Adaptive Kalman filter for the aerobraking phase of Mars missions

Li, Maodeng; Wang, Dayi; Huang, Xiang‐Yu; Li, Ji

doi:10.1109/chicc.2014.6896728

Cited by 1 publication

(2 citation statements)

References 9 publications

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“…Similarly, the perturbing planet ephemeris error propagation model can be established based on the differential of acceleration with respect to the changes in r i , that is dr i (13) can be rewritten as follows…”

Section: Uncertainty In the Target Ephemerismentioning

confidence: 99%

“…Li et al 12 proposed the autonomous navigation scheme applied UPF in celestial navigation to achieve accurate navigation with respect to the target planet in encounter phrase. Li et al 13 proposed the autonomous navigation method based on adaptive Kalman filter for the aerobraking phase of Mars missions. Huang et al 14 designed a semi-physical simulation system of autonomous optical navigation for Mars approaching phase.…”

Section: Introductionmentioning

confidence: 99%

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Autonomous celestial navigation for a deep space probe approaching a target planet based on ephemeris correction

Fang

Ning

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article aims to propose an autonomous navigation method to simultaneously obtain precise position and velocity estimation of a deep space probe both with respect to Earth and with respect to the target, and estimate and correct the ephemeris uncertainty of the target that has a great influence on the navigation accuracy with respect to Earth. In this article, based on the analysis of the influences of ephemeris error on the state model, optical measurement, and the navigation accuracy, the ephemeris error is modeled. By taking the differences between the planned image and the actual image of the target as the ephemeris uncertainty measurement, the method is carried out by augmenting ephemeris uncertainty as system states, and is able to estimate and correct the ephemeris uncertainty of the target planet, and the position and velocity of the probe with respect to Earth and with respect to the target planet autonomously. The results show the influence of ephemeris error is removed from the orbital dynamics of the navigation system, and the proposed method can improve the accuracy with respect to Earth. The results demonstrate the proposed method autonomously yields superior performance with respect to Earth and with respect to the target.

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Section: Uncertainty In the Target Ephemerismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%