On state estimation for an orbiting single tether system

Author

Denney, Thomas S., Jr. ; Greene, Michael E.

Author_Institution

Auburn Univ., AL, USA

Volume

27

Issue

4

fYear

1991

fDate

7/1/1991 12:00:00 AM

Firstpage

689

Lastpage

695

Abstract

The effects of instrumentation accuracy and configuration on estimation error are studied for the small expandable-tether deployment system (SEDS) using a continuous-discrete extended Kalman filter (CDEKF) state estimator. A twelfth order model that incorporates the rigid body modes of the tether as well as the satellite attitude dynamics is developed. Simulation results using the model and the estimator indicate that the originally planned instrumentation package could not estimate the state vector adequately. Recommendations are made and results presented that reduce the estimation error by adding instruments and increasing selected measurement accuracies

Keywords

Kalman filters; aerospace simulation; artificial satellites; digital simulation; estimation theory; state estimation; continuous-discrete extended Kalman filter; estimation error; expandable-tether deployment system; orbiting single tether; satellite attitude dynamics; satellite dynamics; simulation; spacecraft attitude estimation; state estimator; state vector; twelfth order model; Aerodynamics; Angular velocity; Estimation error; Extraterrestrial measurements; Instruments; Length measurement; Packaging; Satellites; State estimation; Velocity measurement;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/7.85043

Filename

85043