Experimental study on the tuned operation of a free piston driver

Tanno, Hideyuki; Itoh, Katsuhiro; Komuro, Tomoyuki; Sato, K.

doi:10.1007/s001930050174

Cited by 19 publications

(12 citation statements)

References 6 publications

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“…Using the theory derived by Ref. 12, the 36 kg piston with a 76.2 mm orifice plate (the original shock tube dimension for T3) should fall into the soft impact region ensuring the usefulness of the condition (Figure 10). …”

Section: Iiia Free Piston Drivermentioning

confidence: 99%

T6: The Oxford University Stalker Tunnel

McGilvray¹,

Doherty²,

Morgan³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The University of Oxford has embarked on developing the UKs fastest wind tunnel, T6, in collaboration with the University of Queensland (Australia) using technology pioneered by the late Professor Ray Stalker. The T6 facility couples the ex-Australian National University T3 free piston driver to the barrels, nozzles and test section of the Oxford gun tunnel. The facility can operate in three different modes; as a shock tube, a reflected shock tunnel or as an expansion tunnel. The T6 facility will be unique to Europe allowing for hypervelocity ground testing not possible in any current EU facilities, whilst having the flexibility to conduct tests across a large range of speeds and binary scaling products (ρL) of interest.

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Section: Iiia Free Piston Drivermentioning

confidence: 99%

T6: The Oxford University Stalker Tunnel

McGilvray¹,

Doherty²,

Morgan³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…22 The basic characteristics of geometry and initial conditions are shown in Table 2. The offered data were mainly about the pressure histories at the end of the compression tube B, so the comparisons were focused in the pressure values.…”

Section: Validation Of Modelmentioning

confidence: 99%

Simulation study on modeling for design parameters analysis of free-piston tunnels

Feng

Chang

Yang

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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A dynamic model was designed and developed using thermodynamic mass conservation equation, energy conservation equation, flow equation of nozzle and motion equation for moving piston and design parameter analysis of free-piston tunnels was proposed. The proposed model was validated by comparing the predictions made with the dynamic model established with the experimental data reported in some of the references and used to run simulation. Simulation results indicated that the target pressure and temperature could be quickly obtained by selecting and adjusting design parameters with the proposed model while the pressure and temperature output of the reservoir were kept long stable with a pneumatic hydraulic driving device. The time domain conditions of free-piston wind tunnel could be established through numerical study at different gas source pressure. The pressure and temperature of reservoir could be obtained by adjusting the valve opening of gas source. The variable specific heat ratio has a remarkable effect on the performance of free-piston wind tunnel. For the variable specific heat ratio, the temperature and pressure of reservoir was lower than the constant specific heat ratio. It was therefore concluded that the proposed model was suitable for performing the design parameter analysis of free-piston wind tunnels, and so, it could be used to facilitate the design of free-piston wind tunnels for long working at high Mach number.

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“…When the current set of tuned X2 driver conditions (two of which are shown in Table 1) were designed by Gildfind et al, 36,55 a maximum driver pressure of 40 MPa was set due to structural limits of the facility. 55 Considering that tuned conditions generally have an over-pressure after diaphragm rupture, 47,[56][57][58] it was decided by Gildfind et al 36,55 to set the maximum diaphragm rupture pressure to 35.7 MPa, which can be seen as the most powerful driver condition shown in Table 1.…”

Section: Actual X2 Performance Limitsmentioning

confidence: 99%

Generating High Speed Earth Re-entry Test Conditions in an Expansion Tube for Interplanetary Return Missions

James¹,

Lewis²,

Gildfind³

et al. 2019

Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019)

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In 2010, planetary entry probe missions to Uranus and Saturn were proposed. This paper details an investigation exploring the operating limits of the X2 superorbital expansion tube at the University of Queensland for the simulation of test conditions related to these proposed entries. Theoretical calculations showed that X2 could recreate the stagnation enthalpy of the proposed 22.3 km/s Uranus entry but not the stagnation enthalpy of the proposed 26.9 km/s Saturn entry. Experiments were able to confirm the theoretical performance calculations. However, losses caused some of the experimental shock speeds to be up to 10% slower than predicted, and due to the high velocity nature of the experiments, the shock speed errors were large making it difficult to properly quantify the test conditions. Further theoretical analysis investigated the possibility of using a more powerful free piston driver to simulate the Saturn entry conditions, and the analysis showed that with a slightly more powerful driver than X2's current most powerful configuration, the stagnation enthalpy of the proposed Saturn entry or other slightly faster entries proposed in the literature could be simulated. However, a very powerful driver would be required to recreate the stagnation enthalpies of these entries with the excess enthalpy needed to perform binary scaled experiments for an X2 sized facility.

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Experimental study on the tuned operation of a free piston driver

Cited by 19 publications

References 6 publications

T6: The Oxford University Stalker Tunnel

T6: The Oxford University Stalker Tunnel

Simulation study on modeling for design parameters analysis of free-piston tunnels

Generating High Speed Earth Re-entry Test Conditions in an Expansion Tube for Interplanetary Return Missions

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