M & Mayer-Gürr, T 2016, 'High-precision dynamic orbit integration for spaceborne gravimetry' 2016 AGU Fall Meeting, San Francisco, United States, 12/12/16 - 16/12/16, .
Ellmer M, Mayer-Gürr T. High-precision dynamic orbit integration for spaceborne gravimetry. 2016. Poster session presented at 2016 AGU Fall Meeting, San Francisco, United States.
Ellmer, Matthias ; Mayer-Gürr, Torsten. / High-precision dynamic orbit integration for spaceborne gravimetry. Poster session presented at 2016 AGU Fall Meeting, San Francisco, United States.
@conference{f5539b662dea43a590bce2f5d7775f6d,
title = "High-precision dynamic orbit integration for spaceborne gravimetry",
abstract = "Future gravity missions like GRACE Follow-On and beyond will deliver low-low satellite-to-satellite ranging measurements of much increased precision. To prepare for the new challenges and opportunities involved in processing this new data, it is necessary to perform a systematic review and re-evaluation of current algorithms and assumptions used in gravity field determination from GRACE data.In this context, this study investigates the computation of dynamic orbits from GRACE accelerometer measurements and background models, which are used at multiple steps in gravity recovery. They are, for example, used in computing linearised observation equations for the low-low satellite-to-satellite tracking instruments, or to evaluate potential models like static fields or dealiasing products. It is thus desirable for the precision at which the dynamic orbits are determined to surpass the precision of the ranging observations.We computed dynamic orbits for GRACE, both in a simple simulation and for real observational data. We observed the differences between successive iterations of orbit determination and used these as a benchmark for the quality of the orbit solution. We implemented a numerically stable orbit determination algorithm employing Encke's method, in which we use a novel reference trajectory determined through rigorous optimization. This reference trajectory was parameterised and computed using equinoctial elements to minimize orbit errors resulting from imprecision in the reference motion. We present the effects of these two optimizations on the dynamic orbits, and show that the resulting orbits are self-consistent to below the expected precision of the GRACE Follow-On ranging instruments.",
keywords = "GRACE, Dynamic orbit",
author = "Matthias Ellmer and Torsten Mayer-G{\"u}rr",
year = "2016",
month = "12",
day = "12",
language = "English",
note = "2016 AGU Fall Meeting ; Conference date: 12-12-2016 Through 16-12-2016",

}

TY - CONF

T1 - High-precision dynamic orbit integration for spaceborne gravimetry

AU - Ellmer, Matthias

AU - Mayer-Gürr, Torsten

PY - 2016/12/12

Y1 - 2016/12/12

N2 - Future gravity missions like GRACE Follow-On and beyond will deliver low-low satellite-to-satellite ranging measurements of much increased precision. To prepare for the new challenges and opportunities involved in processing this new data, it is necessary to perform a systematic review and re-evaluation of current algorithms and assumptions used in gravity field determination from GRACE data.In this context, this study investigates the computation of dynamic orbits from GRACE accelerometer measurements and background models, which are used at multiple steps in gravity recovery. They are, for example, used in computing linearised observation equations for the low-low satellite-to-satellite tracking instruments, or to evaluate potential models like static fields or dealiasing products. It is thus desirable for the precision at which the dynamic orbits are determined to surpass the precision of the ranging observations.We computed dynamic orbits for GRACE, both in a simple simulation and for real observational data. We observed the differences between successive iterations of orbit determination and used these as a benchmark for the quality of the orbit solution. We implemented a numerically stable orbit determination algorithm employing Encke's method, in which we use a novel reference trajectory determined through rigorous optimization. This reference trajectory was parameterised and computed using equinoctial elements to minimize orbit errors resulting from imprecision in the reference motion. We present the effects of these two optimizations on the dynamic orbits, and show that the resulting orbits are self-consistent to below the expected precision of the GRACE Follow-On ranging instruments.

AB - Future gravity missions like GRACE Follow-On and beyond will deliver low-low satellite-to-satellite ranging measurements of much increased precision. To prepare for the new challenges and opportunities involved in processing this new data, it is necessary to perform a systematic review and re-evaluation of current algorithms and assumptions used in gravity field determination from GRACE data.In this context, this study investigates the computation of dynamic orbits from GRACE accelerometer measurements and background models, which are used at multiple steps in gravity recovery. They are, for example, used in computing linearised observation equations for the low-low satellite-to-satellite tracking instruments, or to evaluate potential models like static fields or dealiasing products. It is thus desirable for the precision at which the dynamic orbits are determined to surpass the precision of the ranging observations.We computed dynamic orbits for GRACE, both in a simple simulation and for real observational data. We observed the differences between successive iterations of orbit determination and used these as a benchmark for the quality of the orbit solution. We implemented a numerically stable orbit determination algorithm employing Encke's method, in which we use a novel reference trajectory determined through rigorous optimization. This reference trajectory was parameterised and computed using equinoctial elements to minimize orbit errors resulting from imprecision in the reference motion. We present the effects of these two optimizations on the dynamic orbits, and show that the resulting orbits are self-consistent to below the expected precision of the GRACE Follow-On ranging instruments.

KW - GRACE

KW - Dynamic orbit

UR - https://agu.confex.com/agu/fm16/meetingapp.cgi/Paper/124861

M3 - Poster

ER -