Acoustic Measurement and Prediction of Solid Rockets in Static Firing Tests

Fukuda, Kota; Tsutsumi, Seiji; Fujii, Kozo; Ui, Kyoichi; Oinuma, Hideshi; Kazawa, Junichi; Minesugi, Kenji

doi:10.2514/6.2009-3368

Cited by 25 publications

(20 citation statements)

References 6 publications

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“…One is a static test using full-scale rocket motors [4][5] and the other took advantage of sub-scale motors 6) . Both tests were conducted at JAXA's Noshiro Rocket Test Center.…”

Section: Previous Tests Using Full and Sub-scale Rocket Motorsmentioning

confidence: 99%

Acoustic Measurement of 1:42 Scale Booster and Launch Pad

Ishii

Tsutsumi

et al. 2014

Proceedings of Meetings on Acoustics

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This paper describes the acoustic measurement of the sub-scale booster and launch pad. The 1:42 scale solid propellant booster was settled over the launch pad model on a flat plate. Designed to deflect the hot and high speed jet plume, the launch pad model was expected to mitigate acoustic impact fed back toward the vehicle. The launch pad model plays a role in attenuating the sound due to the impingement of the plume and the deflector. To investigate the acoustic field with a different booster height, acoustic measurement was carried out. The measurement involved the conventional acoustic measurement and the sound source localization. The conventional measurement employed the near-field microphones around the booster model and the far-field microphones on an arc centered on the base of the launch pad. In the sound source localization, a phased array microphone system was settled to focus the deflector exit. The obtained acoustic data helped revise the design of the launch pad model.

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“…One is a static test using full-scale rocket motors [4][5] and the other took advantage of sub-scale motors 6) . Both tests were conducted at JAXA's Noshiro Rocket Test Center.…”

Section: Previous Tests Using Full and Sub-scale Rocket Motorsmentioning

confidence: 99%

Acoustic Measurement of 1:42 Scale Booster and Launch Pad

Ishii

Tsutsumi

et al. 2014

Proceedings of Meetings on Acoustics

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“…Several research studies utilize sub-scale models of actual launch vehicle configuration [1][2][3][4][5][6][7][8], including water injection effects in some cases. Most of these studies used actual scaled down rocket motors to obtain exact launch vehicle exhaust conditions, as an attempt to perfectly simulate the launch vehicle scenario in a smaller scale.…”

Section: Introductionmentioning

confidence: 99%

Flow Field and Acoustic Investigations of the Launch Vehicle Environment during Lift-off

Karthikeyan¹,

Venkatakrishnan²

2015

21st AIAA/CEAS Aeroacoustics Conference

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During the lift-off phase, a launch vehicle is exposed to severe acoustic loads which are detrimental to the vehicle structure as well as sensitive equipment onboard. Any effort to reduce these loads is beneficial, as it reduces the additional strengthening of the vehicle structure and consequently the weight of the vehicle itself. The design of the jet deflector and launch environment such as launch platform influences the noise levels significantly. Any modifications to them for achieving noise reduction is quite challenging as it should take into account, the factors other than acoustics, such heat transfer, ease of vehicle access etc. Existing literature dealing with simplified jet impingement do not replicate the launch scenario faithfully, ignoring contributions from the factors like launch platform geometry and cutouts in launch platform. Very little is known on the level of impact of these factors on the propagation of noise from the jet exhaust. The present study attempts to address this by investigating the influence of presence of a launch platform with cut-outs on the acoustic field and flow field around a generic launch vehicle exhausting on a realistic jet deflector. The measurements include flow field visualization using shadowgraphy and aeroacoustic measurements using microphones in the near and far-field.

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“…There were a number of tests conducted to identify and alleviate the liftoff levels on Ariane V [8]. There are indications of similar tests for the Japan Aerospace Exploration Agency M-V vehicle [9,10]. Sankaran et al [11] provide a summary of various launch acoustic efforts.…”

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confidence: 96%

Microphone Phased Array to Identify Liftoff Noise Sources in Model-Scale Tests

Panda

Mosher²

2013

Journal of Spacecraft and Rockets

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A 70-microphone phased array, protected to withstand the harsh environment of a rocket test facility, was used to identify noise sources in the Ares I Scale Model Acoustics Test. In the unobstructed burn of a single solid rocket motor, the free-flowing plume itself was found to make a long noise source. The scenario changed completely in launch configurations where a 5%-scale model of the Ares I vehicle was tested in static firings. It was found that the impingement by the plume on various regions of the launch pad constituted the primary noise sources. The scenario is very different from current models, which assume that the plume itself is the noise source and do not account for impingement sources. As expected, the addition of water in the trench and the hole for the plume passage attenuated the associated noise sources. Water injection on the top of the pad ("rainbird") was found to attenuate only the peripheral sources around the primary plume impingement zone. The noise maps suggest that the minimization of impingement by reducing vehicle drift, reducing plume spillage via increasing the size of the hole, and covering-up leakage paths for the sound waves from the trench will attenuate the liftoff acoustics level. Nomenclature b = beamformed output d = aperture of the array G = cross-spectral matrix R = radial position of a microphone from array center S = weight applied to individual microphones St = Strouhal frequency U = plume velocity at nozzle exit w = steering vector θ = angular position from the image center λ = wavelength Subscripts D = nozzle exit diameter f = frequency i, j = index for interrogation grid m = microphone index R = Rayleigh resolution

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Acoustic Measurement and Prediction of Solid Rockets in Static Firing Tests

Cited by 25 publications

References 6 publications

Acoustic Measurement of 1:42 Scale Booster and Launch Pad

Acoustic Measurement of 1:42 Scale Booster and Launch Pad

Flow Field and Acoustic Investigations of the Launch Vehicle Environment during Lift-off

Microphone Phased Array to Identify Liftoff Noise Sources in Model-Scale Tests

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