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

Yazar, Işıl; Yasa, Tolga; Kiyak, Emre

doi:10.1108/aeat-02-2015-0062

Cited by 7 publications

(4 citation statements)

References 24 publications

(38 reference statements)

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“…An aircraft control system consists of a large scale of control parameters and variables because of the complex structure of this system. Monitoring and adjusting control variables and parameters such as detecting, isolating and reconfiguring the system faults/failures depend on the flight control design (Yazar et al , 2017a, 2017b).…”

Section: Simulation Resultsmentioning

confidence: 99%

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Integrated design of fault-tolerant control for flight control systems using observer and fuzzy logic

Unal

2021

AEAT

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Purpose Fault detection, isolation and reconfiguration of the flight control system is an important problem to obtain healthy flight. This paper aims to propose an integrated approach for aircraft fault-tolerant control. Design/methodology/approach The integrated structure includes a Kalman filter to obtain without noise, a full order observer for sensor fault detection, a GOS (generalized observer scheme) for sensor fault isolation and a fuzzy controller to reconfigure of the healthy sensor. This combination is simulated using the state space model of a lateral flight control system in case of disturbance and under sensor fault scenario. Findings Using a dedicated observer scheme, the detection and time of sensor fault are correct, but the sensor fault isolation is evaluated incorrectly while the faulty sensor is isolated correctly using GOS. The simulation results show that the suggested approach works affectively for sensor faults with disturbance. Originality/value This paper proposes an integrated approach for aircraft fault-tolerant control. Under this framework, three units are designed, one is Kalman filter for filtering and the other is GOS for sensor fault isolation and another is fuzzy logic for reconfiguration. An integrated approach is sensitive to faults that have disturbances. The simulation results show the proposed integrated approach can be used for any linear system.

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Section: Simulation Resultsmentioning

confidence: 99%

“…Here, they preferred a linearized model of a jet engine for simulation. Because of the unknown input observer, fault is detected and by using the GOS, the isolation process is conducted and decision-making of related backup sensor is defined via Boolean (Yazar et al, 2017a(Yazar et al, , 2017b.…”

Section: Fault-tolerant Control Designmentioning

confidence: 99%

Integrated design of fault-tolerant control for flight control systems using observer and fuzzy logic

Unal

2021

AEAT

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“…The heat transfer outside the engine is neglected and the engine is assumed to be adiabatic. During the nonlinear model construction process, the steps are mentioned in Yazar et al (2017) are followed.…”

Section: Theoretical Backgroundmentioning

confidence: 99%

“…The key point in designing a robust controller for an aircraft engine is highly related to an accurate nonlinear mathematical model. An accurate nonlinear mathematical model reduces costs of real engine tests before manufacturing and also estimates important unmeasured controlled variables like turbine inlet temperature, thrust and so on as well (Yazar, 2015; Yazar et al , 2017; Bazazzadeh et al , 2009).…”

Section: Introductionmentioning

confidence: 99%

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

Yazar

Kiyak

Çalışkan

et al. 2018

AEAT

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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.

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A new online modelling method for aircraft engine state space model

Pang

Zhang

2020

Chinese Journal of Aeronautics

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

Cited by 7 publications

References 24 publications

Integrated design of fault-tolerant control for flight control systems using observer and fuzzy logic

Integrated design of fault-tolerant control for flight control systems using observer and fuzzy logic

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

A new online modelling method for aircraft engine state space model

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