Search results

1 – 10 of 14
Per page
102050
Citations:
Loading...
Access Restricted. View access options
Article
Publication date: 22 September 2023

Oguz Kose, Tugrul Oktay and Enes Özen

The purpose of this paper is to obtain values that stabilize the lateral and longitudinal flight of the quadrotor for which the morphing amount and the best…

292

Abstract

Purpose

The purpose of this paper is to obtain values that stabilize the lateral and longitudinal flight of the quadrotor for which the morphing amount and the best Proportional-Integral-Derivative (PID) coefficients are determined by using the simultaneous perturbation stochastic approximation (SPSA) optimization algorithm.

Design/methodology/approach

Quadrotor consists of body and arms; there are propellers at the ends of the arms to take off and rotors that rotate them. By reducing the angle between mechanism 1 and the rotors with the horizontal plane, the angle between mechanism 2 and the arms, the rotors rise and different configurations are obtained. Conventional multi-rotor aircraft has a fixed fuselage and does not need a tail rotor to change course as helicopters do. The translational and rotational movements are provided by the rotation of the rotors of the aircraft at different speeds by creating moments about the geometric center in 6-degree-of-freedom (DOF) space. These commands sent from the ground are provided by the flight control board in the aircraft. The longitudinal and lateral flight stability and properties of different configurations evaluated by dynamic analysis and simulations in 6 DOF spaces are investigated. An algorithm and PID controller are being developed using SPSA to achieve in-flight position and attitude control of an active deformable aircraft. The results are compared with the results of the literature review and the results of the previous article.

Findings

With SPSA, the best PID coefficients were obtained in case of morphing.

Research limitations/implications

The effects of quadrotor arm height and hub angle changes affect flight stability. With the SPSA optimization method presented in this study, the attitude is quickly stabilized.

Practical implications

With the optimization method, the most suitable PID coefficients and angle values for the lateral and longitudinal flight stability of the quadrotor are obtained.

Social implications

The transition rate and PID coefficients are determined by using the optimization method, which is advantageous in terms of cost and practicality.

Originality/value

With the proposed method, the aircraft can change shape to adapt to different environments, and the parameters required for more stable flight for each situation will be calculated, and this will be obtained more quickly and safely with the SPSA optimization method.

Details

Aircraft Engineering and Aerospace Technology, vol. 95 no. 10
Type: Research Article
ISSN: 1748-8842

Keywords

Access Restricted. View access options
Article
Publication date: 16 March 2022

Hüseyin Şahin, Oguz Kose and Tugrul Oktay

This study aims to optimize autonomous performance (i.e. both longitudinal and lateral) and endurance of the quadrotor type aerial vehicle simultaneously depending on the…

239

Abstract

Purpose

This study aims to optimize autonomous performance (i.e. both longitudinal and lateral) and endurance of the quadrotor type aerial vehicle simultaneously depending on the autopilot gain coefficients and battery weight.

Design/methodology/approach

Quadrotor design processes are critical to performance. Unmanned aerial vehicle durability is an important performance parameter. One of the factors affecting durability is the battery. Battery weight, energy capacity and discharge rate are important design parameters of the battery. In this study, proper autopilot gain coefficients and battery weight are obtained by using a stochastic optimization method named as simultaneous perturbation stochastic approximation (SPSA). Because there is no direct correlation between battery weight and battery energy density, artificial neural network (ANN) is benefited to obtain battery energy density corresponding to resulted battery weight found from SPSA algorithm. By using the SPSA algorithm optimum performance index is obtained, then obtained data is used for longitudinal and lateral autonomous flight simulations.

Findings

With SPSA, the best proportional integrator and derivative (PID) coefficients and battery weight, energy efficiency and endurance were obtained in case of morphing.

Research limitations/implications

It takes a long time to find the most suitable battery values depending on quadrotor endurance. However, this situation can be overcome with the proposed SPSA.

Practical implications

It is very useful to determine quadrotor endurance, PID coefficients and morphing rate using the optimization method.

Social implications

Determining quadrotor endurance, PID coefficients and morphing rate using the optimization method provides advantages in terms of time, cost and practicality.

Originality/value

The proposed method improves quadrotor endurance. In addition, with the SPSA optimization method and ANN, the parameters required for endurance will be obtained faster and more securely. In addition, the energy density according to the battery weight also contributes to the clean environment and energy efficiency.

