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Improving the estimation of thermospheric neutral density via twostep assimilation of in situ neutral density into a numerical model
Earth, Planets and Space volume 74, Article number: 183 (2022)
Abstract
Neutral thermospheric density is an essential quantity required for precise orbit determination of satellites, collision avoidance of satellites, reentry prediction of satellites or space debris, and satellite lifetime assessments. Empirical models of the thermosphere fail to provide sufficient estimates of neutral thermospheric density along the orbits of satellites by reason of approximations, assumptions and a limited temporal resolution. At high solar activity these estimates can be off by 70% when comparing to observations at 12hourly averages. In recent decades, neutral density is regularly observed with satellite accelerometers on board of low Earth orbiting satellites like CHAMP, GOCE, GRACE, GRACEFO, or Swarm. When assimilating such alongtrack information into global models of thermosphere–ionosphere dynamics, it has been often observed that only a very local subdomain of the model grid around the satellite’s position is updated. To extend the impact to the entire model domain we suggest a new twostep approach: we use accelerometerderived neutral densities from the CHAMP mission in a first step to calibrate an empirical thermosphere density model (NRLMSIS 2.0). In a second step, we assimilate—for the first time—densities predicted for a regular threedimensional grid into the TIEGCM (Thermosphere Ionosphere Electrodynamics General Circulation Model). Data assimilation is performed using the Local ErrorSubspace Transform Kalman Filter provided by the Parallel Data Assimilation Framework (PDAF). We test the new approach using a 2weeklong period containing the 5 April 2010 Geomagnetic storm. Accelerometerderived neutral densities from the GRACE mission are used for additional evaluation. We demonstrate that the twostep approach globally improves the simulation of thermospheric density. We could significantly improve the density prediction for CHAMP and GRACE. In fact, the offset between the accelerometerderived densities and the model prediction is reduced by 45% for CHAMP and 20% for GRACE when applying the twostep approach. The implication is that our approach allows one to much better ’transplant’ the precise CHAMP thermospheric density measurements to satellites flying at a similar altitude.
Graphical Abstract
Background
Neutral thermospheric density plays an important role when computing the atmospheric drag acceleration acting on satellites (e.g., Vallado and Finkleman 2014). Applications in need for accurate drag estimates are precise orbit determination (e.g., Montenbruck and Gill 2005; Longuski et al. 2022), the forecasting of orbit decay or mission life time (e.g., Walterscheid 1989), and predicting the reentry of satellites or space debris and identifying locations on Earth that might be endangered by this (e.g., Klinkrad et al. 2006). Especially, satellites flying below 1000 km are affected by atmospheric drag that is the largest nongravitational acceleration at those altitudes.
One can determine the neutral density with different methods (Emmert 2015). In situ measurements are conducted with mass spectrometers or accelerometers mounted on satellites. However, there are only a few satellites equipped with such instruments. It is also possible to estimate time averaged neutral densities from observed satellite orbits. The advantage of this method is that it can be applied to any passive satellite, but it is less accurate when relying on two line elements (TLE) tracking. In case of active satellites—for example, satellites equipped with retro reflectors for satellite laser ranging—the time averaged neutral density can be determined within precise orbit determination with higher precision than using TLE.
Another approach is the use of thermospheric density models. In fact, several numerical and empirical models were developed over the last seven decades (e.g., Doornbos (2012, Table 2.1) and Vallado and Finkleman (2014, Figure 3)). Empirical density models are constructed from observations that are fitted to mathematical equations. This is in particular critical for the effect of solar and geomagnetic forcing on density, since the underlying physics including Joule heating, photochemistry, and particle precipitation is partly not understood owing to a lack of data, and partly too complex for these simple equations. Empirical density models represent the average state of the atmosphere (e.g., Emmert 2015). Examples for empirical models are the Jacchia–Bowman (JB, Bowman et al. 2008) model, Naval Research Laboratory Mass Spectrometer and Incoherent Scatter radar (NRLMSIS 2.0, Emmert 2021) model, and Drag Temperature Model (DTM, Bruinsma and Boniface 2021).
Numerical models propagate an initial state using physical laws and principles, for instance, heat and momentum balance, electromagnetism and chemical reactions. Typically, this is done by solving a set of (partial) differential equations on a grid. Examples for numerical models are the National Center for Atmospheric Research Thermosphere Ionosphere Electrodynamics General Circulation Model (NCAR TIEGCM, Qian et al. 2014), NCAR Whole Atmosphere Community Climate Model (WACCMX, Liu et al. 2018), and Global Ionosphere–Thermosphere Model (GITM, Ridley et al. 2006).
There are significant discrepancies between different models, and between models and observations (e.g., Gaposchkin and Coster 1990; Bruinsma et al. 2012, 2014; He et al. 2018; Panzetta et al. 2019). Hence, there is an ongoing effort in improving the models. In this paper, we present a new experimental approach for that purpose.
While numerical models provide physically consistent solutions, they do not exhibit improved skills in neutral density simulation when compared to empirical models (e.g., Emmert 2015). A common approach to nudge numerical model simulations closer to reality is merging them with observations via data assimilation.
