Intelligent Controller Design for a Blowdown Supersonic Wind Tunnel

Shahrbabaki, Amin Nazarian; Bazazzadeh, Mehrdad; Shahriari, Ali; Manshadi, Mojtaba Dehghan

doi:10.14257/ijca.2014.7.1.37

Cited by 5 publications

(7 citation statements)

References 12 publications

(11 reference statements)

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“…It is previously noted that the stagnation temperature drops according to the polytropic process in the storage tank. In this regard, Figure 10 shows the temperature drops during the wind tunnel run without heater for a Mach 2.5 run [1].…”

Section: Simulation Resultsmentioning

confidence: 99%

“…Thus, to maintain a constant plenum pressure as close as possible to a setpoint pressure signal, the regulator or control valve must open progressively. Besides, to maintain a constant stagnation temperature in the plenum chamber, a heater must operate continuously during a supersonic run [1][2][3]. The controller must operate at different stagnation pressures and Mach numbers and has to be robust to accommodate the varying pressure and mass flow requirements safely.…”

Section: Introductionmentioning

confidence: 99%

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Enhancing the Supersonic Wind Tunnel Performance Based on Plenum Temperature Control

Shahrbabaki

Bazazzadeh

Shahriari

et al. 2014

ISRN Aerospace Engineering

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The application of fuzzy logic controllers (FLCs) to the control of nonlinear processes, typically controlled by a human operator, is a topic of much study. In this paper, the design and application of a FLC is discussed to control the plenum chamber temperature for a blowdown supersonic wind tunnel (BSWT) with the aim of achieving the accurate and desired results. In this regard, first, a nonlinear mathematical model of special BSWT is developed in Matlab/Simulink software environment. Next, an artificially intelligent controller is designed using fuzzy logic approach. For this purpose, a proportional-derivative FLC (PD-FLC) system is developed in the Simulink toolbox to control the plenum stagnation temperature using a heater upstream of the plenum chamber. Finally, the system simulation results inside of the temperature and pressure controllers in comparison with the experimental run are presented. The results for Mach 2.5 blowdown run show the great performance of the Wind Tunnel Simulator Model and its temperature controller system.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Enhancing the Supersonic Wind Tunnel Performance Based on Plenum Temperature Control

Shahrbabaki

Bazazzadeh

Shahriari

et al. 2014

ISRN Aerospace Engineering

Self Cite

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“…The mathematical model (9) -(12) is based on assumptions that there is no energy loss and that air behaves as a perfect gas [5]. However, the finite filling time of the settling chamber is taken into account by expressions (11) and (12). Even for high storage tank pressure, the settling chamber pressure will not have an appreciable rise for the first half-second to second of operation [6].…”

Section: Mathematical Model For the Wind Tunnelmentioning

confidence: 99%

“…The value of K determines the point at which the valve becomes unchocked. Both chocked and unchocked flow across the valve are included in the mathematical model (9) - (12).…”

Section: Mathematical Model For the Wind Tunnelmentioning

confidence: 99%

“…The accuracy of 0.1% is indicated, but at the cost of higher complexity of these controllers, as well as complicated adjusting procedure during the training stage. In [12], an artificial neural network is used for finding the optimum membership functions of the fuzzy logic controller, but experiments with the identified controller demonstrated large wind tunnel starting pressure overshoots.…”

Section: Introductionmentioning

confidence: 99%

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Model-based stagnation pressure control in a supersonic wind tunnel

Ilić¹,

Miloš²,

Milosavljević³

et al. 2016

FME Transaction

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The flow parameters control in wind tunnels is an area of intense research in recent years, with the aim of improving quality and efficiency of the wind tunnel operation. In this paper, an attempt is made to contribute to a better understanding of the stagnation pressure control in supersonic blowdown-type facilities. The stagnation pressure control strategy in the VTI Belgrade T-38 wind tunnel is discussed. An improved mathematical model for a supersonic wind tunnel is suggested and applied to the T-38 facility. Comparisons of simulation and experimental data are made to demonstrate accurate prediction of the facility response in supersonic flow conditions by the mathematical model. The model is used to incorporate a modified feedforward control in the original T-38 wind tunnel control system. The actual wind tunnel tests confirm model-predicted decrease of flow stabilization time and increase of available measurement time, bringing significant improvement in the wind tunnel operation efficiency.

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