Orbital Data Applications for Space Objects

Chen, Lei; Bai, Xian-Zong; Liang, Yangang; Li, Kebo

doi:10.1007/978-981-10-2963-9

Cited by 17 publications

(11 citation statements)

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“…The errors and covariance in the along-track direction are greater than those in the radial and cross-track directions, mainly owing to orbit dynamics. Previous studies [45] determined that the along-track error was larger than the others because it diverges in proportion to the square of the time step, whereas the errors along the other directions are only proportional to the time step. In addition, we estimated that the negative correlations observed between the radial and along-track directions are also mainly due to orbit dynamics.…”

Section: Discussionmentioning

confidence: 94%

“…In general, the orbit error can be induced as the relative movements of two objects, where one orbit is on the true orbit and the other is on the estimated orbit. The orbit propagation properties have been studied using relative motion equations in the RSW frame [43][44][45].…”

Section: Propagation Characteristics Of Orbit Dynamicsmentioning

confidence: 99%

“…The geometric modeling of relative motion can express orbit error by means of orbital elements as follows for a near-circular orbit [45]:…”

Section: Propagation Characteristics Of Orbit Dynamicsmentioning

confidence: 99%

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Covariance Analysis of Real-Time Precise GPS Orbit Estimated from Double-Differenced Carrier Phase Observations

Kim

Song

et al. 2019

Remote Sensing

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The covariance of real-time global positioning system (GPS) orbits has been drawing attention in various fields such as user integrity, navigation performance improvement, and fault detection. The international global navigation satellite system (GNSS) service (IGS) provides real-time orbit standard deviations without correlations between the axes. However, without correlation information, the provided covariance cannot assure the performance of the orbit product, which would, in turn, causes significant problems in fault detection and user integrity. Therefore, we studied real-time GPS orbit covariance characteristics along various coordinates to effectively provide conservative covariance. To this end, the covariance and precise orbits are estimated by means of an extended Kalman filter using double-differenced carrier phase observations of 61 IGS reference stations. Furthermore, we propose a new method for providing covariance to minimize loss of correlation. The method adopted by the IGS, which neglects correlation, requires 4.5 times the size of the covariance to bind orbit errors. By comparison, our proposed method reduces this size from 4.5 to 1.3 using only one additional parameter. In conclusion, the proposed method effectively provides covariance to users.

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Section: Discussionmentioning

confidence: 94%

Section: Propagation Characteristics Of Orbit Dynamicsmentioning

confidence: 99%

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Covariance Analysis of Real-Time Precise GPS Orbit Estimated from Double-Differenced Carrier Phase Observations

Kim

Song

et al. 2019

Remote Sensing

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“…The angle between velocity vectors and their magnitude ratio are found to be η= 1 * 2 =102.458 degree The standard deviation in radial and transverses direction are found to be: == 4356.886 km and = 6387.9253 km The altitude difference and closet approach distance was found to be: ∆h = 10.277 km = 10713.123 The collision probability is obtained by substituting the known values in Eq. (10) and is compared with the existing explicit collision probability result [2] is tabulated in table 5.…”

Section: Results and Discussion A Calculation Of Collision Probability Of Taurus And Iridiummentioning

confidence: 99%

“…This equation is valid for all the satellite irrespective of the shape and size. Lie Chen et al [2] derives the explicit expression for calculating collision probability assuming that the orbits are circular or near-circular orbit. The expression considers only the components of relative position and velocity and their standard deviation of position vectors.…”

Section: Introductionmentioning

confidence: 99%

A Study on the Effect of J2 Perturbation on Optimum Delta-V for Collision Avoidance Maneuver

Gisa¹

2020

IJERT

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The focus of this study aims to understand the probability of collision between any two objects orbiting the earth. Iridium 73 is considered as the primary satellite and the dead satellite Taurus is considered as the debris for the collision probability study. The numerical results agree favorably with the predicted values from the explicit collision probability method. The collision avoidance maneuver is performed to safeguard the satellite by changing its semi-major axis and bringing back to the same orbit after maneuvering. Considering a range of true anomalies, the optimum delta-V is obtained by trial and error method. The effect of J2 perturbation of the earth on the optimum delta-V is carefully studied and has been observed to be less than that of an unperturbed condition. This study shows the significance of the collision avoidance maneuver and the J2 perturbation to perform a safe maneuver.

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Spacecraft Collision Avoidance: Data Management, Risk Assessment, Decision Planning Models and Algorithms

Patnala,

Abdin

2024

Studies in Big Data

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Orbital Data Applications for Space Objects

Cited by 17 publications

References 0 publications

Covariance Analysis of Real-Time Precise GPS Orbit Estimated from Double-Differenced Carrier Phase Observations

Covariance Analysis of Real-Time Precise GPS Orbit Estimated from Double-Differenced Carrier Phase Observations

A Study on the Effect of J2 Perturbation on Optimum Delta-V for Collision Avoidance Maneuver

Spacecraft Collision Avoidance: Data Management, Risk Assessment, Decision Planning Models and Algorithms

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