Turbojet Engine Industrial Min–Max Controller Performance Improvement Using Fuzzy Norms

Jafari, Soheil; Nikolaidis, Theoklis

doi:10.3390/electronics7110314

Cited by 15 publications

(19 citation statements)

References 34 publications

(45 reference statements)

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“…where a i , b i are the constant coefficients. The structure of Equation (15) was selected according to the experimental results in [33]. For this reason, within the entire operating speed range, the dynamic behavior of MTE can be approximately described by a set of second-order models.…”

Section: Model Identificationmentioning

confidence: 99%

“…Each model can be identified by using step input and step response measurements corresponding to a specific speed range. We employ the tfest function in MATLAB to estimate the transfer function in Equation (15). Table 2 shows the identified parameters of the engine within the operating range from 51,900 to 70,800 RPM.…”

Section: Model Identificationmentioning

confidence: 99%

“…In [11], the genetic algorithms are employed to optimize the parameters in the fuzzy logic controller so that the controller can meet the performance requirements and safety constraints. In [15], the fuzzy norms are used to improve Min-Max controller performance for turbojet engine. In addition, the linear model is considered in [16] and stability analysis is performed for a Min-Max multi-regulator system.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Single Neural Adaptive PID Control for Small UAV Micro-Turbojet Engine

Wei

Wang

et al. 2020

Sensors

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The micro-turbojet engine (MTE) is especially suitable for unmanned aerial vehicles (UAVs). Because the rotor speed is proportional to the thrust force, the accurate speed tracking control is indispensable for MTE. Thanks to its simplicity, the proportional–integral–derivative (PID) controller is commonly used for rotor speed regulation. However, the PID controller cannot guarantee superior performance over the entire operation range due to the time-variance and strong nonlinearity of MTE. The gain scheduling approach using a family of linear controllers is recognized as an efficient alternative, but such a solution heavily relies on the model sets and pre-knowledge. To tackle such challenges, a single neural adaptive PID (SNA-PID) controller is proposed herein for rotor speed control. The new controller featuring with a single-neuron network is able to adaptively tune the gains (weights) online. The simple structure of the controller reduces the computational load and facilitates the algorithm implementation on low-cost hardware. Finally, the proposed controller is validated by numerical simulations and experiments on the MTE in laboratory conditions, and the results show that the proposed controller achieves remarkable effectiveness for speed tracking control. In comparison with the PID controller, the proposed controller yields 54% and 66% reductions on static tracking error under two typical cases.

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Section: Model Identificationmentioning

confidence: 99%

Section: Model Identificationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Single Neural Adaptive PID Control for Small UAV Micro-Turbojet Engine

Wei

Wang

et al. 2020

Sensors

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“…The triple loop control system architecture is shown in Figure 6. Limiters and the engine protection logic is not considered, but can be added in any of the loops using the min-max methodology or others [25,26,27]. The inner-most feedback loop controls the fuel flow supply into the engine by computing the pulse width modulated (PWM) signal controlling the fuel pump with control law defined as follows:…”

Section: Controller Designmentioning

confidence: 99%

Virtual Design of Advanced Control Algorithms for Small Turbojet Engines

Főző¹

2019

ACTA POLYTECH HUNG

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Advanced control in the area of turbojet engines defines many different applied complex control strategies. Highly theoretical approaches and designs are often presented in this area. The article is aimed at practical aspects of adaptive controller design for a class of small turbojet engines in triple loop control architecture. The article presents a non-linear dynamic model of a small turbojet engine taking in account the environmental conditions, which it operates in. The designed triple loop control architecture shows increased precision of control keeping acceleration schedule of the simulated engine and is not susceptible to outer disturbances. The article shows pilot dynamic simulation tests, showing feasibility of the taken approach. It can also be used for other classes of turbojet engines as well other similar technical systems.

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“…This strategy is known as a practical algorithm to satisfy all engine control modes simultaneously without any error and malfunction [1,2]. Results of the design and implementation of the min-max controller were presented within the Basic Research in Industrial Technologies for Europe-Europe/America (BRITE-EURAM) project OBIDICOTE (On Board Identification, Diagnosis and Control of gas Turbine Engines) and confirmed by all OBIDICOTE partners [3,4]. Therefore, this strategy is the most practical control method for gas turbine engines [5][6][7].…”

Section: Introductionmentioning

confidence: 99%

Advanced Constraints Management Strategy for Real-Time Optimization of Gas Turbine Engine Transient Performance

Nikolaidis¹,

Li²,

Jafari³

2019

Applied Sciences

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Motivated by the growing technology of control and data processing as well as the increasingly complex designs of the new generation of gas turbine engines, a fully automatic control strategy that is capable of dealing with different aspects of operational and safety considerations is required to be implemented on gas turbine engines. An advanced practical control mode satisfaction method for the entire operating envelope of gas turbine engines is proposed in this paper to achieve the optimal transient performance for the engine. A constraint management strategy is developed to generate different controller settings for short-range fighters as well as long-range intercontinental aircraft engines at different operating conditions by utilizing a model predictive control approach. Then, the designed controller is tuned and modified with respect to different realistic considerations including the practicality, physical limitations, system dynamics, and computational efforts. The simulation results from a verified two-spool turbofan engine model and controller show that the proposed method is capable of maneuverability and/or fuel economy optimization indices while satisfying all the predefined constraints successfully. Based on the parameters, natural frequencies, and dynamic behavior of the system, a set of optimized weighting factors for different engine parameters is also proposed to achieve the optimal and safe operation for the engine at different flight conditions. The paper demonstrates the effects of the prediction length and control horizon; adding new constraints on the computational effort and the controller performance are also discussed in detail to confirm the effectiveness and practicality of the proposed approach in developing a fully automatic optimized real-time controller for gas turbine engines.

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Turbojet Engine Industrial Min–Max Controller Performance Improvement Using Fuzzy Norms

Cited by 15 publications

References 34 publications

Single Neural Adaptive PID Control for Small UAV Micro-Turbojet Engine

Single Neural Adaptive PID Control for Small UAV Micro-Turbojet Engine

Virtual Design of Advanced Control Algorithms for Small Turbojet Engines

Advanced Constraints Management Strategy for Real-Time Optimization of Gas Turbine Engine Transient Performance

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