Identification of Overpressure Sources at Launch Vehicle Liftoff Using an Inverse Method

Troclet, Bernard; Alestra, Stephane; Terrasse, I.; JeanJean, S.; Srithammavanh, Vassili

doi:10.2514/1.21577

Cited by 6 publications

(7 citation statements)

References 6 publications

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“…For h aer α ≫ 1, the transmission coefficient is smaller than predicted by Eqs. (6)(7)(8). However, in the frequency range of interest for the IOP and the width of aerosol layers, h aer ∼ 0.1 m, the wavelength in the aerosol is much larger than the width of the layer, h aer ≪ λ aer .…”

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersmentioning

confidence: 96%

“…Therefore, h aer α ≫ 1 implies λ aer α ≫ 1, which implies that the wave is strongly reflected, and jR fine aer j > 1 − jT fine aer j for jT fine aer j as predicted by Eqs. (6)(7)(8). In the following analysis, attenuation will be neglected for the fine aerosols, meaning that the predicted reflection should be considered as a lower bound on the actual reflection.…”

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersmentioning

confidence: 99%

“…The second reason why the resonances do not effect the IOP wave transmission is that Eqs. (6)(7)(8) are obtained for monochromatic acoustic waves, whereas the IOP pulses are characterized by a finite spectral width. To calculate the transmitted pulse for h aer 0.1 m and f L 0.15, the transmission Figure 5a shows the incident (curve 1) and the transmitted IOP wave obtained from the ANSYS simulations with droplets (curve 2) and theoretically (curve 3), using the transmission coefficient of an appropriate mist layer.…”

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersmentioning

confidence: 99%

“…T fine aer 4c g c aer ρ g ρ aer c g ρ g c aer ρ aer 2 exp−ik aer h aer −c g ρ g −c aer ρ aer 2 expik aer h aer (6) where…”

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersunclassified

“…Remarkably, it is found that various a priori reasonable designs of the aerosol and water sprays may increase the ignition overpressure impact on the vehicle, increasing the risk of vehicle damage. [1][2][3][4][5][6][7][8]. The IOP wave may propagate toward the vehicle and potentially inflict vehicle damage or result in the vehicle's shifting from the nominal position.…”

mentioning

confidence: 99%

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Mitigation of Solid Booster Ignition over Pressure by Water Aerosol Sprays

Осипов

Khasin

Hafiychuk

et al. 2015

Journal of Spacecraft and Rockets

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Interaction of acoustic waves with water aerosol layers is analyzed in the context of the problem of solid booster ignition overpressure suppression. In contrast to the conventional approach to ignition overpressure suppression, which aims at using water to quench the sources of the ignition overpressure waves, this study focuses on blocking the ignition overpressure wave propagation, using reflection and attenuation of the wave by the water aerosol layers. The study considers interaction of the waves with aerosol layers of large mass loading for varying sizes of the droplets. The size of the droplets is shown to substantially affect the mechanisms of interaction with the waves. The criteria for the crossover between different mechanisms are established as functions of the droplet size and the ignition overpressure wave parameters. The optimal parameters and designs for water aerosol sprays are proposed that maximize the ignition overpressure suppression. These results were obtained using the nozzle and the exhaust hole geometries similar to those of the space shuttle. Remarkably, it is found that various a priori reasonable designs of the aerosol and water sprays may increase the ignition overpressure impact on the vehicle, increasing the risk of vehicle damage. Nomenclature C D = drag coefficient C P = specific heat at constant pressure, J∕kg∕K c = sound velocity, m∕s d drop = droplet diameter, m f L = liquid volume fraction h = layer width, m j = mass flux, kg∕m 2 ∕s k = wave vector, 1∕m L D = thermodiffusion length, m M = million p = fluid pressure, Pa R g = gas constant, J∕kg∕K r drop = droplet radius, m T = fluid temperature, K T aer = transmission coefficient T wave = period of acoustic wave, s t = time, s u = gas velocity, m∕s α = attenuation coefficient, m −1 κ = thermal conductivity, W∕m∕K λ = wavelength, m μ = dynamic viscosity, Pa · s ν = frequency, Hz ρ = fluid mass density, kg∕m 3 σ = surface tension, N∕m σ st = Stefan-Boltzmann constant τ = typical time, s ω = angular frequency Subscripts aer = aerosol drop = droplet G = gas ign = ignition L = liquid s = surface, saturation v = vapor w = water 0 = initial state

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Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersmentioning

confidence: 96%

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersmentioning

confidence: 99%

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersmentioning

confidence: 99%

“…T fine aer 4c g c aer ρ g ρ aer c g ρ g c aer ρ aer 2 exp−ik aer h aer −c g ρ g −c aer ρ aer 2 expik aer h aer (6) where…”

Section: B Interaction Of Acoustic Waves With Fine Aerosol Layersunclassified

mentioning

confidence: 99%

See 3 more Smart Citations

Mitigation of Solid Booster Ignition over Pressure by Water Aerosol Sprays

Осипов

Khasin

Hafiychuk

et al. 2015

Journal of Spacecraft and Rockets

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High-fidelity simulations of the aeroacoustic environment of the VEGA launch vehicle at lift-off

et al. 2023

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Supersonic jet noise from launch vehicles: 50 years since NASA SP-8072

Lubert

Gee

Tsutsumi

2022

The Journal of the Acoustical Society of America

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In 1971, the U.S. National Aeronautics and Space Administration (NASA) published a seminal report—NASA SP-8072—which compiled the results of the early supersonic jet noise studies and provided methods to calculate the noise produced from launch vehicles. Fifty years later and despite known limitations, SP-8072 remains the foundation for much of the launch vehicle noise modeling today. This article reviews what has been learned about the physics of noise generation and radiation from free and impinging rocket plumes since the completion of SP-8072. State-of-the-art methods for the mitigation of launch vehicle noise are also reviewed. A discussion of launch vehicle noise modeling, from empirical to numerical and including reduced-order models of supersonic jets, points to promising approaches that can describe rocket noise characteristics not captured by SP-8072.

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Identification of Overpressure Sources at Launch Vehicle Liftoff Using an Inverse Method

Cited by 6 publications

References 6 publications

Mitigation of Solid Booster Ignition over Pressure by Water Aerosol Sprays

Mitigation of Solid Booster Ignition over Pressure by Water Aerosol Sprays

High-fidelity simulations of the aeroacoustic environment of the VEGA launch vehicle at lift-off

Supersonic jet noise from launch vehicles: 50 years since NASA SP-8072

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