Models for Propagation of NORAD Element Sets

Hoots, Felix R.; Roehrich, Ronald L.

doi:10.21236/ada093554

Cited by 338 publications

(162 citation statements)

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“…B = BST AR · 12.741621 is the original relationship between the ballistic coefficient B and BST AR given by Ref. [16]. However, many researchers have shown that this formula has poor accuracy, hence Sang proposed a modified formula as shown in Eq.…”

Section: Pretreatment Of Two-line Elementsmentioning

confidence: 99%

Calibration of atmospheric density model using two-line element data

Ren

Shan

2017

Astrodyn

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For satellites in orbits, most perturbations can be well modeled; however the inaccuracy of the atmospheric density model remains the biggest error source in orbit determination and prediction. The commonly used empirical atmospheric density models, such as Jacchia, NRLMSISE, DTM, and Russian GOST, still have a relative error of about 10%-30%.Because of the uncertainty in the atmospheric density distribution, high accuracy estimation of the atmospheric density cannot be achieved using a deterministic model. A better way to improve the accuracy is to calibrate the model with updated measurements. Twoline element (TLE) sets provide accessible orbital data, which can be used in the model calibration. In this paper, an algorithm for calibrating the atmospheric density model is developed. First, the density distribution of the atmosphere is represented by a power series expansion whose coefficients are denoted by the spherical harmonic expansions. Then, the useful historical TLE data are selected. The ballistic coefficients of the objects are estimated using the BSTAR data in TLEs, and the parameterized model is calibrated by solving a nonlinear least squares problem. Simulation results show that the prediction error is reduced using the proposed calibration algorithm. KEYWORDS atmospheric density model two-line element (TLE)Research Article

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Section: Pretreatment Of Two-line Elementsmentioning

confidence: 99%

Calibration of atmospheric density model using two-line element data

Ren

Shan

2017

Astrodyn

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“…The reference position p r0 will be used for geolocation as well as to cancel ephemeris errors and unknown time and frequency shifts at the satellites [1]. the ascending node, and inclination, respectively [7]. Since k is a function of and t k , we can express ð k Þ and fð k Þ as k ð Þ and f k ð Þ.…”

Section: Satellite Ephemeris Calibrationmentioning

confidence: 99%

“…The coordinate transformation from the two-dimensional earth surface coordinates x surf À y surf to earth-centered earth-fixed coordinates [7] is defined by Bðp int Þ. Then, Eq.…”

Section: Deriving the Ephemeris Calibration Error Covariance Matrixmentioning

confidence: 99%

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Error analysis of ephemeris calibration for dual-satellite TDOA/FDOA geolocation

Amishima

Suzuki

2017

IEICE ComEX

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In this paper, we provide a theoretical error analysis of a satellite ephemeris calibration for the dual-satellite TDOA/FDOA geolocation method. First, the error covariance matrix for the ephemeris calibration is derived. Then, the result is incorporated into the error covariance matrix for geolocation. The derived equation is numerically evaluated to provide an intensive error analysis in time and spatial coordinates. Further, Monte Carlo simulation results are provided, and it is shown that the theoretical results coincide with the Monte Carlo simulation results.

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“…A two-line element 2 is a data format used by NASA, to describe the orbital elements of the orbit of an Earth satellite. The elements in the TLE sets are mean elements calculated to fit a set of observations using a specific model: the SGP4/SDP4 orbital model (Hoots & Roehrich 1980). The mean orbital elements produced by the SGP4/SDP4 orbital model are Earth-centered-inertial coordinates with respect to the true equator and the mean equinox of epoch.…”

Section: Direct Comparisonmentioning

confidence: 99%

NIMASTEP: a software to modelize, study, and analyze the dynamics of various small objects orbiting specific bodies

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2012

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NIMASTEP is a dedicated numerical software developed by us, which allows one to integrate the osculating motion (using Cartesian coordinates) in a Newtonian approach of an object considered as a point-mass orbiting a homogeneous central body that rotates with a constant rate around its axis of smallest inertia. The code can be applied to objects such as particles, artificial or natural satellites, or space debris. The central body can be either any terrestrial planet of the solar system, any dwarf-planet, or even an asteroid. In addition, very many perturbations can be taken into account, such as the combined third-body attraction of the Sun, the Moon, or the planets, the direct solar radiation pressure (with the central body shadow), the non-homogeneous gravitational field caused by the non-sphericity of the central body, and even some thrust forces. The simulations were performed using different integration algorithms. Two additional tools were integrated in the software package; the indicator of chaos MEGNO and the frequency analysis NAFF. NIMASTEP is designed in a flexible modular style and allows one to (de)select very many options without compromising the performance. It also allows one to easily add other possibilities of use. The code has been validated through several tests such as comparisons with numerical integrations made with other softwares or with semi-analytical and analytical studies. The various possibilities of NIMASTEP are described and explained and some tests of astrophysical interest are presented. At present, the code is proprietary but it will be released for use by the community in the near future. Information for contacting its authors and (in the near future) for obtaining the software are available on the web site http://www.fundp.ac.be/en/research/projects/ page_view/10278201/

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Models for Propagation of NORAD Element Sets

Cited by 338 publications

References 5 publications

Calibration of atmospheric density model using two-line element data

Calibration of atmospheric density model using two-line element data

Error analysis of ephemeris calibration for dual-satellite TDOA/FDOA geolocation

NIMASTEP: a software to modelize, study, and analyze the dynamics of various small objects orbiting specific bodies

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