In a coupled model, like the TIEGCM, assimilating quantities associated with a compartment also affects the other compartments. One can assimilate observations of the electron density to improve the representation of the neutral mass density. For example, the total electron content, an integrated measure of electrons along a path through the atmosphere, could be used for that. Although we only assimilate neutral mass densities here, our assimilative version of the TIEGCM can be easily modified to assimilate other quantities.
The in situ measurements of a single satellite mission only intersect with a small subset of the model grid cells. This means, compared with models the in situ measurements of a single satellite are very sparse. The farther an observation is away from a grid cell, the less information is provided by it for that cell. For instance, a measurement of the neutral density on the day side provides little information about the density on the night side. Thus, assimilating such alongtrack data should only affect grid cells in the vicinity of the satellite’s orbit. Matsuo et al. (2013) have assimilated neutral densities derived form the CHAMP (Reigber et al. 2002) accelerometer into the TIEGCM. The model densities were only improved in the vicinity of the satellite’s orbit. But they achieved global improvements by co estimation of model drivers.
Besides co estimating parameters for the model drivers, one could also assimilate data of many sources at different locations simultaneously for global model improvements. In this study we test another approach that consists of two steps and is illustrated in Fig. 1. We use the alongtrack densities derived from the CHAMP accelerometer to calibrate an empirical model (the NRLMSIS 2.0). The calibrated empirical model is viewed here as a combination of the data used to build the empirical model itself and the densities derived from the CHAMP accelerometer, with more weight given to the CHAMP observations. For the calibration we evaluate the empirical model along the CHAMP orbit and scale the observed densities by the modeled densities to derive scale factors. We also apply a low pass filter to the scale factors. The calibrated model is the output of the original model multiplied with the corresponding scale factor. In the first step, we evaluate the calibrated empirical model on a regular threedimensional grid. We call it the data grid. In the second step, we assimilated the data located on the data grid into the TIEGCM that is located on what we call the state grid.
Data assimilation of various observations types has already been applied to different models of the upper atmosphere in several studies: Solomentsev et al. (2012) have assimilated simulated GPS observations into a numerical model of the ionosphere using the Ensemble Square Root Filter. The aim was assessing the state estimation of the ionosphere and improving the estimation of model drivers. Observations from GPS Occultation have been assimilated by Lee et al. (2012) into the TIEGCM using the Ensemble Kalman filter under geomagnetic quiet conditions. They aimed at improving the global ionospheric electron density specification. Matsuo et al. (2013) have assimilated CHAMP observations and GPS Occultation measurements into the TIEGCM using the Ensemble Kalman filter. They found that assimilation of accelerometerderived densities only improves the model densities in the vicinity of the satellite’s orbit. But they also demonstrated that co estimating the F10.7 parameter together with accelerometerderived densities impacts the global model. In the study of Morozov et al. (2013) the ensemble adjustment Kalman filter is used to assimilate CHAMP observations into the Global Ionosphere–Thermosphere Model during a geomagnetically calm period. They estimate the F10.7 index in a way it has a constant variance. They could reduce the model bias along the CHAMP and GRACE orbits. Codrescu et al. (2018) have assimilated neutral densities derived from accelerometers on board of the CHAMP mission into the CTIPe model during quiet conditions at solar minimum using the Ensemble Kalman Filter. The model results were improved when comparing to CHAMP and GRACE observations. Forootan (2022) have applied a calibration and data assimilation technique to the empirical NRLMSISE00 model using observations from the GRACE accelerometer.
In contrast to the existing approaches, the twostep approach enables us to assimilate globally distributed neutral densities that are derived from satellite accelerometers and an empirical model, which is also build from many observations.
Methods
Data assimilation
Data assimilation (e.g., Lahoz et al. 2010) combines the state estimation of a model with observations taking into account the uncertainty of both to get an estimate of the state with higher accuracy. There are many different data assimilation approaches. For highly nonlinear problems, like atmosphere models, ensemble Kalman filters (e.g., VetraCarvalho et al. 2018) are frequently employed. By implicitly representing the variance–covariance matrix of the model state by an ensemble of states, ensemble filters are very efficient in terms of computational cost and computer memory requirements and can be easily integrated into the model code. These filters utilize a sequence of forecast and analysis steps. The forecast step uses the model to predict the observations. At the subsequent analysis step the state of the model is fitted so that it minimizes the distance to the forecasted observations and the actual observations w.r.t. the associated variance–covariance matrices.
The Parallel Data Assimilation Framework (Nerger et al. 2020) developed at the Alfred Wegener Institute Bremerhaven is opensource software for ensemblebased data assimilation. It is designed for large scale numerical models and allows the application of different filter algorithms. Moreover, it enables parallel computation of all ensemble members, which in turn can also be calculated in parallel if supported by the model. Both, the TIEGCM and PDAF are written in Fortran which simplifies the implementation. In this study, we use the localized (Nerger et al. 2006) errorsubspace transform Kalman filter (Nerger et al. 2012b, ESTKF).
