GRACE accelerometer calibration by high precision non-gravitational force modeling

Wöske, Florian; Kato, Takahiro A.; Rievers, Benny; List, Meike

doi:10.1016/j.asr.2018.10.025

Cited by 25 publications

(23 citation statements)

References 15 publications

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“…For GRACE, we refer to Bettadpur (2012). While very recent studies Wöske et al 2019) consider finite element models, here we use the eight-panel model from Bettadpur (2012). Errors in these models are usually not specified, even though they would be helpful for developing a realistic error budget.…”

Section: Solar Radiation Pressurementioning

confidence: 99%

“…Integrating over all wavelengths of the spectrum yields the total solar irradiance of approximately 1362 W/m 2 (Dewitte and Clerbaux 2017) and 1360.5 W/m 2 during the solar minimum in 2008 (Kopp and Lean 2011), respectively. SPR models commonly use visible wavelengths only (e.g., Sutton et al 2007;Cerri et al 2010;Doornbos 2012;Wöske et al 2019) as input, which is-at least for GNSS satellites-due to the lack of thermal material properties (e.g., Ziebart 2004;Hackel et al 2017). When the material properties given are in the visible and infrared domain, we can discretize the λintegration in Eq.…”

Section: Solar Radiation Pressurementioning

confidence: 99%

“…Additionally, some models account for thermal reradiation of the satellite by considering a simple static temperature model (Fliegel et al 1992;Montenbruck et al 2015) or by using an advanced model accounting for transient heating and heat conduction (Wöske et al 2019). Anisotropic or delayed thermal reradiation including the possibly rerouted heat generated by the satellite's electrical components (Rievers et al 2010) may be relevant, but cannot be considered here.…”

Section: Solar Radiation Pressurementioning

confidence: 99%

“…But both orbiters had a complex shape as compared to GRACE, and SRP plays a much larger role in the lunar and Mars force models. Self-shadowing of the GRACE satellites has been considered in Wöske et al (2019) but was found to cause a very small effect. Therefore, we ignore the selfshadowing of both solar and Earth radiation in this study; however, the influence of self-shadowing and multiple reflections has to be reviewed when transferring the model to other spacecraft as considered, e.g., in List et al (2015).…”

Section: Solar Radiation Pressurementioning

confidence: 99%

“…Other recent publications assume a grid of 2.5 • in longitude and latitude (Rodríguez-Solano et al 2012). In this paper, the FOV is discretized with a grid of 1 • in longitude and latitude as, e.g., in Visser et al (2019); Wöske et al (2019). Currently, a grid of 1 • appears sufficient, since this corresponds to the spatial resolution of the Earth's outgoing radiation data.…”

Section: Earth Radiation Pressurementioning

confidence: 99%

See 4 more Smart Citations

Extended forward and inverse modeling of radiation pressure accelerations for LEO satellites

Vielberg

Kusche

2020

J Geod

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For low Earth orbit (LEO) satellites, activities such as precise orbit determination, gravity field retrieval, and thermospheric density estimation from accelerometry require modeled accelerations due to radiation pressure. To overcome inconsistencies and better understand the propagation of modeling errors into estimates, we here suggest to extend the standard analytical LEO radiation pressure model with emphasis on removing systematic errors in time-dependent radiation data products for the Sun and the Earth. Our extended unified model of Earth radiation pressure accelerations is based on hourly CERES SYN1deg data of the Earth's outgoing radiation combined with angular distribution models. We apply this approach to the GRACE (Gravity Recovery and Climate Experiment) data. Validations with 1 year of calibrated accelerometer measurements suggest that the proposed model extension reduces RMS fits between 5 and 27%, depending on how measurements were calibrated. In contrast, we find little changes when implementing, e.g., thermal reradiation or anisotropic reflection at the satellite's surface. The refined model can be adopted to any satellite, but insufficient knowledge of geometry and in particular surface properties remains a limitation. In an inverse approach, we therefore parametrize various combinations of possible systematic errors to investigate estimability and understand correlations of remaining inconsistencies. Using GRACE-A accelerometry data, we solve for corrections of material coefficients and CERES fluxes separately over ocean and land. These results are encouraging and suggest that certain physical radiation pressure model parameters could indeed be determined from satellite accelerometry data.