Details

Aircraft Engineering and Aerospace Technology, vol. 94 no. 8
Type: Research Article
ISSN: 1748-8842

Keywords

Access Restricted. View access options
Article
Publication date: 5 June 2024

Oguz Kose

This study aims to discuss the simultaneous longitudinal and lateral flight control of the octorotor, a rotary wing unmanned aerial vehicle (UAV), for the first time under the…

95

Abstract

Purpose

This study aims to discuss the simultaneous longitudinal and lateral flight control of the octorotor, a rotary wing unmanned aerial vehicle (UAV), for the first time under the effect of morphing and to improve autonomous flight performance.

Design/methodology/approach

This study aims to design and control the octorotor flight control system with stochastic optimal tuning under morphnig effect. For this purpose, models of different arm lengths of the octorotor were drawn in the Solidworks program. The morphing was carried out by simultaneously lengthening or shortening the arm lengths of the octorotor. The morphing rate was estimated by using simultaneous perturbation stochastic approximation (SPSA). The stochastic gradient descent algorithm, which is frequently used in machine learning, was used to estimate the changing moments of inertia with the change of arm lengths. The proportional integral derivative (PID) controller has been preferred as an octorotor control algorithm because of its simplicity of structure. The PID gains required to control both longitudinal and lateral flight were also estimated with SPSA.

Findings

With SPSA, three longitudinal flight PID gains, three lateral flight PID gains and one morphing ratio were estimated. PID gains remained within the limits set for SPSA, giving satisfactory results. In addition, the cost index created was 93% successful. The gradient descent algorithm used for the moment of inertia estimation achieved the optimum result in 1,570 iterations. However, in the simulations made with the obtained data, longitudinal and lateral flight was successfully carried out.

Originality/value

Octorotor longitudinal and lateral flight control was performed quickly and effectively with the proposed method. In addition, the desired parameters were obtained with the optimization methods used, and the longitudinal and lateral flight of the octorotor was successfully carried out in the desired trajectory.

Details

Aircraft Engineering and Aerospace Technology, vol. 96 no. 5
Type: Research Article
ISSN: 1748-8842

Keywords

Access Restricted. View access options
Article
Publication date: 13 February 2023

Oguz Kose and Tugrul Oktay

The purpose of this paper is to optimize the simultaneous flight performance of a hexarotor unmanned aerial vehicle (UAV) by using simultaneous perturbation stochastic…

251

Abstract

Purpose

The purpose of this paper is to optimize the simultaneous flight performance of a hexarotor unmanned aerial vehicle (UAV) by using simultaneous perturbation stochastic approximation (i.e. SPSA), deep neural network and proportional integral derivative (i.e. PID) according to varying arm length (i.e. morphing).

Design/methodology/approach

In this paper, proper PID gain coefficients and morphing ratio were obtained using the stochastic optimization method, also known as SPSA to maximize flight efficiency. Because it is difficult to establish an analytical connection between the morphing ratio and hexarotor moments of inertia, the deep neural network was used to obtain the moments of inertia according to the morphing ratio. By using SPSA and deep neural network, the best performance indexes were obtained and both longitudinal and lateral flight simulations were performed with the obtained data.

Findings

With SPSA, the best PID coefficients and morphing ratio are obtained for both longitudinal and lateral flight. Because the hexarotor solid body model changes according to the morphing ratio, the moment of inertia values used in the simulations also change. According to the morphing ratio, the moment of inertia values was obtained with the deep neural network over a created data set.

Research limitations/implications

It takes a long time to obtain the morphing ratio suitable for the hexarotor model and the PID gain coefficients suitable for this morphing ratio. However, this situation can be overcome with the proposed SPSA. In addition, it takes a long time to obtain the appropriate moments of inertia according to the morphing ratio. However, in this case, it was overcome using the deep neural network.

Practical implications

Determining the morphing ratio and PID gain coefficients using the optimization method, as well as determining the moments of inertia using the deep neural network, is very useful as it can increase the efficiency of hexarotor flight and flight efficiently with different arm lengths. With the proposed method, the hexarotor design performance criteria (i.e. rise time, settling time and overshoot) values were significantly improved compared to similar studies.

Social implications

Determining the hexarotor flight parameters using SPSA and deep neural network provides advantages in terms of time, cost and applicability.

