Simulation-based dynamic model and speed controller design of a small-scale turbojet engine

2018 ◽  
Vol 90 (2) ◽  
pp. 351-358 ◽  
Author(s):  
Isil Yazar ◽  
Emre Kiyak ◽  
Fikret Caliskan ◽  
T. Hikmet Karakoc
Keyword(s):  
Mathematical Model ◽  
Controller Design ◽  
Small Scale ◽  
Performance Parameters ◽  
Nonlinear Mathematical Model ◽  
Content Type ◽  
Speed Controller ◽  
Turbojet Engine ◽  
Anfis Method ◽  
Operating Points

Purpose This paper aims to present a nonlinear mathematical model of a small-scale turbojet aeroengine and also a speed controller design that is conducted for the constructed nonlinear mathematical model. Design/methodology/approach In the nonlinear mathematical model of the turbojet engine, temperature, rotational speed, mass flow, pressure and other parameters are generated using thermodynamic equations (e.g. mass, energy and momentum conservation laws) and some algebraic equations. In calculation of the performance parameters, adaptive neuro fuzzy inference system (ANFIS) method is preferred in related components. All calculated values from the mathematical model are then compared with the cycle data of the turbojet engine. Because of the single variable control need and effect of noise factor, modified proportional–integral–derivative (PID) controller is treated for speed control. For whole operation envelope, various PID structures are designed individually, according to the operating points. These controller structures are then combined via gain-scheduling approach and integrated to the nonlinear engine model. Simulations are performed on MATLAB/Simulink environment for design and off-design operating points between idle to maximum thrust levels. Findings The cascade structure (proposed nonlinear engine aero-thermal model and speed controller) is simulated and tested at various operating points of the engine and for different transient conditions. Simulation results show that the transitions between the operating points are found successfully. Furthermore, the controller is effective for steady-state load changes. It is suggested to be used in real-time engine applications. Research limitations/implications Because of limited data, only speed control is treated and simulated. Practical implications It can be used as an application in the industry easily. Originality/value First point of novelty in the paper is in calculation of the performance parameters of compressor and turbine components. ANFIS method is preferred to predict performance parameters in related components. Second novelty in the paper can be seen in speed controller design part. Because of the single variable control need and effect of noise factor, modified PID is treated.

scholarly journals IMC Multi-Controller Strategies applied on a Manipulator Robot

2017 ◽  
Vol 2 (1) ◽  
pp. 51-62
Author(s):  
Y. Zennir ◽  
E. Guechi ◽  
L. Chetioui ◽  
R. Bendib
Keyword(s):  
Controller Design ◽  
Parametric Models ◽  
Nonlinear Mathematical Model ◽  
Lqg Control ◽  
Robot Wrist ◽  
Simulation Results ◽  
Solid Works ◽  
3D Solid ◽  
Operating Points ◽  
Manipulator Robot

The paper focuses on the use of multi-controller approach to control a robot wrist (STÄUBLI robot RX 90). The descriptions of a nonlinear mathematical model of the process have been presented with the local parametric models around operating points. Controller design of a conventional PID, IMC control, LQG control and Hv (loop shaping) has been described around each selected operating points for each local parametric models. Finally , in order to show the efficiency of the proposed method, some simulation results in CAO 3D solid-works and MATLAB environments are given.

Large amplitude bending behaviour of laminated composite curved panels

2016 ◽  
Vol 33 (1) ◽  
pp. 116-138 ◽  
Author(s):  
Trupti Ranjan Mahapatra ◽  
Vishesh Ranjan Kar ◽  
Subrata Kumar Panda
Keyword(s):  
Mathematical Model ◽  
Numerical Model ◽  
Laminated Composite ◽  
Higher Order ◽  
Design Parameters ◽  
Nonlinear Mathematical Model ◽  
Flexural Behaviour ◽  
Content Type ◽  
Curved Panel ◽  
Laminated Structures