The original ensemble Kalman filter (Evensen 1994, EnkF) formulation is typically expanded with perturbed observations to account for an underestimation of the analysis error covariance that leads to a too small ensemble spread after the analysis step (Burgers et al. 1998; Houtekamer and Mitchell 1998). The perturbed observations are an additional source for sampling errors (Whitaker and Hamill 2002), which are avoided by a class of filters using a deterministic transformation from the forecast ensemble to the analysis ensemble (e.g., Tippett et al. 2003). We choose The ESTKF since it belongs to this class and is formulated in an efficient way (Nerger et al. 2012b).
Determining neutral densities from spaceborne accelerometers
Given the atmospheric drag acting on a satellite, together with a model describing the shape and material of the satellite one can derive the neutral mass density at the satellite’s position (e.g., Doornbos 2012, p.91). Accelerometers onboard satellites measure the superposition of all nonconservative accelerations acting on the satellite. To isolate the atmospheric drag acceleration from the measurements, one needs to carefully model all other nonconservative forces and remove their effect. In practice, one needs to simulate the acceleration caused by thermal reradiation, solar radiation pressure and Earth radiation pressure, and remove it from the the measured accelerations. For this study, we use the neutral mass densities derived from the accelerometers on board of the CHAMP (Reigber et al. 2002) and GRACE (Tapley et al. 2007) mission using the approach described in Vielberg et al. (2018); Vielberg and Kusche (2020). Further information can be found at Vielberg (2021).
Neutral density models used in this study
The NCAR Thermosphere Ionosphere Electrodynamics General Circulation Model (TIEGCM, Qian et al. 2014), represents a global, numerical model of the upper atmosphere. The TIEGCM ranges from approximately 97 km to 500 km altitude. The upper boundary is not fixed in geometric height coordinates, since the TIEGCM uses pressure levels as vertical coordinate. For this study we use the latest version of the TIEGCM (version 2.0). An important proxy driver for the TIEGCM is the F10.7 index (e.g., Tapping 2013) that is used to compute the extreme ultraviolet (EUV) radiation, based on the model of Richards et al. (1994). The TIEGCM includes two alternative empirical highlatitude potential models computing ionospheric convection: the Heelis model (Heelis et al. 1982) and the Weimer model (Weimer 2005). The first requires the three hourly Kp index (e.g., Matzka et al. 2021), whereas the second uses solar wind and interplanetary magnetic field parameters provided by the OMNI Dataset with one minute temporal resolution (Papitashvili and King 2020).
The Naval Research Laboratory Mass Spectrometer Incoherent Scatter radar 2.0 (NRLMSIS 2.0, Emmert 2021) model is a global, empirical model of the atmosphere. It takes location, time, geomagnetic activity represented by the Kp index, and solar activity represented by the F10.7 index as input. It computes the neutral composition, density, and temperature. Since it is derived from various observations at different periods and locations the results represent the averaged observed state of the atmosphere for the given inputs. The model extends from the ground to the exobase.
Period for experiments
The period of the assimilation experiment is restricted by three factors: first, it must contain measurements of the CHAMP and GRACE missions. That is, the period must be between 2002 and 2010. Second, the period must contain at least one strong storm (Kp \(\ge 7\)), but also quiet condition, so we can evaluate the assimilation framework for different geomagnetic activity. Finally, the duration is restricted by the computing time. A 2weeklong period is processed on our hardware (400 cores distributed over 25 Intel(R) Xeon(R) Gold 6130 processors) in about four hours and 20 min. This allows us to test different settings in a reasonable amount of time. We choose the period from 27 Mar 2010 00:00 UTC+0 till 10 April 2010 00:00 UTC+0, that satisfies all three conditions. In Fig. 2, the solar and geomagnetic activity during the experiments is illustrated. On April 5, 2010, an interplanetary coronal mass ejection reached Earth around 8:27h UTC+0 and triggered a geomagnetic storm (Lu et al. 2014; Sheng et al. 2017). The mean altitudes of the CHAMP and GRACE satellite during the experiment are 302 km and 474 km, respectively.
Calibration of NRLMSIS 2.0
The majority of the observations used to estimate the NRLMSIS 2.0 parameters are between the ground and 105 km altitude (Emmert 2021, Table 1). Above this altitude only density observations derived from two line elements were used along with synthetic observations from the preceding model NRLMSISE00. Since, the TIEGCM starts at approximately 97 km altitude it does not intersect with most of the observations used for building the NRLMSIS 2.0. Moreover, empirical models return average states of the atmosphere. Thus, we calibrate the model to perform better at the altitudes covered by the TIEGCM.
We calibrate the NRLMSIS 2.0 by scaling it with time dependent factors. The scale factor is thus defined as the quotient of the density derived from the CHAMP accelerometer \(\rho _\text {CHAMP}\) and the density \(\rho _\text {NRLMSIS 2.0}\) predicted by the NRLMSIS 2.0 for the corresponding location and time (see also Zeitler et al. 2021, Eq. 10):
In Fig. 3, the scale factors for the duration of the experiment are plotted. During and after the strong storm (starting at 5th April), the scale factors are much larger compared to the rest of the period (Fig. 3 a and c). Within each orbit, the scale factors vary according to latitude and whether the satellite is on the day or night side (Fig. 3 b). For example, on the night side equator (argument of latitude is zero) the scale factors are systematically larger than on the day side equator (argument of latitude is 180\(^{\circ }\)). The median scale factor on the night side is about 16% larger than the median on the day side.