Originality/value

The hexarotor flight efficiency is improved with the proposed SPSA and deep neural network approaches. In addition, the desired flight parameters can be obtained more quickly and reliably with the proposed approaches. The design performance criteria were also improved, enabling the hexarotor UAV to follow the given trajectory in the best way and providing convenience for end users. SPSA was preferred because it converged faster than other methods. While other methods perform 2n operations per iteration, SPSA only performs two operations. To obtain the moment of inertia, many physical parameter values of the UAV are required in the existing methods. In the proposed method, by creating a date set, only arm length and moment of inertia were estimated without the need to obtain physical parameters with the deep neural network structure.

Details

Aircraft Engineering and Aerospace Technology, vol. 95 no. 6
Type: Research Article
ISSN: 1748-8842

Keywords

Access Restricted. View access options
Article
Publication date: 11 June 2020

Oguz Kose and Tugrul Oktay

The purpose of this paper is to design a quadrotor with collective morphing using the simultaneous perturbation stochastic approximation (SPSA) optimization algorithm.

402

Abstract

Purpose

The purpose of this paper is to design a quadrotor with collective morphing using the simultaneous perturbation stochastic approximation (SPSA) optimization algorithm.

Design/methodology/approach

Quadrotor design is made by using Solidworks drawing program and some mathematical performance relations. Modelling and simulation are performed in Matlab/Simulink program by using the state space model approaches with the parameters mostly taken from Solidworks. Proportional integral derivative (PID) approach is used as control technique. Morphing amount and the best PID coefficients are determined by using SPSA algorithm.

Findings

By using SPSA algorithm, the amount of morphing and the best PID coefficients are determined, and the quadrotor longitudinal and lateral flights are made most stable via morphing.

Research limitations/implications

It takes quite a long time to model the quadrotor in Solidworks and Matlab/Simulink with the state space model and using the SPSA algorithm. However, this situation is overcome with the proposed model.

Practical implications

Optimization with SPSA is very useful in determining the amount of morphing and PID coefficients for quadrotors.

Social implications

SPSA optimization method is useful in terms of cost, time and practicality.

Originality/value

It is released to improve performance with morphing, to determine morphing rate with SPSA algorithm and to determine PID coefficients accordingly.

Details

Aircraft Engineering and Aerospace Technology, vol. 92 no. 7
Type: Research Article
ISSN: 1748-8842

Keywords

Access Restricted. View access options
Article
Publication date: 31 May 2022

Mehmet Numan Kaya, Oguz Uzol, Derek Ingham, Faruk Köse and Riza Buyukzeren

The purpose of this paper is to thoroughly investigate the aerodynamic effects of blade pitch angle on small scaled horizontal axis wind turbines (HAWTs) using computational fluid…

440

Abstract

Purpose

The purpose of this paper is to thoroughly investigate the aerodynamic effects of blade pitch angle on small scaled horizontal axis wind turbines (HAWTs) using computational fluid dynamics (CFD) method to find out the sophisticated effects on the flow phenomena and power performance.

Design/methodology/approach

A small HAWT is used as a reference to validate the model and examine the aerodynamic effects. The blade pitch angle was varied between +2 and −6 degrees, angles which are critical for the reference wind turbine in terms of performance, and the CFD simulations were performed at different tip speed ratio values, λ = 2, 3, 4, 5, 6, 7, 9 and 10.5 to cover the effects in various conditions. Results are examined in two different aspects, namely, general performance and the flow physics.

Findings

The power performance varies significantly according to the tip speed ratio; the power coefficient increases up to a certain pitch angle at the design tip speed ratio (λ = 6); however, between λ = 2 and 4, the more the blade is pitched downwards, the larger is the power coefficient, the smaller is the thrust coefficient. Similarly, for tip speed ratios higher than λ = 8, the positive effect of the low pitch angles on the power coefficient at λ = 6 reverses. The flow separation location moves close to the leading edge at low tip speed ratios when the blade is pitched upwards and the also tip vortices become more intense. In conclusion, the pitch control can significantly contribute to the performance of small HAWTs depending on different conditions.

Originality/value

In the literature, only very little attention has been paid to the aerodynamic effects of pitch angle on HAWTs, and no such study is available about the effects on small HAWTs. The change of blade pitch angle was maintained at only one degree each time to capture even the smallest aerodynamic effects, and the results are presented in terms of the power performance and flow physics.

