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TECHNICAL BRIEFS

Receding Horizon Stabilization of a Rigid Spacecraft With Two Actuators

[+] Author and Article Information
Nicolas Marchand, Mazen Alamir

Laboratoire d’Automatique de Grenoble (LAG), INPG-UJF-CNRS UMR 5528, ENSIEG BP 46, 38402 Saint Martin d’Hères Cedex, France

J. Dyn. Sys., Meas., Control 125(3), 489-491 (Sep 18, 2003) (3 pages) doi:10.1115/1.1591806 History: Received March 17, 1999; Revised October 17, 2002; Online September 18, 2003
Copyright © 2003 by ASME
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References

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Figures

Grahic Jump Location
Closed loop behavior of the rigid spacecraft with J1=2500 kg m2,J2=6500 kg m2,J3=8500 kg m2 (SPOT4, Sira-Ramirez and Siguerdidjane, 1996 12), prediction horizon tf=10 s with Nf=20 points, a sampling period T=0.5 s, a Chebyshev’s polynomial basis of dimension N+1=6 and initial condition (ω102030000)=(0,0,0,2π/3,π/3,0). The perturbed case is with 10% error on a simulating a momentum error and 5° of permanent offset on θ simulating a captor error.

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