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Kalman filtering applied to real-time monitoring of apogee maneuversPart of the Space Mathematics Division in CNES, the Flight Dynamics Center provides attitude and orbit determinations and maneuvers during the Launch and Early Operation Phase (LEOP) of geostationary satellites. Orbit determination is based on a Kalman filter method; when the 2 GHz CNES/NASA network is used, Doppler measurements are available and allow orbit determination during the apogee maneuvers. This method was used for TELE-X and TDF 2 LEOP (3-axis controlled satellites) and also for TELECOM 2 and HISPASAT (spun satellites): it enables us to follow the evolution of the maneuver and gives out a quite accurate estimation of the reached orbit. In this paper, we briefly describe the dynamic models of the orbit evolution in both cases, '3-axis' and 'inertial' thrust. Then, we present the results obtained for each case. Afterwards, we present some cases to show the robustness of the filter.
Document ID
19940019450
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Deboer, Frederic
(MATRA Marconi Space Toulouse, France)
Barbier, Christian
(Alcatel Espace Toulouse, France)
Date Acquired
September 6, 2013
Publication Date
March 1, 1993
Publication Information
Publication: JPL, SpaceOps 1992: Proceedings of the Second International Symposium on Ground Data Systems for Space Mission Operations
Subject Category
Astrodynamics
Accession Number
94N23923
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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