As shown, the scale factor depends on the horizontal location. However, for each epoch, we can only derive the scale factor at one location if we use only one satellite. That is, the scale factor is expected to work best for locations near the CHAMP satellite.
Thus, we decided to filter out the orbital signal in the scale factor time series. We found that a cutoff frequency of three hours, which approximately corresponds to two revolutions of the CHAMP satellite, eliminates this signal (see Fig. 3 d and e). That is, the variability between day and night side within an orbit vanishes in the filtered scale factor time series. The three hourly filtered scale factor is an average value that can be applied to the whole model, at the cost of signal loss (compare Fig. 3 a and d). Consequently, the cutoff frequency also limits the duration between subsequent analysis steps.
As shown in Zeitler et al. (2021), half daily scale factors derived at different heights are highly correlated. For CHAMP and GRACE the correlation is 89%. Thus, when calibrating the NRLMSIS 2.0 with observations from the CHAMP mission, we expect that the calibrated model also fits better to the densities derived from the GRACE accelerometer.
Spatial resolution of the data grid
We choose the horizontal resolution of the data grid, so that it reflects the resolution of the NRLMSIS 2.0. The NRLMSIS 2.0 uses spherical harmonics up to degree six to expand the model parameters to the global atmosphere (Hedin (1987, Equation A22) and Emmert et al. (2021, Section2.4)). That is, the NRLMSIS 2.0 cannot resolve signals with wavelength smaller than \(\frac{360^{\circ }}{6} = 60^{\circ }\) arc length. To sample these signals, one needs at least half the wavelength. Here, we choose a third with gives 20\(^{\circ }\) for the horizontal resolution of the data grid. Using a finer grid would increase the number of observations and slow down the assimilation while the gain in information is limited. The data grid starts at 100 km and ends at 550 km covering most of the state grid. The vertical resolution is 25 km. This value corresponds approximately to the number density scale height at 200 km altitude.
Setup for TIEGCM
We use the latest version of the TIEGCM (version 2.0). The TIEGCM either runs with 5.0\(^{\circ }\) or 2.5\(^{\circ }\) horizontal resolution. For this study, we use the coarser five degree resolution since it runs about ten times faster and requires one eighth of the disk space to store the results at the same temporal resolution. The step size—the time between subsequent model states—is 15 seconds. We found it difficult to use longer values as this caused some ensemble members to crash. We do not save every model step, since it would require too much memory: Saving the ensemble mean of the neutral density at the state grid at each model step for a 2weeklong period using single precision requires approximately 24 GB. But we also need to save the data at the data grid and the corresponding standard deviations. If one also stores the results of each ensemble member the storage requirements increase accordingly. Thus, we save the results every ten minutes.
The TIEGCM requires lower boundary constraints for neutral temperature, horizontal neutral wind, and geopotential altitude. By default a ’flat’ lower boundary is assumed. That is, there is no wind, the neutral temperature is 181 K, and the geopotential height is 96.4 km. Alternatively, one can use zonal monthly mean climatologies to specify the lower boundaries. This feature is based on the work of Jones et al. (2014). The TIEGCM comes with a file containing zonal climatologies derived from the NRLMSISE00 (Picone et al. 2002) and the Horizontal Wind Model (HWM07, Drob et al. 2008). To use it with the five degree grid one has to interpolate, since it is only given for the 2.5 degree grid. Regardless which method is chosen to specify the lower boundary, we additionally add tidal perturbations derived from the Global Scale Wave Model 2002 (GSWM02 Hagan and Forbes 2002) to it to account for migrating diurnal and semidiurnal tides.
Ensemble generation
We create the ensemble by adding perturbations to the external forcing, lower boundary conditions and some constants to each ensemble member that are sampled from a truncated multivariate normal distribution with zero mean. The truncation of the normal distribution is necessary to prevent model crashes caused by extreme values sampled from the tails of the normal distribution that are invalid or unrealistic. We sample the perturbations once and use the same values for the entire duration of the experiment. For each lower boundary condition, only one value is sampled, which is added to all elements of the corresponding field. We do not consider errors within the field, but a global offset of the lower boundary condition. In Table 1, the parameters of the probability density function are listed.
Since we have no access to the true probability density function of the perturbed parameters, we have to determine it to a certain extend arbitrarily. The standard deviation of the constants that we perturb is assumed to be 10% of the constant itself. Following Tapping (2013) we assume that the standard deviation of the F10.7 index is one solar flux unit for values smaller than 100. When using the Heelis model we perturb hemispheric power and cross tail potential. Since both are computed within the TIEGCM from the Kp index we introduce a correlation of 0.9. If the Weimer model is employed, we perturb the solar wind velocity and density instead. The lower boundary conditions of the TIEGCM are perturbed by diurnal and semidiurnal tides computed by the global scale wave model (GSWM). We decided to approximate the standard deviation of the lower boundary conditions from the GSWM tidal perturbations. We take 10% of the largest absolute tidal perturbation in March.