Details

International Journal of Numerical Methods for Heat & Fluid Flow, vol. 33 no. 1
Type: Research Article
ISSN: 0961-5539

Keywords

Access Restricted. View access options
Article
Publication date: 1 March 2016

Ömer Erem and Selen Abbasoğlu Ermiyagil

This paper aims to define an adapted contemporary design language for housing built next to vernacular residential buildings of Anatolian villages. The case has been selected from…

68

Abstract

This paper aims to define an adapted contemporary design language for housing built next to vernacular residential buildings of Anatolian villages. The case has been selected from Balıkesir province in the North-western part of Anatolia within a corpus of 104 houses from selected 81 villages of the region. Originally, vernacular house plans consist of allocation of rooms around a hall: sofa. Each room is a core living space with everyday living needs for a family. House is formed with various spatial relations between sofa and rooms around it. This relation is the determinative feature in formation of vernacular language for each Anatolian house. The study has three phases: analysis, adaptation and generation. The first phase analyzes the elements of vernacular by decomposing its language into sub-parts. In the second phase, the inadequacies of existing vernacular structures were exposed with methods of observation and questionnaires applied on users and new demands for living have been adapted with vernacular existing language grammar rules. In the last phase within the framework of adapted language rules for Balıkesir vernacular, numerous novel design alternatives were generated. This study claims to sustain the existing socio-cultural spatial configuration by adapting newly built contemporary houses to actual vernacular architecture in the planning context.

Details

Open House International, vol. 41 no. 1
Type: Research Article
ISSN: 0168-2601

Keywords

Access Restricted. View access options
Article
Publication date: 1 November 2018

Umer Jeelanie Banday and Ranjan Aneja

The purpose of this paper is to find out the relationship between energy consumption, economic growth and CO2 emissions for the G7 countries over the period 1971–2014. The second…

937

Abstract

Purpose

The purpose of this paper is to find out the relationship between energy consumption, economic growth and CO2 emissions for the G7 countries over the period 1971–2014. The second intent of the paper is to make a comparison whether it is renewable energy consumption, non-renewable energy consumption, or both that determine sustainable economic growth in G7 countries.

Design/methodology/approach

The authors testify the relationship among energy consumption, economic growth and CO2 emissions using numerous econometric techniques. The authors have applied pooled mean group autoregressive distribution model (ARDL) for long-run and short-run relationships for individual countries. Finally, the authors have applied Granger causality testing based on Dumitrescu and Hurlin (2012) and Emirmahmutoglu and Kose’s (2011) approach in order to check the causal relationship between energy consumption and economic growth, CO2 emission and economic growth and vice versa.

Findings

However, energy usage is a greater concern due to the increase in imported energy prices. With this preposition, new thinking needs to be carried out for energy usage and sustainable economic growth. The authors consider cross-sectional reliance and cross-country heterogeneity for seven developed countries. The tests utilized in this investigation include the bootstrap causality approach of Dumitrescu and Hurlin (2012) and LA–VAR approach of Toda and Yamamoto (1995) that permits testing the causality for every individual panel individuals independently. However, not very many empirical works bring these two separate streams of writing together to analyze the causal connections between energy consumption, economic growth and CO2 emission for G7 countries.

Originality/value

However, energy usage is a greater concern due to the increase in imported energy prices. Meanwhile, the exhaustive use of fossil fuels increases emission level which leads to climate change, global warming, reduction in agriculture productivity and danger to human life. With this preposition, new thinking needs to be carried out for energy usage and sustainable economic growth. There are limited number of studies addressing energy consumption, economic growth and CO2 emission relationship. This study employs different methodology to find out the relationship among the variables.

Details

World Journal of Science, Technology and Sustainable Development, vol. 16 no. 1
Type: Research Article
ISSN: 2042-5945

Keywords

Available. Content available
Book part
Publication date: 4 July 2019

Abstract

Details

Contemporary Issues in Behavioral Finance
Type: Book
ISBN: 978-1-78769-881-9

Available. Open Access. Open Access

Abstract

Details

Journal of Intelligent Manufacturing and Special Equipment, vol. 4 no. 1
Type: Research Article
ISSN: 2633-6596

1 – 10 of 14
Per page
102050