Purpose – The purpose of this paper is to analyse the nonlinear flexural behaviour of laminated curved panel under uniformly distributed load. The study has been extended to analyse different types of shell panels by employing the newly developed nonlinear mathematical model. Design/methodology/approach – The authors have developed a novel nonlinear mathematical model based on the higher order shear deformation theory for laminated curved panel by taking the geometric nonlinearity in Green-Lagrange sense. In addition to that all the nonlinear higher order terms are considered in the present formulation for more accurate prediction of the flexural behaviour of laminated panels. The sets of nonlinear governing equations are obtained using variational principle and discretised using nonlinear finite element steps. Finally, the nonlinear responses are computed through the direct iterative method for shell panels of various geometries (spherical/cylindrical/hyperboloid/elliptical). Findings – The importance of the present numerical model for small strain large deformation problems has been demonstrated through the convergence and the comparison studies. The results give insight into the laminated composite panel behaviour under mechanical loading and their deformation behaviour. The effects of different design parameters and the shell geometries on the flexural responses of the laminated curved structures are analysed in detailed. It is also observed that the present numerical model are realistic in nature as compared to other available mathematical model for the nonlinear analysis of the laminated structure. Originality/value – A novel nonlinear mathematical model is developed first time to address the severe geometrical nonlinearity for curved laminated structures. The outcome from this paper can be utilized for the design of the laminated structures under real life circumstances.

A neural network model for UAV propulsion system

2020 ◽  
Vol 92 (8) ◽  
pp. 1177-1184
Author(s):  
Gültekin Işık ◽  
Selçuk Ekici ◽  
Gökhan Şahin
Keyword(s):  
Neural Network ◽  
Neural Networks ◽  
Network Model ◽  
Neural Network Model ◽  
Propulsion System ◽  
Performance Parameters ◽  
Ann Model ◽  
Content Type ◽  
Fuel Flow ◽  
Turbojet Engine

Purpose Determining the performance parameters of the propulsion systems of the aircraft, which is the key product of the aviation industry, plays a critical role in reducing adverse environmental impacts. Therefore, the purpose of this paper is to present a temperature performance template for turbojet engines at the design stage using a neural network model that defines the relationship between the performance parameters obtained from ground tests of a turbojet engine used in unmanned aerial vehicles (UAV). Design/methodology/approach The main parameters of the flow passing through the engine of the UAV propulsion system, where ground tests were performed, were obtained through the data acquisition system and injected into a neural network model created. Fifteen sensors were mounted on the engine – six temperature sensors, six pressure sensors, two flow meters and one load cell were connected to the data acquisition system to make sense of this physical environment. Subsequently, the artificial neural network (ANN) model as a complement to the approach was used. Thus, the predicted model relationship with the experimental data was created. Findings Fuel flow and thrust parameters were estimated using these components as inputs in the feed-forward neural network. In the network experiments to estimate fuel flow parameter, r-square and mean absolute error were calculated as 0.994 and 0.02, respectively. Similarly, for thrust parameter, these metrics were calculated as 0.994 and 1.42, respectively. In addition, the correlation between fuel flow, thrust parameters and each input parameters was examined. According to this, air compressor inlet (ACinlet,temp) and outlet (ACoutlet,temp) temperatures and combustion chamber (CCinlet,temp, CCoutlet,temp) temperature parameters were determined to affect the output the most. The proposed ANN model is applicable to any turbojet engines to model its behavior. Practical implications Today, deep neural networks are the driving force of artificial intelligence studies. In this study, the behavior of a UAV is modeled with neural networks. Neural networks are used here as a regressor. A neural network model has been developed that predicts fuel flow and thrust parameters using the real parameters of a UAV turbojet engine. As a result, satisfactory findings were obtained. In this regard, fuel flow and thrust values of any turbojet engine can be estimated using the neural network hyperparameters proposed in this study. Python codes of the study can be accessed from https://github.com/tekinonlayn/turbojet. Originality/value The originality of the study is that it reports the relationships between turbojet engine performance parameters obtained from ground tests using the neural network application with open source Python code. Thus, small-scale unmanned aerial propulsion system provides designers with a template showing the relationship between engine performance parameters.