We use an ensemble with 100 members. The initial value for the assimilation are computed with an openloop simulation, which starts 10 days before the assimilation experiment.
State vector and observation operator
The TIEGCM approximates the state of the atmosphere at an epoch with multiple quantities located on the state grid, given for the current and previous model step. Since TIEGCM computes time derivatives simply via finite differences from the previous and current steps, this can be viewed as equivalent to storing variables and their derivative in the state vector. The neutral mass density can be linked to these fields via the mass fractions w of the modeled species and the neutral temperature T. Thus, in our study the state vector is composed of
O, \(\hbox {O}_{2}\), and He denote atomic oxygen, molecular oxygen and atomic helium, respectively. The quantities evaluated at the previous step are denoted with a prime symbol.
The observation operator H is a composition of the function computing the neutral mass density \(\rho ({\varvec{x}})\) and an interpolation function I() that computes the values at the data grid given values on the state grid:
For each cell of the state grid and each step, we can compute the neutral mass density assuming an ideal gas with
Here, p is the pressure, R denotes the gas constant and \(\overline{M}\) is the mean molar mass
The molar mass of a species is denoted with M, and the mass fraction of molecular Nitrogen is \({w_{{\mathrm{N}}_2}} = 1 w_{\mathrm{O}} {w_{{\mathrm{O}}_2}}  w_{\mathrm{He}}\).
Since the state grid is irregularly spaced in the vertical dimension, we first perform linear interpolation along this axis. Since the neutral mass density decreases almost exponentially with height, we apply the natural logarithm to the neutral densities before performing the vertical interpolation. This ensures small interpolation and especially small extrapolation errors, since on a logarithmic scale the density profiles are almost linear. We then apply the exponential function to the vertically interpolated values to transform the interpolated values back to neutral mass densities. Two more linear interpolations along the horizontal coordinates axes are performed to compute the mass densities on the data grid. If the observations are given exactly at the time of the current step, another interpolation along the time axis is not necessary.
Observations
At each analysis step we assimilate the neutral mass densities from the calibrated NRLMSIS 2.0 located on the data grid into the TIEGCM. These densities are not real observations, but we still use the term ’observation’ here to be consistent with data assimilation terminology. The current implementation only supports uncorrelated observation. Thus, although the observations are highly correlated we cannot account for it by using the full variance–covariance matrix of the observations.
We approximate the standard deviation of the NRLMSIS 2.0 neutral mass density by multiplying the uncalibrated neutral mass density \(\rho\) with a factor \(f_h\) depending on the altitude. The height dependent factor is obtained from the standard deviations provided in (Emmert 2021, Data Set 5) for the epoch 20062013 at 250 km and 400 km altitude. We use linear interpolation to get the standard deviation for arbitrary heights:
We introduce additional weights: \(p_{\text {ga}}(\text {Kp})\), \(p_{\text {dist}}(d)\), and \(p_0\) to account for the geomagnetic activity, the distance to the CHAMP satellite and a constant factor, respectively. The standard deviation is computed with
We use the Kp index as indicator of the geomagnetic activity. For quiet periods (Kp \(< 4\frac{2}{3}\)) the weight is one. For the maximal Kp value of 9, the factor is \(\frac{1}{2}\). The values in between are linearly interpolated. This factor ensures that the NRLMSIS 2.0 observations have a lower weight during storms.
The standard deviation is weighted by the distance between the CHAMP satellite and the center of the corresponding data grid cell. We use two exponential decay functions depending on the spherical distance \(\Delta _\phi\) on the unit sphere and the vertical geocentric distance \(\Delta _h\):
The weighting is controlled by the half life parameters \(\Lambda _\phi\) and \(\Lambda _h\). For the experiments presented in this study \(\Lambda _\phi\) is infinite. That is, the spherical distance has no impact on the weights.
Forecast duration
The forecast duration is the duration between two subsequent analysis steps. We refer to model runs with infinite forecast duration, i.e., runs in which no data are assimilated, as openloop simulations. If the forecast duration is too long, it will resemble the openloop simulation some time before the next analysis step. If it is too short, the model state is mainly constrained by the observations and not the model dynamics. In that case the assimilation is useless since one could use the observations directly. For this consideration also the standard deviation of the observations and the model forecast are important. If the observations have much larger uncertainties than the forecast, the result resembles the openloop simulation and the other way round.
The lower bound of the forecast duration is given by the model step length. The forecast duration should not exceed the cutoff period of the low pass filter applied to the scale factors.
The model step length is 15 seconds and the NRLMSIS 2.0 has been filtered with a three hourly low pass filter. Thus, we choose to perform the analysis step hourly.
