Coupled Motion Determination and Stabilization of a Satellite Equipped with Large Flexible Elements Using ADCS Only

Paper number

IAC-19,C1,5,9,x52922

Author

Dr. Danil Ivanov, Russian Federation, Keldysh Institute of Applied Mathematics, RAS

Coauthor

Dr. Stepan Tkachev, Russian Federation, Keldysh Institute of Applied Mathematics, RAS

Coauthor

Prof. Mikhail Ovchinnikov, Russian Federation, Keldysh Institute of Applied Mathematics, RAS

Coauthor

Mr. Aleksey Shestopyorov, Russian Federation, Keldysh Institute of Applied Mathematics, RAS

Coauthor

Dr. Andrey Ovchinnikov, Russian Federation, JSC Reshetnev Information Satellite System

Coauthor

Dr. Sergey Meus, Russian Federation, JSC Reshetnev Information Satellite System

Coauthor

Dr. Evgenii Yakimov, Russian Federation, JSC Reshetnev Information Satellite System

Coauthor

Dr. Dmitry Roldugin, Russian Federation, Keldysh Institute of Applied Mathematics of RAS

Coauthor

Mr. Sergey Shestakov, Russian Federation, Keldysh Institute of Applied Mathematics of RAS

Coauthor

Dr. Anna Nuralieva, Russian Federation, Keldysh Institute of Applied Mathematics of RAS

Year

2019

Abstract

Satellites with flexible elements are used to solve a variety of applied problems. Such satellites includes telecommunication satellites with large-sized antennas, deep-space research satellites with solar sails, and satellites with robotic manipulators and external rods. During orbital and angular satellite maneuvering the vibrations inevitably excite due to the large dimensions of flexible elements, which are often made of light materials. These vibrations can not only degrade the accuracy of attitude of the entire satellites, but even lead to instability of the required motion. The installation of special damping actuators is desirable for damping low-frequency oscillations in the flexible elements. Usually piezoelectric devices installed on the non-rigid elements are used for this task. However, the case when the satellite is controlled using only the ADCS located on the main satellite body is of practical interest.

The paper considers the rigid satellite with a set of flexible elements attached to its body. The flexible motion determination along with attitude motion of the main body is estimated in real time using measurements of the star tracker and angular velocity sensor only. The damping of the oscillations and attitude stabilization in the orbital reference frame is performed by reaction wheels installed on the main body. The dependence of the flexible motion determination accuracy on the number of estimated vibration modes is studied. The comparison between the achieved motion determination accuracy using measurements of ADS sensors and using extra measurements of accelerometers installed on flexible elements or optical measurements is presented. A set of control algorithms based on LQR are proposed in the paper. Its convergence rate and final stabilization accuracy taking into account inaccuracy in motion estimation and unknown disturbances are studied. The problem of the isolated vibration modes that have small influence on the main body motion is discussed.

Abstract document

IAC-19,C1,5,9,x52922.brief.pdf

Manuscript document

IAC-19,C1,5,9,x52922.pdf (🔒 authorized access only).

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