Implementation of a Differential Geometric Filter for Spacecraft Formation Orbit Estimation | Zendy

Shu Ting Goh | Zendy; Ossama Abdelkhalik | Zendy; Seyed A. Zekavat | Zendy

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Implementation of a Differential Geometric Filter for Spacecraft Formation Orbit Estimation

Author(s) -

Shu Ting Goh,

Ossama Abdelkhalik,

Seyed A. Zekavat

Publication year - 2012

Publication title -

international journal of aerospace engineering

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.361

H-Index - 22

eISSN - 1687-5974

pISSN - 1687-5966

DOI - 10.1155/2012/910496

Subject(s) - spacecraft , extended kalman filter , kalman filter , position (finance) , filter (signal processing) , differential (mechanical device) , orbit (dynamics) , control theory (sociology) , stability (learning theory) , computer science , aerospace engineering , engineering , computer vision , artificial intelligence , control (management) , finance , machine learning , economics

The differential geometric filter is implemented to estimate the absolute andrelative positions of the spacecraft in a formation. The extended Kalman Filter isalso implemented as a benchmark for the differential geometric estimation. Onlyrelative positions between the spacecraft are measured. Relative positions are measuredusing a wireless local positioning system (WLPS) installed in all spacecraft. Two different scenarios are studied: (1) the observations include WLPS measurementsonly and (2) the observations include WLPS measurements in addition tomeasurements for the absolute position of one spacecraft made by a radar thattakes measurements from the earth’s surface. Results show that the differentialgeometric estimation has better stability performance and a faster convergencerate compared to the extended Kalman filter

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