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Robust Control Design for a Nanosat Launch Vehicle

[+] Author Affiliations
Estuardo Iriarte, Bei Lu, Eric Besnard

California State University, Long Beach, CA

Paper No. IMECE2012-85970, pp. 143-150; 8 pages
doi:10.1115/IMECE2012-85970
From:
  • ASME 2012 International Mechanical Engineering Congress and Exposition
  • Volume 4: Dynamics, Control and Uncertainty, Parts A and B
  • Houston, Texas, USA, November 9–15, 2012
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4520-2
  • Copyright © 2012 by ASME

abstract

The attitude control of a launch vehicle is a challenging task due to the dramatically varied vehicle dynamics along a flight path. The objective of this paper is to design robust controllers for a nanosat launch vehicle developed by California Launch Vehicle Education Initiative at California State University Long Beach. In order to control the rocket along a trajectory ascending through the earth’s atmosphere, a set of operating points at different times along the flight path are selected, the corresponding dynamics models of the rocket are obtained via linearization, and a robust H controller is designed for each operating point. Simulations are conducted in Matlab/Simulink to verify if the proposed control law stabilizes the inherent, unstable pitching motions of the vehicle at different times.

Copyright © 2012 by ASME

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