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Optimizing the Satellite Control Gains with Nonlinear Motion Equations using SQP Method

by Sayed Mohammad Hadi Taherzadeh, Mohammad Fatehi, Mehran Nosratollahi, Amirhossein Adami
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International Journal of Computer Applications
Foundation of Computer Science (FCS), NY, USA
Volume 118 - Number 22
Year of Publication: 2015
Authors: Sayed Mohammad Hadi Taherzadeh, Mohammad Fatehi, Mehran Nosratollahi, Amirhossein Adami
10.5120/20879-3626

Sayed Mohammad Hadi Taherzadeh, Mohammad Fatehi, Mehran Nosratollahi, Amirhossein Adami . Optimizing the Satellite Control Gains with Nonlinear Motion Equations using SQP Method. International Journal of Computer Applications. 118, 22 ( May 2015), 33-36. DOI=10.5120/20879-3626

@article{ 10.5120/20879-3626,
author = { Sayed Mohammad Hadi Taherzadeh, Mohammad Fatehi, Mehran Nosratollahi, Amirhossein Adami },
title = { Optimizing the Satellite Control Gains with Nonlinear Motion Equations using SQP Method },
journal = { International Journal of Computer Applications },
issue_date = { May 2015 },
volume = { 118 },
number = { 22 },
month = { May },
year = { 2015 },
issn = { 0975-8887 },
pages = { 33-36 },
numpages = {9},
url = { https://ijcaonline.org/archives/volume118/number22/20879-3626/ },
doi = { 10.5120/20879-3626 },
publisher = {Foundation of Computer Science (FCS), NY, USA},
address = {New York, USA}
}
%0 Journal Article
%1 2024-02-06T23:02:27.046813+05:30
%A Sayed Mohammad Hadi Taherzadeh
%A Mohammad Fatehi
%A Mehran Nosratollahi
%A Amirhossein Adami
%T Optimizing the Satellite Control Gains with Nonlinear Motion Equations using SQP Method
%J International Journal of Computer Applications
%@ 0975-8887
%V 118
%N 22
%P 33-36
%D 2015
%I Foundation of Computer Science (FCS), NY, USA
Abstract

Two functions of control system are attitude maneuver and attitude stability. The capability to attitude-maneuver a satellite is based on using control torques. In this paper, the torques generated by Euler angle errors and quaternion error vector for small attitude commands are compared and then the same is done for large attitude commands. It's founded that Euler angle errors characterized by a fixed control do not produce the desirable response. The SQP optimization method also used to optimize calculated control gains. This SQP optimization method with the following provisions such as maximum settling time, maximum rise time, maximum overshoot and maximum steady state error causes that the Euler angles error method provides an appropriate responses.

References
  1. Gollu, N. , & Rodrigues, L. (2007, July). Control of Large Angle Attitude Maneuvers for Rigid Bodies Using Uum of Squares. In American Control Conference, 2007. ACC'07 (pp. 3156-3161). IEEE
  2. Marcel J. Sidi. (1997). Spacecraft Dynamics and Control: A Practical Engineering Approach. Cambridge University Press.
  3. Wie, B. (1998). Space Vehicle Dynamics and Control. Aiaa.
  4. Wertz, J. R. (Ed. ). (1978). Spacecraft attitude determination and control (Vol. 73). Springer Science & Business Media.
  5. Bonnans, J. F. , Gilbert, J. C. , Lemaréchal, C. , & Sagastizábal, C. A. (2006). Numerical optimization: theoretical and practical aspects. Springer Science & Business Media.
  6. Fatehi, Mohammad. , New optimization methods in engineering design. MSc seminar. Space Research center. Tehran, 2015.
  7. Roger Fletcher. (2007). the Sequential Quadratic Programming Method.
Index Terms

Computer Science
Information Sciences

Keywords

Optimizing control gains SQP Nonlinear Equations of Motion Euler Angles Error Quaternion Error Vector

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