Research Article
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Year 2017, Volume: 18 Issue: 4, 788 - 803, 31.10.2017
https://doi.org/10.18038/aubtda.340842

Abstract

References

  • [1] Kamişli H. Design of control systems for a launcher to reduce the thrust effect (thesis in Turkish with an abstract in English). MSc, Gazi University, Ankara, Turkey, 2015.
  • [2] Haug D, Wagner H. Active hardkill protection systems: analysis and evaluation of different system concepts. Technical Report, 2011.
  • [3] Zhang D, Xiao J. A dynamic model for rocket launcher with coupled rigid and flexible motion. Applied Mathematics and Mechanics 2005; 26: 5: 609-617.
  • [4] Dziopa Z, Krzysztofik I, Koruba Z. An analysis of the dynamics of a launcher-missile system on a movable base. Bulletin of the Polish Academy of Sciences, Technical Sciences, 2010; 58: 4: 645-650.
  • [5] Bingül Z, Küçük S. Robot Dinamiği ve Kontrolü. İstanbul, Turkey: Birsen Yayınevi, 2008.
  • [6] Dokumacı K. Mathematical modelling, PID and sliding mode control of a rocket launcher system. MSc, Gazi University, Ankara, Turkey, 2014. [7] Kamişli H, Salamci MU, Özkan B. Elektromekanik eyletimli bir firlatma sisteminin itki etkisini en aza indirgeyecek şekilde denetimi. Otomatik Kontrol Ulusal Toplantısı (TOK), Denizli, Turkey, 2015.
  • [8] Utkin VI. Sliding Mode Control. Encylopedia of Life Support Systems (EOLSS), Control Systems, Robotics and Automation. Vol XIII, 2009.
  • [9] Utkin V, Guldner J, Shi J. Sliding Mode Control in Electromechanical Systems. USA: Taylor and Francis, 103-153, 271-302, 2009.
  • [10] Özkan B. Dynamic modeling and control of an electromechanically-actuated launcher (proceeding in Turkish with an abstract in English). Ulusal Makine Teorisi Sempozyumu, Erzurum, Turkey, 2013.
  • [11] Kamişli H, Salamci MU, Özkan B. Dynamic modeling of an electromechanically-actuated launcher. 17th International Carpathian Control Conference, Slovakia, 2016.
  • [12] Kamişli H, Salamci MU, Özkan B. Design of a cascaded control system for an electromechanically-actuated launcher to reduce the thrust effect. 17th International Carpathian Control Conference, Slovakia, 2016.
  • [13] Ogata K. Modern Control Engineering. 5th ed. New Jersey, USA: Pearson, 2010.

PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY

Year 2017, Volume: 18 Issue: 4, 788 - 803, 31.10.2017
https://doi.org/10.18038/aubtda.340842

Abstract

Dynamic modeling and control of two-degree-of-freedom launchers which
are utilized for launching munitions such as missiles and rockets have become
one of the most popular fields in recent years. Control of launch vehicles
gains more importance especially when they are mounted on moving vehicles. In
this study, the mathematical modeling and control with parameter uncertainties of
a high-accuracy two-degree-of-freedom electromechanically-actuated launcher are
investigated in the direction of reducing the impact impulse on the control
system. In this context, after the dynamic equations of the system are derived,
the design of convenient control systems is carried out so as to reduce the undesired
contribution of the thrust effect. In control, computed torque and
proportional, integral, and derivative (PID) and computed torque and sliding
mode control algorithms, and computed torque and sliding mode control cascaded
control algorithms are developed by taking the parameter uncertainties into consideration.
In the conclusion part, the performance characteristics of these controllers
are compared and it is shown that the cascaded control scheme yields more
satisfactory results in accurate position control. In the computer simulations
conducted in this extent, the MATLAB
Ò software and its SIMULINKÒ module are utilized.

