LQG/LTR control law of drag-free satellite based on linearized orbital motion equation

Author

Wang Tao ; Zhang Hongbo ; Tang Guojian

Author_Institution

Coll. of Aerosp. Sci. & Eng., Nat. Univ. of Defense Technol., Changsha, China

fYear

2014

fDate

28-30 July 2014

Firstpage

539

Lastpage

543

Abstract

Drag-free satellite can achieve a high flight precision, offering an ideal stage to some scientific experiment. For control of LEO drag-free satellite in accelerator mode, this article builds a LQG control law, which is based on the linearization of orbital motion equation. J₂ perturbation is considered in the linearization, and the drift of accelerator is estimated by Kalman filter. LTR is introduced to improve robustness of the system. Taking a satellite of 260km altitude as an example for simulation, considering atmospheric noise, thruster noise and measure noise, maximum position error is 1 μm, and maximum control acceleration is 5 μm/s².

Keywords

Kalman filters; artificial satellites; atmospherics; linear quadratic Gaussian control; robust control; J₂ perturbation; Kalman filter; LEO drag-free satellite; LQG-LTR control law; accelerator drift estimation; accelerator mode; altitude 260 km; atmospheric noise; linearized orbital motion equation; measure noise; system robustness; thruster noise; Electronic mail; Equations; Low earth orbit satellites; Mathematical model; Noise; Space vehicles; Drag-free; J2; LEO; LQG; Linearization;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Conference (CCC), 2014 33rd Chinese

Conference_Location

Nanjing

Type

conf

DOI

10.1109/ChiCC.2014.6896681

Filename

6896681