CFD analysis of unsteady ignition overpressure effects on Delta II and III launch vehicles

Pavish, D.; Deese, J.

doi:10.2514/6.2000-3922

Cited by 6 publications

(5 citation statements)

References 5 publications

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“…One of the main conclusions drawn by the authors is the importance of afterburning for determining the IOP amplitude. Three-dimensional simulations based on Euler's equations for a gas-phase reacting flow were performed by Pavish and Deese [13] on Delta II and III launchers on their pads to estimate unsteady loads and by Engblom et al [14] for a nonreacting flow. Majamaki and Lee [15] used the unsteady Reynolds-averaged Navier-Stokes equations, written for a nonreacting flow and closed by a k-ω turbulence model on two configurations of Delta IV vehicles, with an overall good agreement between flight data and numerical results.…”

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confidence: 99%

Numerical Study of Solid-Rocket Motor Ignition Overpressure Wave Including Infrared Radiation

Dargaud

Troyes

Lamet

et al. 2014

Journal of Propulsion and Power

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The ignition overpressure wave generated during the pressure build-up of a solid-rocket motor is numerically investigated in this study. Numerical simulations are compared to the LP10 experiments, consisting of the horizontal firing of a scaled-down model for the Ariane 5 P230 booster. The present work aims at the prediction of the main characteristics of the ignition overpressure in the far field and the assessment of afterburning influence on both its formation mechanisms and its alteration by the jet plume. Two three-dimensional large-eddy simulations are performed, one considering inert flow and one modeling the afterburning. Infrared images of the plume are also computed with a dedicated radiation transfer solver. An overall good agreement with the experimental results is reported on amplitude and duration. Nevertheless, the reactive case is found to provide better results on amplitude and directivity. The signature is also better reproduced on the microphones near the jet centerline, and the emitted infrared intensity is well captured. Computations indicate that the formation of the shock wave is obtained by coalescence of compression waves emitted by the accelerating jet at early times. For the reactive case, computations show an increased interaction between the jet and the overpressure wave. Nomenclature A = area, m 2 a = ellipse x-axis length, m b = ellipse y-axis length, m C s = sth far-field microphone c = speed of sound, m · s −1 D = diameter, m e = eccentricity h = infrared field height, m I = acoustic intensity, W k = absorption index l = infrared field length, m M = Mach number m = alumina complex refraction index n = refraction index p = pressure, Pa R = shock traveled distance, m t = time, ms u = velocity, m · s −1 x, y, z = Cartesian coordinates α = far-field microphone angle, deg γ = ratio of specific heats Δp = shock amplitude, Pa Δt = time step, s Δx = maximal grid cell size, mm δ = duration, s λ = wavelength, m ρ = density, kg · m −3 Subscripts 0 = isotropic shock initial characteristics atm = atmospheric conditions bu = properties at rupture instant em = properties at ignition overpressure emission instant i = stagnation value ini = simulation initial characteristics int = shock tube intermediate properties iop = ignition overpressure properties ir = infrared properties j = nozzle exit plane properties le = ignition overpressure leading front arrival time max = ignition overpressure pressure maximum nl = ignition overpressure nonlinear propagation predicted time prop = propellant properties s = far-field sensor index st = shock-tube properties theo = ideal seal rupture characteristics at sensor location tr = ignition overpressure trailing front arrival time Superscript = nozzle throat properties

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mentioning

confidence: 99%

Numerical Study of Solid-Rocket Motor Ignition Overpressure Wave Including Infrared Radiation

Dargaud

Troyes

Lamet

et al. 2014

Journal of Propulsion and Power

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“…Both subscale experiments and CFD were recently used in the development process of the Ares I [8,9]. All previous studies based on CFD employed the conventional second-order method for both space and time evaluations [3,[5][6][7]9,11]. Because the pressure wave of IOP wave has a large amplitude with low frequency compared with aeroacoustics, the second-order method may be sufficient for resolving the IOP.…”

Section: Introductionmentioning

confidence: 99%

“…Because the pressure wave of IOP wave has a large amplitude with low frequency compared with aeroacoustics, the second-order method may be sufficient for resolving the IOP. Ignition overpressure features are basically dominated by the inviscid features of fluid dynamics, so full Euler equations are used for the governing equations [5][6][7]. The unsteady Reynolds averaged Navier-Stokes (URANS) equations [3], hybrid RANS and largeeddy simulation (LES) [9], and pure LES [11] have also been employed in previous studies.…”

Section: Introductionmentioning

confidence: 99%

“…Only experimental and theoretical works from the early days of space development are available [1,2,4]. In the late 1990s, computational fluid dynamics (CFD) began being applied [3,[5][6][7]9,11]. Both subscale experiments and CFD were recently used in the development process of the Ares I [8,9].…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, much research is being devoted to it for the development of launch vehicles, such as the Ariane 5, and Ares I [1][2][3][4][5][6][7][8][9][10]. Only experimental and theoretical works from the early days of space development are available [1,2,4].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Analysis of Ignition Overpressure Effect on H-IIB Launch Vehicle

Tsutsumi¹,

Takaki²,

Hara³

et al. 2014

Journal of Spacecraft and Rockets

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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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CFD analysis of unsteady ignition overpressure effects on Delta II and III launch vehicles

Cited by 6 publications

References 5 publications

Numerical Study of Solid-Rocket Motor Ignition Overpressure Wave Including Infrared Radiation

Numerical Study of Solid-Rocket Motor Ignition Overpressure Wave Including Infrared Radiation

Numerical Analysis of Ignition Overpressure Effect on H-IIB Launch Vehicle

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

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