Localization
At each analysis step of a global filter, each element of the state vector is updated taking into account all observations, regardless of how far the observations are away from the location of the corresponding element of the state vector. This can be of advantage if there are longrange correlation in the system (e.g., the ocean or the atmosphere). For instance, a single in situ observation within the atmosphere could theoretically improve the state estimate of the whole atmosphere. However, this requires that significant longrange correlations exist and that they are correctly represented by the ensemble. Typically, the random errors in the representation of the covariances are larger than the actual signal for small ensembles (Nerger et al. 2006, p.640). This can lead to spurious correlations (e.g., Hamill et al. 2001) and locally incredible estimates (Nerger et al. 2006, p.640). This problem is addressed by filtering out longrange correlations in the analysis step by applying localization (e.g., Nerger et al. 2012a).
For the ESTKF, domain localization (Nerger et al. 2006) together with an optional observation localization (Hunt et al. 2007) is implemented within PDAF: the state grid is subdivided into disjoint subdomains. Only observations whose distance from the center of the corresponding subdomain is smaller than a cutoff radius are used to update the elements of the state vector within the subdomain.
The geometric horizontal extent of the state grid cells and data grid cells increases with altitude. An edge at 550 km altitude is 7% larger than at 100 km. Moreover, the vertices of each grid are located closer to each other at the poles. At the equator the distance between two neighboring vertices along a circle of latitude is almost six times larger than at 80\(^{\circ }\) latitude. Additionally, the vertical extent of the state grid cells increases with altitude due to the use of pressure levels. To include about the same number of observations at each subdomain, we compute the distance using the indices of the state grid cells as coordinates. To transfer the coordinates of the data grid to the index coordinates of the state grid, we use the geometric height of the ensemble mean.
We subdivided the state grid into subdomains containing at most three cells in meridional, zonal and vertical direction. The distance is computed using the L2 norm. The cutoff radius is seven grid cells, which corresponds to a horizontal metric radius of about 4000 km at the equator and about 700 km at \(\pm 80^{\circ }\) latitude.
Additionally, we apply observation localization in some experiments. For each subdomain the associated observations are weighted based on the distance. PDAF computes the weights with a finite function that mimics a Gaussian, realized as polynomial of order five (Gaspari and Cohn 1999, Eq. 4.10). This weighting function monotonically decreases from one at zero distance to zero at a distance equal to the cutoff radius.
State constraints
After the analysis step the state vector may contain values that are physically impossible. Thus, we enforce the following constraints:

The neutral temperatures given in Kelvin must be positive.

The mass fraction of each species must be in the interval [0, 1].

The mass fractions at each location must sum up to one.
Results and discussion
Openloop experiments
At first we try different setups for the TIEGCM without assimilating any data. We investigate two setups for the lower boundary conditions: a flat lower boundary and a zonal mean climatology lower boundary derived from the MSIS and HWM. Additionally, we compare openloop simulations using the Heelis and Weimer models. The Heelis model implies the use of the Kp index, whereas the Weimer model implies the use of solar wind and interplanetary magnetic field parameters. The F10.7 index is used in all experiments. The openloop experiments are summarized in Table 2. The following discussion always refers to the ensemble mean of the openloop experiments.
When using the zonal mean climatology instead of a flat lower boundary the median density (computed over the whole time period of the simulations) along the CHAMP orbit increases by 5% (OLS 2 vs. OLS 1). When using the Weimer model instead of the Heelis model the median density along the CHAMP orbit increases by 13% (OLS 3 vs. OLS 2). The alongtrack densities of OLS 1 and OLS 2 show the same behavior and are basically separated by an offset, whereas the alongtrack densities of OLS 3 show other features (see Fig. 4), for example, a larger density drop at the north pole.
The height profiles showing the median neutral density in Fig. 5 associated with the OLS 2 and OLS 3 intersect with the profiles associated with the calibrated NRLMSIS 2.0. The median density of OLS 2 and OLS 3 below the intersections is higher than the median density of the calibrated NRLMSIS 2.0. Accordingly, above the intersections the NRLMSIS 2.0 has higher densities. This means that at the analysis steps, the densities above the corresponding intersection must increase, while the densities below must decrease. In other words, the innovation (in the language of data assimilation, it is generally the difference between observations and model forecasts) has a different sign depending on the altitude.
Data assimilation experiments
We tested different setups for the data assimilation that are summarized in Table 3. For the TIEGCM we use the same setup as for the OLS 3, since the external forcing has the highest temporal resolution. We use the median of the differences between the accelerometerderived neutral densities and the corresponding densities of the TIEGCM as performance indicator for our experiments (see last column of Table 3). We show only the results of experiment 8 in more detail since it achieved the best improvement for GRACE and the second best improvements for CHAMP.
We present only the ensemble mean of the neutral densities, since it reduces the dimensionality of the ensemble, simplifying the illustration of the results.
