Attitude Tracking Control Using an Online Identification and a Linear Quadratic Regulator–Based Strategy in the Presence of Orbital Eccentricity-Reference-Cited by-同舟云学术

Attitude Tracking Control Using an Online Identification and a Linear Quadratic Regulator–Based Strategy in the Presence of Orbital Eccentricity

Published:2012-01 Issue:1 Volume:25 Page:71-79
ISSN:0893-1321
Container-title:Journal of Aerospace Engineering
language:en
Short-container-title:J. Aerosp. Eng.

Author:

Moradi Morteza¹²³,Menhaj Mohammad B.¹²³,Ghasemi Ali¹²³

Affiliation:

1. Islamic Azad Univ., Nowshahr Branch, Nowshahr, Mazandaran, Iran (corresponding author).

2. Electrical Engineering Dept., Amir-Kabir Univ. of Technology, Tehran, Iran.

3. Islamic Azad Univ., South Tehran Branch, Tehran, Iran.

Publisher

American Society of Civil Engineers (ASCE)

Subject

Mechanical Engineering,Aerospace Engineering,General Materials Science,Civil and Structural Engineering

Link

http://ascelibrary.org/doi/pdf/10.1061/%28ASCE%29AS.1943-5525.0000098

Reference27 articles.

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2. Spacecraft pitch and roll/yaw actuations using control moment gyroscopes for attitude stabilization;Bohari B.;Jurnal Mekanikal,2007

3. Large and sharp solar wind dynamic pressure variations as a source of geomagnetic field disturbances at the geosynchronous orbit

4. Suboptimal attitude control of a spin-stabilized axisymmetric spacecraft

5. Fan Z. Hua S. Chundi M. and Yuchang L. (2002). “An optimal attitude control of small satellite with momentum wheel and magnetic torquerods.” IEEE Proc. 4th World Congress on Intelligent Control and Automation Press of East China University of Science and Technology Shanghai China 2 1395–1398.

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