Study of a Four Rotor Aircraft Modeling

2014 ◽  
Vol 494-495 ◽  
pp. 293-296
Author(s):  
Yang Jin Xian ◽  
Li Zhi Peng ◽  
Chen Chao
Keyword(s):  
Mathematical Model ◽  
Attitude Control ◽  
Controller Design ◽  
Simplified Model ◽  
Linear Motion ◽  
Motion Model ◽  
Nonlinear Mathematical Model ◽  
Attitude Control System ◽  
Linearization Principle ◽  
The Mathematical Model

In order to design the four rotor aircraft attitude control system, take the hover state or low speed flight state as a benchmark, firstly, divide the aircraft model into linear motion model and the angular motion model and model it separately, the nonlinear mathematical model of aircraft can be obtained. And then use the small disturbance linearization principle to linear mathematical model for a simplified model. After substituting into the previous experimental data, the mathematical model which controller design needs is got.

scholarly journals Linear Mathematical Model for State-Space Representation of Small Scale Turbojet Engine with Variable Exhaust Nozzle

2017 ◽  
Vol 46 (1) ◽  
pp. 1 ◽  
Author(s):  
Károly Beneda ◽  
Rudolf Andoga ◽  
Ladislav Főző
Keyword(s):  
Mathematical Model ◽  
State Space ◽  
Nozzle Geometry ◽  
Space Representation ◽  
Small Scale ◽  
Linear Quadratic ◽  
Convergent Nozzle ◽  
State Space Representation ◽  
Turbojet Engine ◽  
Engine Components

The goal of this article is to develop a linear mathematical model for a small scale turbojet engine with variable convergent nozzle, and validate it on existing laboratory hardware owned by the authors’ Departments.Control of gas turbine engines plays an essential role in the safety of aviation. Although its role is constantly expanding, ranging from pilot workload reduction to detailed diagnostics, the basic competence is to regulate the thrust output of the power plant with maximum available accuracy, rapidity, stability, and robustness. The linear quadratic control is one possible solution for the above mentioned criteria.Although civil aircraft engines include fixed exhaust nozzle geometry, in military applications the exhaust nozzle geometry is also adjustable to reach optimum efficiency due to better matching of individual engine components, etc.In the present article the authors deduce the members of state space governing equations to acquire the basis of the LQ control.The established model is based on the physical laws describing the operational behavior of the engine as well as its complexity should be reduced to an acceptable level where still enough details remain to reflect the nature of the controlled object.

An innovative method for exhaust gases toxicity evaluation in the miniature turbojet engine

2017 ◽  
Vol 89 (6) ◽  
pp. 757-763 ◽  
Author(s):  
Bartosz Gawron ◽  
Tomasz Białecki ◽  
Anna Janicka ◽  
Aleksander Górniak ◽  
Maciej Zawiślak
Keyword(s):  
Respiratory System ◽  
Direct Method ◽  
Small Scale ◽  
Gas Mixture ◽  
Toxicity Evaluation ◽  
Content Type ◽  
Exhaust Gases ◽  
Turbojet Engine ◽  
Human Respiratory System

Purpose The purpose of this paper is to present an assessment method of the toxicity emission evaluation during combustion in the miniature turbojet engine. Design/methodology/approach A small-scale turbojet engine was used for the research because measurements on real aircraft turbines are complex and expensive. The experiment was performed in accordance with innovative BAT – CELL Bio – Ambient Cell method which consists of determination of virtual toxic impact of the gas mixture on the living cells; it is therefore a direct method. The most significant innovation of this method is that, during the test, which consists of exposing the cells to the gas mixture, the cells are deprived of culture fluid. Findings The preliminary analysis shows that the method used here allows to determine the virtual impact of the gases on the human respiratory system and skin. It could be useful in defining the arduousness of an airport. The obtained results show that both of exhaust gases represent similar toxicity. Practical implications The new in vitro method allows to determine the virtual impact of the gases on the human respiratory system and skin. Significant potential for further research not only on the miniaturised engines, but also in the case of real objects, as this method does not have to be performed in a laboratory. Originality/value The work presents potential application of the innovatory method for exhaust gases toxicity evaluation in jet engines, which could be useful in defining the arduousness of an airport.

