Nalbantoğlu, Volkan

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Profile URL
https://hdl.handle.net/20.500.14411/8476
Name Variants
Nalbantoglu, V.
V., Nalbantoglu
Nalbantoglu, Volkan
Nalbantoğlu, Volkan
N.,Volkan
Volkan, Nalbantoglu
N., Volkan
Volkan, Nalbantoğlu
Nalbantoglu,V.
V.,Nalbantoğlu
V.,Nalbantoglu
Nalbantoğlu,V.
Job Title
Doktor Öğretim Üyesi
Email Address
volkan.nalbantoglu@atilim.edu.tr
Main Affiliation
Airframe and Powerplant Maintenance
Status
Former Staff
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ORCID ID
Scopus Author ID
Turkish CoHE Profile ID
Google Scholar ID
WoS Researcher ID

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Scholarly Output

3

Articles

2

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0/0

Supervised MSc Theses

0

Supervised PhD Theses

0

WoS Citation Count

14

Scopus Citation Count

14

WoS h-index

2

Scopus h-index

2

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0

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0

WoS Citations per Publication

4.67

Scopus Citations per Publication

4.67

Open Access Source

0

Supervised Theses

0

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JournalCount
7th Asian/Australian Rotorcraft Forum, ARF 2018 -- 7th Asian/Australian Rotorcraft Forum, ARF 2018 -- 30 October 2018 through 1 November 2018 -- Seogwipo City, Jeju Island -- 1507001
International Journal of Robust and Nonlinear Control1
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering1
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Subject: nonlinear control

Scholarly Output Search Results

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    Article
    Citation - WoS: 4
    Citation - Scopus: 4
    Multiloop State-Dependent Nonlinear Time-Varying Sliding Mode Control of Unmanned Small-Scale Helicopter
    (Sage Publications Ltd, 2020) Ozcan, Sinan; Salamci, Metin U.; Nalbantoglu, Volkan
    Time delays, parameter uncertainties, and disturbances are the fundamental problems that hinder the stability and reduce dramatically the tracking performance of dynamical systems. In this paper, a new state-dependent nonlinear time-varying sliding mode control autopilot structure is proposed to cope with these dynamical and environmental complexities for an unmanned helicopter. The presented technique is based on freezing the nonlinear system equations on each time step and designing a controller using the frozen system model at this time step. The proposed method offers an improved performance in the presence of major disturbances and parameter uncertainties by adapting itself to possible dynamical varieties without a need of trimming the system on different operating conditions. Unlike the existing linear cascade autopilot structure, this study also proposes a nonlinear cascade state-dependent coefficient helicopter autopilot structure consisting of four separate nonlinear sub-systems. The proposed method is tested through the real time and PC-based simulations. To show the performance of the proposed robust method, it is also bench-marked against a linear sliding control control in PC-based simulations.