B. Loomis, D. Wiese, R. S. Nerem (1) P. L. Bender (2) P. N. A. M. Visser (3)
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1 Possible mission architectures for a GRACE follow-on mission including a study on upgraded instrumentation suites, and multiple satellite pairs in moderately-inclined orbits B. Loomis, D. Wiese, R. S. Nerem (1) P. L. Bender (2) P. N. A. M. Visser (3) (1) Colorado Center for Astrodynamics Research, Dept. of Aerospace Engineering Sciences, Univ. of Colorado, Boulder, CO (2) JILA, Univ. of Colorado and Nat. Inst. Of Standards & Technology, Boulder, CO (3) Delft Institute of Earth Observation and Space Systems (DEOS), Delft University of Technology, Delft, The Netherlands
2 2 Presentation outline Limitations of GRACE Simulation procedure GRACE Follow-On with upgraded technologies GRACE Follow-On with multiple satellite pairs Future work
3 3 Limitations of GRACE Instrument errors Satellite-to-satellite ranging Accelerometers Orbital altitude Temporal aliasing Caused by under-sampling of the highfrequency changes in the gravity field GFO with upgraded technologies Force model errors Ocean and solid Earth tides Atmospheric and non-tidal mass variations GFO with multiple satellite pairs
4 4 Simulation procedure Goal: recover time-variable hydrological and ice mass variations in the presence of instrument and temporal aliasing errors Simulated error sources Satellite-to-satellite range-rate errors Removal of non-conservative forces Satellite positioning errors Imperfections in geophysical models (AOD & tides)
5 5 GFO with upgraded technologies Interferometric laser ranging system Replaces the K-band microwave ranging system Reduces error RMS from ~0.2 μ/s to ~0.6 nm/s Gravitational reference sensor (GRS) Proof mass isolated within the body of the spacecraft Micro-thrusting is used to maintain the position of satellite with respect to the proof mass resulting in a drag-free system Reduces errors associated with on-board accelerometers Reduction in orbital altitude Lower altitude satellites are more sensitive to higher spatial resolution features of gravity field Would need to be accompanied by GRS to maintain orbital altitude
6 6 GFO with upgraded technologies Four different missions are simulated: GRACE and three possible GFO configurations Mission Altitude / satellite separation Range-rate noise Removal of nonconservative forces GRACE 480 km / 220 km K-band Accelerometer GFO Case km / 220 km Laser Accelerometer GFO Case km / 50 km K-band GRS (drag-free) GFO Case km / 50 km Laser GRS (drag-free) GFO Case 3 is best-case scenario GFO Case 1 and Case 2 are hybrid missions Simulations estimate monthly regional mascon gravity estimates for South America and Greenland
7 7 GFO with upgraded technologies Error RMS of monthly South America maps Error RMS of monthly Greenland maps
8 8 GFO with upgraded technologies Spatial resolution study GRACE GFO Case 1 Total mass recovered GFO Case 2 GFO Case 3
9 9 GFO with multiple satellite pairs Reducing temporal aliasing errors Improving atmosphere, ocean, and tide models Co-estimating parameters (i.e. tidal coefficients) Multiple satellite pairs
10 10 GFO with multiple satellite pairs Multiple satellite pair configurations Lower inclined satellite pair Repeat Period (revs/sidereal days) Altitude (km) Inclination (deg) 360/ / / Polar satellite pair Repeat Period Altitude Inclination (revs/ sidereal days) (km) (deg) 79/ Compare these to a single pair of polar satellites Repeat Period (revs/ sidereal days) Altitude (km) Inclination (deg) 363/ / /
11 11 GFO with multiple satellite pairs Simulation setup Satellites have laser interferometer and fly drag-free AOD and tidal errors are included Length of simulations: 10, 15, and 23 days Spherical harmonics solved to degree and order 60 Low degree and order gravity fields can be estimated daily to correct the final multi-day solution (reduces the effect of temporal aliasing errors)
12 12 Results: plots in cm of water Truth Single polar pair (15 day) Single polar pair (15 day), estimate q daily 10x10 g ( ) fields Truth Multiple pairs ( day) Multiple pairs ( day), estimateq daily 20x20 g ( ) field
13 13 GFO with multiple satellite pairs Comparison of performance for different configurations Mission configuration Single Polar Pair (estimating daily 10x10 fields) Hydrology error RMS (cm of water) Ice mass error RMS (cm of water) 10 day day day Multiple Pairs (estimating daily 20x20 fields) 10 day + 5 day day + 5 day day + 5 day
14 14 Future work Increase fidelity of simulations to higher degree and order Further examine post-processing techniques such as Gaussian smoothing and de-striping Design more configurations and perform trade studies (different repeat periods, inclinations, formation types) Possible application of a global mascon estimation technique to achieve optimal solution with use of spatial constraints
15 15 Acknowledgements This research was funded by the following grants: NASA Earth System Science Fellowship National Science Foundation Graduate Fellowship National Defense Science and Engineering Graduate Fellowship Additional thanks to: NASA Goddard Space Flight Center for providing GEODYN orbit determination software and various models ESA Mass Study Transport Team, ESA contract number 20403
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