Reduction of supersonic jet noise - Application to the Ariane 5 launch vehicle

Gely, D.; Elias, G.; Bresson, C.; Foulon, Henri; Radulovic, S.; Roux, P.

doi:10.2514/6.2000-2026

Cited by 29 publications

(16 citation statements)

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“…It has been reported that the water injection system deployed by NASA and ESA for their launch pads can attenuate the sound levels by 8-12 dB [24][25][26][27][28][29][30][31][32]. The optimal injection parameters were generated based on studies with cold and hot gas models.…”

Section: Introductionmentioning

confidence: 99%

“…A series of studies on hot and cold gas models were conducted at the Martel facility of the Centre National d'Etudes Spatiale in Poitiers, France and the facility at the Ecole Centrale de Lyon in Ecully Cedex, France, to find to find the optimal water injection parameters for implementation in launch pads [27][28][29][30][31][32]. Zoppelari and Juvé [31,32] used an MFR of 3-4.…”

Section: Introductionmentioning

confidence: 99%

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Suppression of High Mach Number Rocket Jet Noise by Water Injection

Sankaran¹,

Ignatius²,

Ramkumar³

et al. 2009

Journal of Spacecraft and Rockets

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The present work experimentally investigates suppression of the sound level from an underexpanded jet of Mach number 2.8 by water injection. The jet is produced by a solid rocket motor being static test fired. Water is injected from a radial distance of 5.2 jet diameters, at different axial locations from the exit of the nozzle, at two different angles of injection relative to the downstream jet axis. The ratio of mass flow rates of water to the nozzle exhaust gas (referred to as the mass flow rate ratio) and the injection pressure are varied independently. Acoustic measurements are performed at a radius of 30 jet diameters, over angles in the range of 30-130 deg, relative to the downstream jet axis. Sound levels continuously decrease by 10 dB with the increase in the angle of observation. With water injection, higher levels of reduction in sound are observed in the upstream quadrant. Injection closer to the nozzle exit leads to better reduction, mainly due to suppression in the high-frequency range when observed from downstream, but it is almost in the entire frequency range as observed at the upstream locations. At intermediate mass flow rate ratios, an optimum injection pressure exists for maximum noise suppression, due to the penetration of water to the potential core and its evaporation there at high injection pressures. The results affirm that the validity of many past studies obtained on water injection to suppress noise levels on simulated jets can be extended to an actual rocket situation.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Suppression of High Mach Number Rocket Jet Noise by Water Injection

Sankaran¹,

Ignatius²,

Ramkumar³

et al. 2009

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…Such result also supports the design of the launch pad to attenuate acoustic level at lift-off. [13,15] …”

Section: Introductionmentioning

confidence: 99%

“…Since each test at the MARTEL facility can be conducted easily, the flame duct and water injection system are designed. [13,14] Recently, phased array having several tens of microphones is used to identify the acoustic source distribution. Such result also supports the design of the launch pad to attenuate acoustic level at lift-off.…”

Section: Introductionmentioning

confidence: 99%

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

Tsutsumi

Ishii

et al. 2015

Journal of Spacecraft and Rockets

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“…A lot of work has been done to minimize the impact of the noise produced during the launch on devices under the fairing (Gely et al, 2000;Defosse, Hamdi, 2000;Chemoul et al, 2001). Noise level generated by the venting system on the ground does not exceed 94 dB.…”

Section: Introductionmentioning

confidence: 99%

Acoustic Simulation’s Verification of WFI ATHENA Filterwheel Assembly

Pilch

Kamisiński

Rataj

et al. 2017

Archives of Acoustics

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Ariane 5 rocket produces very high sound pressure levels during launch, what can influence structures located in the fairing. To reduce risk of damage, launch in vacuum conditions is preferred for noise sensitive instruments. In Wide Filed Imager (WFI) project, the main part of the filterwheel assembly is an extremely thin (∼240 nm) filter of large area (170 × 170 mm), very sensitive to noise and vibrations.The aim of this study was to verify numerical calculations results in anechoic measurements. The authors also checked the influence of WFI geometry and sound absorbing material position on sound pressure level (SPL) affecting the filter mounted inside the assembly. Finite element method (FEM) simulations were conducted in order to obtain noise levels in filter position during Ariane 5 rocket launch. The results will be used in designing of WFI filterwheel assembly and endurance of the filter during launch verification.

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Reduction of supersonic jet noise - Application to the Ariane 5 launch vehicle

Cited by 29 publications

References 0 publications

Suppression of High Mach Number Rocket Jet Noise by Water Injection

Suppression of High Mach Number Rocket Jet Noise by Water Injection

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

Acoustic Simulation’s Verification of WFI ATHENA Filterwheel Assembly

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