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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1/0

Supervised MSc Theses

0

Supervised PhD Theses

0

WoS Citation Count

14

Scopus Citation Count

14

WoS h-index

2

Scopus h-index

2

Patents

0

Projects

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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Author: Ozcan, S.

Scholarly Output Search Results

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    Article
    Citation - WoS: 10
    Citation - Scopus: 10
    Nonlinear Sliding Sector Design for Multi-Input Systems With Application To Helicopter Control
    (Wiley, 2020) Ozcan, S.; Salamci, M. U.; Nalbantoglu, V.
    The ability of helicopters to hover and land vertically has spurred an interesting field of research on the development of autonomous flight for these rotatory wing aircrafts. Linear control theory with gain scheduling, which is based on linearizing the system at the equilibrium points, dominated the helicopter autopilot design. Unlike the linear cascaded autopilot structure used in the existing literature, this paper uses state-dependent linear like structure, including rate-limited actuator dynamics, with cascaded autopilot topology. This approach allows nonlinear control laws to be implemented throughout the entire flight envelope, providing satisfactory robustness and stability over the various parameter uncertainties and time delays. The cascaded autopilot topology with nonlinear dynamical equations contains a new sliding sector control (SSC) mechanism which is derived for multi-input nonlinear dynamical systems. The proposed SSC structure for multi-input nonlinear systems is used in the inner loop of the cascaded autopilot system where the fastest dynamics are required to be controlled for rapid changes in the helicopter dynamical characteristics which enables one to stabilize the helicopter over a wide range of flight conditions. The proposed cascaded autopilot topology with the new SSC mechanism is tested in simulations to assess its robustness and stability properties. To establish its feasibility, the proposed control method is replaced with a suboptimal control method, namely state-dependent differential Riccati equation (SDDRE) method, for the inner loop and the results of the proposed control architecture are compared with those of SDDRE method.