An epoch state filter for use with analytical orbit models of low earth satellites
Montenbruck, O. (2000) An epoch state filter for use with analytical orbit models of low earth satellites. Aerospace Science and Technology, Vol. 4 (4), pp. 277-287.
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Kalman filters provide a well established means for satellite orbit determination. In combination with space based sensors like GPS, DORIS or PRARE, accurate estimates of the spacecraft position and velocity can be obtained in real-time on-board the space vehicle. Traditionally, numerical methods of varying complexity are applied for propagating the state vector are referred to the epoch of the lastest sensor output. In the present stude a different approach is followed, which offers increased on-board autonomy and is particularly promising for small satellites with moderate accuracy requirements. An analytical orbit model is used to describe the spacecraft trajectory and mean elements at epoch are estimated instead of the instantaneous, osculating state vector. This adds the capability of performing on-board orbit prediction over time scales of up to one week, which is required, for instance, for the autonomous forecast of eclipse times or station contacts. Making use of the SGP4 orbit model that is compatible with NORAD twoline elements, an epoch state Kalman filters has been implemented and tested with GPS flight data of GPS/MET (MicroLab-1) and MOMSNAV (MIR). It is demonstrated that the proposed method provides an accuracy compatible with that of the analytical model and is robust enough to handle large data gaps in case of limited on-board resources for GPS operation. By adjusting the ballistic coefficient along whith the mean elements, a considerable improvement of mid-term orbit predictions is achieved over methods that are restricted to the estimation of the state vector alone.
|Title:||An epoch state filter for use with analytical orbit models of low earth satellites|
|Journal or Publication Title:||Aerospace Science and Technology|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 277-287|
|Keywords:||on-board orbit determination/Kalman filter/twoline elements/GPS|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Space|
|HGF - Program Themes:||W EO - Erdbeobachtung|
|DLR - Research area:||Space|
|DLR - Program:||W EO - Erdbeobachtung|
|DLR - Research theme (Project):||W -- no assignement (old)|
|Institutes and Institutions:||Space Operations and Astronaut Training > Hauptabteilung Raumflugbetrieb und Astronautenausbildung|
Microwaves and Radar Institute > Hauptabteilung Raumflugbetrieb und Astronautenausbildung
Institute of Communication and Navigation > Hauptabteilung Raumflugbetrieb und Astronautenausbildung
|Deposited By:||elib DLR-Beauftragter|
|Deposited On:||16 Sep 2005|
|Last Modified:||14 Jan 2010 17:16|
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