We first look at the temporal evolution of the ensemble mean. Figure 6 shows the time series of the neutral mass densities at nine cells of the data grid for the first 2 days of the experiment. The columns contain the time series located at 250 km, 300 km, and 475 km, respectively. The average height during the experiment of the CHAMP and GRACE satellite are 302 km and 474 km, respectively. Thus, the second column is associated with the CHAMP mission and the third column with the GRACE satellite. The innovation is the difference between the densities of the calibrated NRLMSIS 2.0 and the densities forecasted by the model. At the first analysis step (27 March) and at 250 km (first column), the correction is larger than the innovation. This is especially visible at 60\(^{\circ } N\) latitude (panel a). However, this initial overshooting does not affect the long term behavior of the assimilated time series. In fact the assimilated densities stays close to the calibrated NRLMSIS 2.0 densities after the second analysis step.
At 300 km and 60\(^{\circ } N\) (panel b) one can observe the opposite: After the analysis step the density is pushed further away from the calibrated NRLMSIS 2.0. But, after a few more analysis steps the assimilated time series follows the calibrated NRLMSIS 2.0 closely.
Figure 7 illustrates in the same way as Fig. 6 neutral density time series, but shows another period including the storm. The corrections are larger than in Fig. 6 showing quiet conditions. During the forecast phase the ensemble mean departs much faster from the analyzed state as under quiet conditions. Consequently, at the subsequent analysis steps larger corrections are necessary. The analyzed state does not fit to the model dynamics during the storm.
As suggested by Fig. 6, the overshooting after the first analysis step depends on the altitude. Figure 8 relates the innovation at each altitude of the data grid with the actual correction performed at the analysis step for the first nine analysis steps. Overshooting occurs mainly between 190 km and 260 km after the first analysis step (intersections of the dark blue line with right vertical line). The profiles of the analysis steps following the first one are similar: At 100 km the calibrated NRLMSIS 2.0 is basically ignored. With increasing altitude the influence of the calibrated NRLMSIS 2.0 gets larger. At 500 km roughly half of the innovation is adopted at the analysis step. Above 500 km the influence of the calibrated NRLMSIS 2.0 decreases slightly.
In Fig. 9, we show the average ratio of the standard deviations of the calibrated NRLMSIS 2.0 (computed using Eq. 7) and the forecasted ensemble at the four first analysis steps. Before the first analysis step the median standard deviation of the calibrated NRLMSIS 2.0 is about one and a half times larger than the standard deviation of the ensemble. Only at 100 km altitude the calibrated NRLMSIS 2.0 has on average a slightly smaller standard deviation than the ensemble. After the first analysis step the ratio becomes larger, since the standard deviation of the ensemble is reduced: Above 200 km the standard deviation of the ensemble is about 4 times smaller. After the fourth step it is about 6 times smaller. The profiles have a local minimum at 300 km altitude that is caused by the weighting of the calibrated NRLMSIS 2.0 based on the vertical distance to CHAMP flying at that altitude.
The difference between the forecast and analysis ensemble mean is shown in Fig. 10 on world maps for different pressure levels and analysis steps. The position of CHAMP is marked with a star symbol. The model is updated globally, as expected. Above roughly 200 km negative values (density is increased at analysis step) mainly occur on the night side south pole. At the day side the density is mostly decreased at the analysis step (positive difference). Below 200 km the differences are almost only negative. A dependency on the location of the satellite is not visible.
To compare the neutral densities from the assimilation experiment with the densities derived from the accelerometers, we interpolate the densities on the state grid to the corresponding orbits using the same method that is used to interpolate the state grid to the data grid. In Fig. 11, the alongtrack neutral densities are plotted for a twelve hour long subset of the experiment including the storm. The assimilation run fits much better to the observations compared with the openloop simulation, since it is not constantly too small. Indeed, it often resembles the observed time series better than the calibrated NRLMSIS 2.0 time series, for example, at 10:50, 14:05, 16:10. The same holds for the GRACE time series. Especially, from 15:0018:00 the assimilation time series outperforms the others.
Figure 12 confirms the previous findings. Along the orbit of CHAMP the assimilation run is much closer to the accelerometerderived densities than the openloop simulation. Along the GRACE orbit the assimilation run also outperforms the openloop simulation. The calibrated NRLMSIS 2.0 is closest to the accelerometerderived densities and has the smallest spread for CHAMP and GRACE.
The major issue with our approach are large jumps in the ensemble mean time series especially during the storm. The model departs from the analyzed state much faster as during quiet conditions. We believe that those jumps can be reduced by co estimating suitable (internal) model parameters, that are not limited to corrections for external forcing, like the F10.7 proxy. For example, one could try corrections for hard coded parameters like chemical reaction rates, eddy diffusion, thermal diffusion, characteristic energy of particles, or solar proton flux, but at present we cannot yet provide a specific recommendation. Sheng et al. (2017) suggests that the cooling processes are not correctly represented in the TIEGCM at the 5 April 2010 geomagnetic storm and Lu et al. (2014) suspects that the eddy diffusion coefficient is too high during the storm.
There are many options for the data assimilation setup: The ensemble generation, filter choice and related settings, and the calibration of the NRLMSIS 2.0 and the approximation of the standard deviation could be tuned in followon research. Within the limitations of this study, we have explored only a small subset.