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Section: Solar Radiation Pressurementioning

confidence: 99%

Section: Solar Radiation Pressurementioning

confidence: 99%

Section: Solar Radiation Pressurementioning

confidence: 99%

Section: Solar Radiation Pressurementioning

confidence: 99%

Section: Earth Radiation Pressurementioning

confidence: 99%

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Extended forward and inverse modeling of radiation pressure accelerations for LEO satellites

Vielberg

Kusche

2020

J Geod

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Upper-atmosphere mass density variations from CASSIOPE precise orbits

Calabia

Jin

2020

Preprint

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Low Earth Orbit (LEO) satellites are significantly affected by variable air drag forces, which are mainly altered by atmospheric expansion/contraction driven by solar and geomagnetic activity. Air drag reduces the orbital velocity of a satellite, its nominal altitude, and shortens its lifespan. The effect of air drag pressure on the position of a satellite orbiting at an altitude of around 450 km may drag around 3 m per revolution in the along-track axis, limiting the satellite's lifespan to approximately 5-10 years. In applications, such as remote sensing or satellite altimetry and gravity, the orbital trajectory and velocity (ephemeris) of satellites must be known to an accuracy of a few millimeters. Moreover, the exponential increase in presence of space debris (consider the recent destructive events of Fengyun-1C, Iridium, and Mission Shakti) has highlighted the importance of orbital tracking and prediction of potential collisions. The dynamic Precise Orbit Determination (POD) method tracks and predicts the orbital ephemeris by calculating an orbital trajectory through a double integration and linearization of Newton-Euler's equation of motion (Montenbruck & Gill, 2013). In the POD method, by combining force models with empirical observations, used for example in laser-ranging, Doppler, accelerometer, or Global Navigation Satellite System (GNSS) measurements, the position, and velocity of a satellite can be stochastically estimated with significant accuracy (Jin & Su, 2020;Tapley et al., 2004).Due to variable air drag force being so important, in the last decade, thermospheric mass density (TMD) variations driven by solar and geomagnetic activity have been investigated using satellite technology to a great extent (e.g.

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Kalman-Filter Based Hybridization of Classic and Cold Atom Interferometry Accelerometers for Future Satellite Gravity Missions

HosseiniArani

Tennstedt

Schilling

et al. 2022

International Association of Geodesy Symposia

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Proof-of-principle demonstrations have been made for cold atom interferometer (CAI) sensors. Using CAI-based accelerometers in the next generation of satellite gravimetry missions can provide long-term stability and precise measurements of the non-gravitational forces acting on the satellites. This would allow a better understanding of climate change processes and geophysical phenomena which require long-term monitoring of mass variations with sufficient spatial and temporal resolution. The proposed accuracy and long-term stability of CAI-based accelerometers appear promising, while there are some major drawbacks in the long dead times and the comparatively small dynamic range of the sensors. One interesting way to handle these limitations is to use a hybridization with a conventional navigation sensor. This study discusses one possible solution to employ measurements of a CAI accelerometer together with a conventional Inertial Measurement Unit (IMU) using a Kalman filter framework.A hybrid navigation solution of these two sensors for applications on ground has already been demonstrated in simulations. Here, we adapt this method to a space-based GRACE-like gravimetry mission. A simulation is performed, where the sensitivity of the CAI accelerometer is estimated based on state-of-the-art ground sensors and further published space scenarios. Our results show that the Kalman filter framework can be used to combine the measurements of conventional inertial measurement units with the CAI accelerometers measurements in a way to benefit from the high accuracy of the conventional IMU measurements in higher frequencies together with the high stability of CAI measurements in lower frequencies. We will discuss the challenges, potential solutions, and the possible performance limits of the proposed hybrid accelerometry scenario.

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GRACE accelerometer calibration by high precision non-gravitational force modeling

Cited by 25 publications

References 15 publications

Extended forward and inverse modeling of radiation pressure accelerations for LEO satellites

Extended forward and inverse modeling of radiation pressure accelerations for LEO satellites

Upper-atmosphere mass density variations from CASSIOPE precise orbits

Kalman-Filter Based Hybridization of Classic and Cold Atom Interferometry Accelerometers for Future Satellite Gravity Missions

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