Modelling and Comparison of Compressor Performance Parameters by Using ANFIS

2014 ◽  
Vol 1016 ◽  
pp. 710-715 ◽  
Author(s):  
Isil Yazar ◽  
Emre Kiyak ◽  
Hasan Serhan Yavuz
Keyword(s):  
Mathematical Model ◽  
Fuzzy Inference System ◽  
Fuzzy Inference ◽  
Aircraft Engine ◽  
Performance Parameters ◽  
Nonlinear Mathematical Model ◽  
Inference System ◽  
Compressor Performance ◽  
Compressor Map ◽  
Map Data

Developing a robust control algorithm for an aircraft engine requires an accurate nonlinear mathematical model. In formation of a nonlinear mathematical model, some components like compressor and turbine are modeled by using component maps. These maps show the connection between the compressor performance parameters. To show this connection, map data is digitized by using some techniques. In this study, we digitized a compressor map data by using ANFIS (Adaptive Neuro Fuzzy Inference System). RMSE (Root Mean Square Error) were calculated for different types of FIS (Fuzzy Inference System) structures constructed with different number of membership functions. The model was formed by using all valid data which is collected from a small turboprop engine compressor. Results demonstrate that the designed ANFIS structure can serve as an alternative model to estimate both online and offline compressor performance parameters.

Performance monitoring and analysis of various parameters for a small UAV turbojet engine

2018 ◽  
Vol 90 (5) ◽  
pp. 779-787 ◽  
Author(s):  
Emre Kiyak ◽  
Gulay Unal ◽  
Nilgun Fazilet Ozer
Keyword(s):  
Performance Monitoring ◽  
Engine Performance ◽  
Real Data ◽  
Point Of View ◽  
Performance Parameters ◽  
Engine Operation ◽  
Content Type ◽  
Turbojet Engine ◽  
Engine Industry ◽  
Aerial Vehicle

Purpose This paper aims to discuss engine health monitoring for unmanned aerial vehicles. It is intended to make consistent predictions about the future status of the engine performance parameters by using their current states. Design/methodology/approach The aim is to minimize risks before they turn into problems. In accordance with these objectives, temporal and financial savings are planned to be achieved by contributing processes such as extending the engine life, preventing early disassembly-reassembly and mechanical wears and reducing the maintenance costs. Based on this point of view, a data-based software is developed in MATLAB (Matrix Laboratory) program for the so-called process. Findings The software is operated for the performance parameters of the turbojet engine that is used in a small unmanned aerial vehicle of Tusas Engine Industry. The obtained results are compared with the real data of the engine. As a result of this comparison, a fault that may occur in the engine can be detected before being determined. Originality/value It is clearly demonstrated that the engine operation in adverse conditions can be prevented. This situation means that the software developed operates successfully.

Simulation-based steady-state aero-thermal model for small-scale turboprop engine

2017 ◽  
Vol 89 (2) ◽  
pp. 203-210 ◽  
Author(s):  
Isil Yazar ◽  
Tolga Yasa ◽  
Emre Kiyak
Keyword(s):  
Steady State ◽  
Large Scale ◽  
Controller Design ◽  
Complex Structure ◽  
Fuzzy Model ◽  
Aircraft Engine ◽  
Operating Conditions ◽  
Small Scale ◽  
Content Type ◽  
Turboprop Engine

Purpose An aircraft engine control system consists of a large scale of control parameters and variables because of the complex structure of aero-engine. Monitoring and adjusting control variables and parameters such as detecting, isolating and reconfiguring the system faults/failures depend on the controller design. Developing a robust controller is based on an accurate mathematical model. Design/methodology/approach In this study, a small-scale turboprop engine is modeled. Simulation is carried out on MATLAB/Simulink for design and off-design operating conditions. Both steady-state and transient conditions (from idle to maximum thrust levels) are tested. The performance parameters of compressor and turbine components are predicted via trained Neuro-Fuzzy model (ANFIS) based on component maps. Temperature, rotational speed, mass flow, pressure and other parameters are generated by using thermodynamic formulas and conservation laws. Considering these calculated values, error calculations are made and compared with the cycle data of the engine at the related simulation conditions. Findings Simulation results show that the designed engine model’s simulation values have acceptable accuracy for both design and off-design conditions from idle to maximum power operating envelope considering cycle data. The designed engine model can be adapted to other types of gas turbine engines. Originality/value Different from other literature studies, in this work, a small-scale turboprop engine is modeled. Furthermore, for performance prediction of compressor and turbine components, ANFIS structure is applied.

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