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A folding wing system for guided ammunitions: mechanism design, manufacturing and real-time results with LQR, LQI, SMC and SOSMC

Published online by Cambridge University Press:  01 September 2023

A. Sayıl Open the ORCID record for A. Sayıl [Opens in a new window] ,
F. Erden Open the ORCID record for F. Erden [Opens in a new window] ,
A. Tüzün Open the ORCID record for A. Tüzün [Opens in a new window] ,
B. Baykara Open the ORCID record for B. Baykara [Opens in a new window]  and
M. Aydemir Open the ORCID record for M. Aydemir [Opens in a new window]
A. Sayıl
Affiliation:
Department of Astronautical Engineering, Sivas University of Science and Technology, Sivas 58000, Türkiye
F. Erden*
Affiliation:
Department of Aeronautical Engineering, Sivas University of Science and Technology, Sivas 58000, Türkiye
A. Tüzün*
Affiliation:
Department of Mechatronic Systems, TUBITAK Defense Industries Research and Development Institute – SAGE, Ankara 06261, Türkiye
B. Baykara
Affiliation:
Department of Mechatronic Systems, TUBITAK Defense Industries Research and Development Institute – SAGE, Ankara 06261, Türkiye
M. Aydemir
Affiliation:
Department of Mechatronic Systems, TUBITAK Defense Industries Research and Development Institute – SAGE, Ankara 06261, Türkiye
*
Corresponding authors: F. Erden and A. Tüzün; Emails: [email protected]; [email protected]
Corresponding authors: F. Erden and A. Tüzün; Emails: [email protected]; [email protected]
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Abstract

In the present work, a folding wing system (FWS) was developed for guided ammunitions, so that the swept-back angle could be adjusted during both gliding and diving phases. Unlike previous designs, the FWS does not have any fixing mechanisms or brake elements, and it provides folding functionality to reduce the drag force during the terminal phase. We conducted mechanism design, manufactured the FWS, performed system identification and designed various controllers including linear quadratic regulator (LQR), linear quadratic integrator (LQI), sliding mode control (SMC) and second-order sliding mode control (SOSMC) to adjust and hold the desired swept-back angles. Then, the performance of the FWS was tested experimentally under two different flight scenarios, with and without aerodynamic loads. While all controllers operated with almost zero steady-state error (SSE) in the absence of aerodynamic loads, the SOSMC was the most effective controller under aerodynamic loads, considering SSE, delay, chattering, and energy consumption.

Keywords

wing mechanismsystem identificationsliding mode controlsecond-order sliding modelinear quadratic regulatorlinear quadratic integrator
Type
Research Article
Information
The Aeronautical Journal , Volume 128 , Issue 1322 , April 2024 , pp. 788 - 811
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Copyright
© The Author(s), 2023. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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