A caveat is that our experiments were conducted in a period with small solar irradiance, and that for a period with high solar activity other settings might be necessary. Moreover, we suggest that further research could focus on adding, additional independent observations. An evident candidate are TEC values as provided via GNSS observations or—more representative for the low Earth orbit—from radar altimetry over the oceans.
Conclusions
We have implemented a new twostep approach for assimilating alongtrack observations into a physicsbased model of the upper atmosphere. First an empirical model is calibrated via scale factors derived from the accelerometer aboard a LEO satellite. In a second step, the calibrated model is evaluated on a regular grid and the resulting neutral densities are assimilated into the numerical model. Here, we use densities derived from the CHAMP accelerometer to calibrate the NRLMSIS 2.0 and assimilate the densities into the TIEGCM. We applied the approach to a 2weeklong period in 2010 including the 5 April 2010 geomagnetic storm.
We demonstrated that the assimilation approach has a global impact on the model and that the model prediction along the CHAMP and GRACE orbit fits well to the corresponding observations. When comparing the openloop simulation with the assimilation run, the RMSE was reduced from \(2.4\times 10^{15}\) to \(1.7\times 10^{15}\) \(\frac{\text {g}}{\text {cm}^3}\) for CHAMP and from \(1.4\times 10^{16}\) to \(9.6\times 10^{17}\) \(\frac{\text {g}}{\text {cm}^3}\) for GRACE (experiment 8 in Table 3). The median difference between model and observations is 45% smaller for CHAMP and 20% smaller for GRACE. We believe this approach could be thus beneficial for ’transplanting’ the high accuracy of in situ neutral density observations to other satellites at similar altitudes. It could also be used by modelers to improve the representation of processes and boundary conditions.
We found that large jumps in the density time series were introduced by the analysis steps. Here, the model moves away fast from the analyzed state, since the model parameters controlling the dynamics of the model are not updated at the analysis step. We suspect, that the jumps can be handled by adding additional entries to the state vector for estimating corrections for TIEGCM parameters. For example, cooling rates, eddy diffusion, or reaction rates. Estimating the dynamics of the TIEGCM in that way could produce solutions that outperform the calibrated NRLMSIS 2.0. Another idea for future research is applying the twostep approach to CHAMP and GRACE simultaneously.
Availability of data and materials
The TIEGCM model code can be downloaded at https://www.hao.ucar.edu/modeling/tgcm/tie.php after a registration. The data to run the TIEGCM are available at http://download.hao.ucar.edu/pub/tgcm/data/. The NRLMSIS 2.0 model code is attached to the corresponding publication as supplement (Emmert 2021, Data Set 8) https://agupubs.onlinelibrary.wiley.com/action/downloadSupplement?doi=10.1029%2F2020EA001321&file=ess2666sup00092020EA001321ds08.zip The code of PDAF can be downloaded http://pdaf.awi.de/register/index.php after a registration. The accelerometerderived densities are provided by Vielberg (2021). However, for CHAMP the data sets contains only NaNs in March 2010. The supplement includes a corrected version (Additional files 1, 2, 3, 4). The scale factors and the neutral densities (calibrated NRLMSIS 2.0, openloop simulation 3 and assimilation experiment 8) along the GRACE (Additional files 5, 6, 7) and CHAMP (Additional files 8, 9, 10) orbit can be found in the supplement of this paper. Please contact the author for the source code of the assimilative version of TIEGCM or the TIEGCM output of our experiments on the state grid or data grid.
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Acknowledgements
We thank Kristin Vielberg for providing the accelerometerderived neutral densities for CHAMP and GRACE. We would also like to show our gratitude to Lars Nerger for answering many questions about PDAF and Astrid Maute for answering questions about TIEGCM.
Funding
Open Access funding enabled and organized by Projekt DEAL. The authors are grateful to the research grant through the TIPOD project (FKZ.: KU 1207/271) supported by the German Research Foundation under SPP 1788 (DynamicEarth).
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AC has integrated PDAF into TIEGCM, conducted the experiments, created all plots and written large parts of the manuscript. JK helped to refine the draft and contributed to the writing. All authors read and approved the final manuscript.
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Supplementary Information
Additional file 1.
Accelerometer derived densities CHAMP March 2010.
Additional file 2.
Accelerometer derived densities CHAMP April 2010.
Additional file 3.
Accelerometer derived densities GRACE March 2010.
Additional file 4.
Accelerometer derived densities GRACE April 2010.
Additional file 5.
Calibrated NRLMSIS 2.0 GRACE.
Additional file 6.
Assimilation experiment 8 GRACE.
Additional file 7.
Open loop simulation 3 GRACE.
Additional file 8.
Calibrated NRLMSIS 2.0 CHAMP.
Additional file 9.
Assimilation experiment 8 CHAMP.
Additional file 10.
Open loop simulation 3 CHAMP.
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Corbin, A., Kusche, J. Improving the estimation of thermospheric neutral density via twostep assimilation of in situ neutral density into a numerical model. Earth Planets Space 74, 183 (2022). https://doi.org/10.1186/s4062302201733z
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DOI: https://doi.org/10.1186/s4062302201733z