References

  • [1] Kamişli H. Design of control systems for a launcher to reduce the thrust effect (thesis in Turkish with an abstract in English). MSc, Gazi University, Ankara, Turkey, 2015.
  • [2] Haug D, Wagner H. Active hardkill protection systems: analysis and evaluation of different system concepts. Technical Report, 2011.
  • [3] Zhang D, Xiao J. A dynamic model for rocket launcher with coupled rigid and flexible motion. Applied Mathematics and Mechanics 2005; 26: 5: 609-617.
  • [4] Dziopa Z, Krzysztofik I, Koruba Z. An analysis of the dynamics of a launcher-missile system on a movable base. Bulletin of the Polish Academy of Sciences, Technical Sciences, 2010; 58: 4: 645-650.
  • [5] Bingül Z, Küçük S. Robot Dinamiği ve Kontrolü. İstanbul, Turkey: Birsen Yayınevi, 2008.
  • [6] Dokumacı K. Mathematical modelling, PID and sliding mode control of a rocket launcher system. MSc, Gazi University, Ankara, Turkey, 2014. [7] Kamişli H, Salamci MU, Özkan B. Elektromekanik eyletimli bir firlatma sisteminin itki etkisini en aza indirgeyecek şekilde denetimi. Otomatik Kontrol Ulusal Toplantısı (TOK), Denizli, Turkey, 2015.
  • [8] Utkin VI. Sliding Mode Control. Encylopedia of Life Support Systems (EOLSS), Control Systems, Robotics and Automation. Vol XIII, 2009.
  • [9] Utkin V, Guldner J, Shi J. Sliding Mode Control in Electromechanical Systems. USA: Taylor and Francis, 103-153, 271-302, 2009.
  • [10] Özkan B. Dynamic modeling and control of an electromechanically-actuated launcher (proceeding in Turkish with an abstract in English). Ulusal Makine Teorisi Sempozyumu, Erzurum, Turkey, 2013.
  • [11] Kamişli H, Salamci MU, Özkan B. Dynamic modeling of an electromechanically-actuated launcher. 17th International Carpathian Control Conference, Slovakia, 2016.
  • [12] Kamişli H, Salamci MU, Özkan B. Design of a cascaded control system for an electromechanically-actuated launcher to reduce the thrust effect. 17th International Carpathian Control Conference, Slovakia, 2016.
  • [13] Ogata K. Modern Control Engineering. 5th ed. New Jersey, USA: Pearson, 2010.
There are 12 citations in total.

Details

Subjects Engineering
Journal Section Articles
Authors

Hamza Kamişli This is me

Metin U. Salamcı

Bülent Özkan

Publication Date October 31, 2017
Published in Issue Year 2017 Volume: 18 Issue: 4

Cite

APA Kamişli, H., Salamcı, M. . U., & Özkan, B. (2017). PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY. Anadolu University Journal of Science and Technology A - Applied Sciences and Engineering, 18(4), 788-803. https://doi.org/10.18038/aubtda.340842
AMA Kamişli H, Salamcı MU, Özkan B. PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY. AUJST-A. October 2017;18(4):788-803. doi:10.18038/aubtda.340842
Chicago Kamişli, Hamza, Metin U. Salamcı, and Bülent Özkan. “PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY”. Anadolu University Journal of Science and Technology A - Applied Sciences and Engineering 18, no. 4 (October 2017): 788-803. https://doi.org/10.18038/aubtda.340842.
EndNote Kamişli H, Salamcı MU, Özkan B (October 1, 2017) PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY. Anadolu University Journal of Science and Technology A - Applied Sciences and Engineering 18 4 788–803.
IEEE H. Kamişli, M. . U. Salamcı, and B. Özkan, “PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY”, AUJST-A, vol. 18, no. 4, pp. 788–803, 2017, doi: 10.18038/aubtda.340842.
ISNAD Kamişli, Hamza et al. “PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY”. Anadolu University Journal of Science and Technology A - Applied Sciences and Engineering 18/4 (October 2017), 788-803. https://doi.org/10.18038/aubtda.340842.
JAMA Kamişli H, Salamcı MU, Özkan B. PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY. AUJST-A. 2017;18:788–803.
MLA Kamişli, Hamza et al. “PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY”. Anadolu University Journal of Science and Technology A - Applied Sciences and Engineering, vol. 18, no. 4, 2017, pp. 788-03, doi:10.18038/aubtda.340842.
Vancouver Kamişli H, Salamcı MU, Özkan B. PRECISE CONTROL OF AN ELECTROMECHANICALLY-ACTUATED LAUNCHER UNDER PARAMETER UNCERTAINTY. AUJST-A. 2017;18(4):788-803.