Study on Acoustic Prediction and Reduction of Epsilon Launch Vehicle at Liftoff

Tsutsumi, Seiji; Ishii, Tatsuya; Ui, Kyoichi; Tokudome, Shinichiro; Wada, Kazumi

doi:10.2514/1.a33010

Cited by 33 publications

(26 citation statements)

References 37 publications

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“…Acoustic testing is conducted using a 2.4%-scaled solid motor that is designed based on the requirements to predict a full-scale environment. 7) The jet conditions of the solid motor are listed in Table 1. The exhaust velocity of the jet is designed to have the same value as the full-scale solid motor used in the Japanese H-IIA, H-IIB, and Epsilon launchers.…”

Section: Acoustic Testsmentioning

confidence: 99%

“…Then, acoustic measurements using 2.5-10%scale models are conducted for the detailed design and to predict the full-scale acoustic environments. [3][4][5][6][7] However, it is hard to determine the mechanism of acoustic generation using the empirical method and subscale measurements. The lack of understanding generation of the acoustics results in difficulty to devise an acoustic reduction technique.…”

Section: Introductionmentioning

confidence: 99%

“…Then, in the detailed design phase, a hybrid of the LES and Reynolds averaged Navier-Stokes (RANS) method coupled with a 2.4%-scale model test was utilized to determine details of the configuration and predict full-scale acoustic levels. 7) The numerical method is now utilized as one of the tools applied in the acoustic design of launch pads. However, quantitative prediction of the acoustic level using the numerical method is still a challenge, and subscale model testing is inevitable for the detailed design phase at this moment.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Validation and Verification of a Numerical Prediction Method for Lift-off Acoustics of Launch Vehicles

Tsutsumi

Terashima

2017

AEROSPACE TECHNOLOGY JAPAN

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To predict harmful acoustic loading due to the intense acoustic waves generated by exhaust jets from propulsion systems of launch vehicles during lift-off, a numerical method based on computational fluid dynamics is developed. High-fidelity large-eddy simulations, or hybrid large-eddy and Reynolds-averaged Navier-Stokes simulations are employed for the computation of the hydrodynamic field. Computational aeroacoustic simulations based on full-Euler equations are applied to compute acoustic propagation to the farfield. Validation and verification studies are conducted using experimental results of free and impinging jets from a 2.4%-scale solid motor. It is found that the prediction accuracy with approximately 4 dB in overall sound-pressure level is obtained for both the free and impinging jets.

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Section: Acoustic Testsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Validation and Verification of a Numerical Prediction Method for Lift-off Acoustics of Launch Vehicles

Tsutsumi

Terashima

2017

AEROSPACE TECHNOLOGY JAPAN

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“…1) One of the most successful examples was the application to the epsilon rocket launched in 2014. The launch site, designed based on the simulation results by LES, 2) achieved the reduction of the acoustic level more than 10 dB compared with the previous launch of the M-V rocket. The success of the epsilon rocket showed the capability of qualitative prediction of the acoustic waves from the rocket plume.…”

Section: Introductionmentioning

confidence: 99%

Computational Analysis of Compressible Gas-Particle-Multiphase Turbulent Mixing Layer in Euler-Euler Formulation

Terakado

Nagata

Nonomura

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Effects of solid particles in the gas-particle multiphase compressible turbulent mixing layer were investigated by direct numerical simulation, compared with the single phase turbulent mixing layer of which the net density ratio (sum of gas and particle densities) was set to be the same as the multiphase case. Here, the situation of solid rocket motor was considered, so that the Mach number and the density (temperature) ratio were set to be high and far from unity, respectively, and the solid particles were distributed only in one side of the mixing layer for the initial condition. Three-dimensional compressible gas-particle-multiphase Navier-Stokes equations in the Euler-Euler formulation were solved with an alternative weighted essentially non-oscillatory scheme with a positivity preserving limiter of the particle density for the multiphase flow computation. It was found that the existence of solid particles leads to the sparse structures of turbulence and suppresses the fine scale turbulent structures, especially for the JET side, which corresponds to the side where particles were initially distributed and the gas density was low. The growth rate of the mixing layer thickness for multiphase flow became smaller due to the change in flow. The change in flow structures also affected the properties of acoustic waves. The Mach wave like structures do not appear for the initially particle existing side for the multiphase flow due to the suppression of fine scale turbulent structures, compared with single phase flow.

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“…However, more accurate and reliable prediction is required to construct a new rocket launch site more safely. Various numerical studies have been conducted to realize qualitative prediction [2][3][4] until now. In real largescale liquid launch vehicles, generated acoustic waves are suppressed by water injection.…”

Section: Introductionmentioning

confidence: 99%

A Simple Immersed Boundary Method for Compressible Flow Simulation around a Stationary and Moving Sphere

Mizuno

Takahashi

Nonomura

et al. 2015

Mathematical Problems in Engineering

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This study is devoted to investigating a flow around a stationary or moving sphere by using direct numerical simulation with immersed boundary method (IBM) for the three-dimensional compressible Navier-Stokes equations. A hybrid scheme developed to solve both shocks and turbulent flows is employed to solve the flow around a sphere in the equally spaced Cartesian mesh. Drag coefficients of the spheres are compared with reliable values obtained from highly accurate boundary-fitted coordinate (BFC) flow solver to clarify the applicability of the present method. As a result, good agreement was obtained between the present results and those from the BFC flow solver. Moreover, the effectiveness of the hybrid scheme was demonstrated to capture the wake structure of a sphere. Both advantages and disadvantages of the simple IBM were investigated in detail.

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Study on Acoustic Prediction and Reduction of Epsilon Launch Vehicle at Liftoff

Cited by 33 publications

References 37 publications

Validation and Verification of a Numerical Prediction Method for Lift-off Acoustics of Launch Vehicles

Validation and Verification of a Numerical Prediction Method for Lift-off Acoustics of Launch Vehicles

Computational Analysis of Compressible Gas-Particle-Multiphase Turbulent Mixing Layer in Euler-Euler Formulation

A Simple Immersed Boundary Method for Compressible Flow Simulation around a Stationary and Moving Sphere

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