Spacecraft Localization via Angle Measurements for Autonomous Navigation in Deep Space Missions

Ceccarelli, Nicola; Garulli, Andrea; Giannitrapani, Antonio; Leomanni, Mirko; Scortecci, Fabrizio

doi:10.3182/20070625-5-fr-2916.00094

Cited by 8 publications

(8 citation statements)

References 8 publications

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“…Yet this case was deliberately not considered as in deep space missions this would not represent a realistic scenario. The orders of magnitude of the errors obtained were not too different from those obtained by Ceccarelli et al (2007) although it was difficult to compare as Ceccarelli et al (2007) obtained their position errors in units of kilometres. Yet we did not use measurements of the Earth's azimuth and elevation.…”

Section: The Noise Sourcesmentioning

confidence: 83%

“…The question of estimating the orbit from imprecise or noisy measurements was only addressed after the development of the Kalman filter and its extension to non-linear systems by Julier et al (1995; and Julier and Uhlmann (2004). Ceccarelli et al (2007) applied the Unscented Kalman Filter (UKF) to the problem of spacecraft localisation using only angle measurements. Giannitrapani et al (2011) presented a comparison of Extended Kalman Filter (EKF) and UKF for spacecraft localisation via angle measurements.…”

Section: J O I N T P O S I T I O N L O C a L I S At I O N O F S Pa C mentioning

confidence: 99%

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Joint Position Localisation of Spacecraft and Debris for Autonomous Navigation Applications using Angle Measurements only

Vepa

2017

J. Navigation

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In this paper, we consider the joint estimation of the position of a spacecraft and debris in Earth orbit to achieve spacecraft localisation based on angular measurements and precise measurements of the debris relative to the spacecraft. The dynamic model of the spacecraft caters for several perturbing effects, such as Earth and Moon gravitational field asymmetry and the Earth's oblateness effect. The Moon's position is assumed to be accurately known for the purposes of simulation from published Jet Propulsion Laboratory (JPL) ephemerides. The measurement process is based on the elevation and azimuth of the Moon and the Sun with respect to the spacecraft reference system. Range measurements are not assumed to be available. Position and velocity of the spacecraft are estimated by using the Unscented Kalman Filter (UKF). The performance of the filters are evaluated on an example of an Earth-orbiting satellite at an altitude over 1200 km with measurements of the directions of the Moon and the Sun only. It is shown that the estimates of position and velocity components track the corresponding simulated position and velocity components.

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Section: The Noise Sourcesmentioning

confidence: 83%

Section: J O I N T P O S I T I O N L O C a L I S At I O N O F S Pa C mentioning

confidence: 99%

Joint Position Localisation of Spacecraft and Debris for Autonomous Navigation Applications using Angle Measurements only

Vepa

2017

J. Navigation

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“…The filters have been tested on simulated data concerning two different missions. The resulting localization errors [7] and the associated confidence intervals show that the proposed algorithms provide reliable estimates, whose accuracy is sufficient for autonomous navigation in the considered class of missions. In general, for the orbit determination purpose the Kalman filtering technique is used.…”

Section: Introductionmentioning

confidence: 91%

Error Analysis of Orbit Determination for the Geostationary Satellite with Single Station Antenna Tracking Data

Chingiz¹,

Ata²

2011

POS

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In the study, position and velocity values of a geostationary satellite are found. When performing this, a MATLAB algorithm is used for Runge-Kutta Fehlberg orbit integration method to solve spacecraft’s position and velocity. Integrated method is the solution for the systems which mainly work with a single station. Method provides calculation of azimuth, elevation and range data by using the position simulation results found by RKF. Errors of orbit determination are analysed. Variances of orbit parameters are chosen as the accuracy criteria. Analysis results are the indicator of the method’s accurac

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“…In Ceccarelli et al (2009), the problem of spacecraft self-localization is addressed using angular measurements. A dynamic model of the spacecraft accounting for several perturbing effects, such as Earth and Moon gravitational field asymmetry and errors associated with the Moon ephemerides, is used.…”

Section: Introductionmentioning

confidence: 99%

“…It is assumed that range measurements are not available, and the localization problem is tackled on the basis of angle-only measurements. The dynamic model of the spacecraft is the same as in Ceccarelli et al (2009). The measurement process is based on elevation and azimuth of Moon and Earth with respect to the spacecraft reference system.…”

Section: Introductionmentioning

confidence: 99%

Spacecraft localization by indirect linear measurements from a single antenna

Hajiyev

Sofyalı

2018

AEAT

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Purpose The purpose of this paper is to present a two-stage approach for estimation of spacecraft’s position and velocity by indirect linear measurements from a single antenna. Design/methodology/approach In the first stage, direct nonlinear antenna measurements are transformed to linear x-y-z coordinate measurements of spacecraft’s position, and statistical characteristics of orbit determination errors are analyzed. Variances of orbit parameters’ errors are chosen as the accuracy criteria. In the second stage, the outputs of the first stage are improved by the designed Extended Kalman Filter for estimation of the spacecraft’s position and velocity on indirect linear x-y-z measurements. Findings The complex content of the measurement matrix in the conventional method causes periodic singularities in simulation results. In addition, the convergence of the filter using direct measurements is highly dependent on the initialization parameters’ values due to the nonlinear partial derivatives in the Jacobian measurement matrix. The comparison of the accuracy of both methods shows that the estimation by using indirect measurements reduces the absolute estimation errors. The simulation results show that the proposed two-stage procedure performs both with better estimation accuracy and better convergence characteristics. The method based on indirect measurements provides an unnoticeably short transient duration. Practical implications The proposed method can be recommended for satellite orbit estimation regarding its presented superiorities. Originality/value Inputting the single antenna measurements to the filter indirectly results in a quite simpler measurement matrix. As a result, the convergence of the filter is faster and estimation errors are lower.

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Spacecraft Localization via Angle Measurements for Autonomous Navigation in Deep Space Missions

Cited by 8 publications

References 8 publications

Joint Position Localisation of Spacecraft and Debris for Autonomous Navigation Applications using Angle Measurements only

Joint Position Localisation of Spacecraft and Debris for Autonomous Navigation Applications using Angle Measurements only

Error Analysis of Orbit Determination for the Geostationary Satellite with Single Station Antenna Tracking Data

Spacecraft localization by indirect linear measurements from a single antenna

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