Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems

Large, James; Pesyridis, Apostolos

doi:10.3390/aerospace6050055

Cited by 29 publications

(12 citation statements)

References 2 publications

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“…Naturally, the system must be checked for observability, whether the required information can be gained by other measurable parameters. Hence, one must carry out another assessment of observability, which requires a different assumption for output matrix, instead of the one published in (9), namely, the two measurable variables n and p t4 are considered as outputs, from which the unknown parameter can be estimated. The corresponding C obs can be seen in (20) in a transposed form for better layout only.…”

Section: Discussion Of Conducted Investigationsmentioning

confidence: 99%

“…The measurement was carried out in multiple steps, thus the engine can sufficiently be stabilized in each different operating mode. At each stable operating regime the main parameters have been evaluated in order to obtain the matrix members as shown in (7) to (9). Matrix D is excluded as the system does not have a direct feed forward behavior.…”

Section: Lpv Model Of the Turbojetmentioning

confidence: 99%

“…Turbojet engines, even if their utilization has reduced in commercial aviation during the past decades due to their comparably less propulsive efficiency [4], still have a role in different propulsion systems. There is an increasing interest in Unmanned Aerial Vehicles (UAV's) in the past decade [5], which has led to a considerable interest in developing micro turbojet engines, as stated in [6,7] or [8], because these engines can be applied on military UAV's, which can include high-speed aircraft (as shown in [9]), where the turbojet already provides fair propulsive efficiency. Meanwhile, there is an ever-increasing interest in radio-controlled model airplanes that imitate real aircraft in civil sector as already reported by [10], and these devices are becoming more attractive [11].…”

Section: Introductionmentioning

confidence: 99%

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Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

Derbel

Beneda

2020

Energies

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The interest in turbojet engines was emerging in the past years due to their simplicity. The purpose of this article is to investigate sliding mode control (SMC) for a micro turbojet engine based on an unconventional compound thermodynamic parameter called Turbofan Power Ratio (TPR) and prove its advantage over traditional linear methods and thrust parameters. Based on previous research by the authors, TPR can be applied to single stream turbojet engines as it varies proportionally to thrust, thus it is suitable as control law. The turbojet is modeled by a linear, parameter-varying structure, and variable structure sliding mode control has been selected to control the system, as it offers excellent disturbance rejection and provides robustness against discrepancies between mathematical model and real plant as well. Both model and control system have been created in MATLAB® Simulink®, data from real measurement have been taken to evaluate control system performance. The same assessment is conducted with conventional Proportional-Integral-Derivative (PID) controllers and showed the superiority of SMC, furthermore TPR computation using turbine discharge temperature was proven. Based on the results of the simulation, a controller layout is proposed and its feasibility is investigated. The utilization of TPR results in more accurate thrust output, meanwhile it allows better insight into the thermodynamic process of the engine, hence it carries an additional diagnostic possibility.

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Section: Discussion Of Conducted Investigationsmentioning

confidence: 99%

Section: Lpv Model Of the Turbojetmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

Derbel

Beneda

2020

Energies

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“…The turbojet engine is recognized as a powerful candidate propulsion system for unmanned aerial vehicles (UAVs) [1]. In the past decade, owing to the extremely high thrust-to-weight ratio, small-sized turbojet engines, especially micro-turbojet engines, are becoming attractive for the application in UAVs or remotely-controlled airplanes.…”

Section: Introductionmentioning

confidence: 99%

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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“…Ukrainian and global manufacturers offer gas-turbine engines for UAVs of various types [1][2][3][4]. While full-scale turboprops and turbofans, as a rule, are based on engines designed for manned aircraft, small turbofans ( Figure 1) have original structure [5][6][7], which is determined by the tactical and technical characteristics of the platform [8].…”

Section: Introductionmentioning

confidence: 99%

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

Павленко¹,

Dvirnyk²,

Przysowa³

2020

Preprint

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BACKGROUND: Manufacturing costs, along with operational performance, are among the major factors determining the selection of the propulsion system for unmanned aerial vehicles (UAVs), especially for aerial targets and cruise missiles. OBJECTIVES: In this paper, the design requirements and operating parameters of small turbofan engines for single-use and reusable UAVs are analysed to introduce alternative materials and technologies for manufacturing their compressor blades, such as sintered titanium, a new generation of aluminium and an alloy based on titanium aluminides. METHODS: To assess the influence of severe plastic deformation (SPD) on the hardening efficiency of the proposed materials, the alloys in the coarse-grained and submicrocrystalline states were studied. Changes in physical and mechanical properties of materials were taken into account. The thermodynamic analysis of the compressor was performed in a finite element analysis system (ANSYS) to determine the impact of gas pressure and temperature on the aerodynamic surfaces of compressor blades of all stages. RESULTS: Based on thermal and structural analysis, the stress and temperature maps on compressor blades and vanes were obtained, taking into account the physical and mechanical properties of advanced materials and technologies of their processing. The safety factors of the components were established based on the assessment of their stress-strength reliability. Thanks to nomograms, the possibility of using the new materials and the technologies was confirmed in view of the permissible operating temperature and safety factors of blades. CONCLUSIONS: The proposed alternative materials and production technologies for the compressor blades and vanes meet the design requirements of the turbofan at lower manufacturing costs.

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Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems

Cited by 29 publications

References 2 publications

Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

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

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

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