Energy-Based Acoustical Measurements of Rocket Noise

Gee, Kent L.; Giraud, Jarom H.; Blotter, Jonathan D.; Sommerfeldt, Scott D.

doi:10.2514/6.2009-3165

Cited by 25 publications

(48 citation statements)

References 5 publications

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“…Recently, three-dimensional intensity probes have been used to measure the sound field of a solid rocket motor plume. 6,7,8 The same probe design was also used to make nearfield acoustic intensity measurements of the F-22A Raptor. The intensity probe was attached to the top of a 90-microphone rectangular array of microphones, which was moved to multiple locations to the sideline and aft of the aircraft.…”

Section: Introductionmentioning

confidence: 99%

Intensity analysis of the dominant frequencies of military jet aircraft noise

Stout

Gee

Neilsen

et al. 2014

Proceedings of Meetings on Acoustics

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Section: Introductionmentioning

confidence: 99%

Intensity analysis of the dominant frequencies of military jet aircraft noise

Stout

Gee

Neilsen

et al. 2014

Proceedings of Meetings on Acoustics

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“…The first was a three-dimensional (3D) spherical probe developed previously for other rocket firings. 3,7,8) The idea of a multimicrophone probe within a rigid sphere was based on prior work [12][13][14] and prompted a number of complementary investigations to further quantify its performance. [15][16][17] Seen in Fig.…”

Section: Probe Designmentioning

confidence: 99%

“…With these constraints in mind, measurement and analysis methodologies have been developed to measure the magnitude, peak directivity, and spectral content of the rocket source. 7,8) Determination of these quantities over a sufficiently large spatial aperture near the rocket provides insight into physical noise generation mechanisms that originate in the turbulent exhaust flow field. The analysis for this paper was based on the measurements of a GEM-60 horizontal static firing at Promontory, Utah on September 6, 2012.…”

Section: Gem-60 Experimental Setup and Near-field Intensity Measuremementioning

confidence: 99%

Development of a Near-field Intensity Measurement Capability for Static Rocket Firings

Gee

Whiting

Neilsen

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Near-field characterization of the acoustical environment near rockets has often involved extrapolating far-field measurements. However, because far-field amplitude data reveals only limited information about source characteristics, a vector intensity measurement system and analysis package has been developed to examine source features more directly. This paper describes the development of the measurement and analysis capability and its application to a horizontal firing of a GEM-60 solid propellant rocket motor firing conducted at ATK Space Systems near Promontory, Utah. An analysis of near-field intensity data provides insight both into the spatial extent and principal radiation lobe as a function of frequency. For 50 Hz, the far-field spectral peak frequency in the maximum radiation direction, the dominant source region derived from tracing the near-field intensity vectors spans 17-32 nozzle diameters, with peak radiation at ~68 o . At high frequencies, the radiation results from a more contracted region that occurs farther upstream and is directed at about ~85°. These results point to the potential utility of near-field vector intensity measurements, in part because the near-field environments represented do not agree with historical far-field data-based models.

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“…The analyses in this paper are based on a data subset recorded using 6.35 mm GRAS 40BD pressure microphones at 76, 305, and 1220 m (250, 1000, and 4000 ft) from the chosen origin (about 10 m downstream of the nozzle) and along a 60° radial relative to the plume axis. This angle likely approximates the peak directivity angle, based on vector intensity estimates 21,22 and prior measurements of other solid rocket motors. 3,7 The microphones were located 2-3 m above the ground, which was covered with about 15 cm of snow.…”

Section: Solid Rocket Motor Static Firing Test Measurementmentioning

confidence: 99%

“…Noise measurements 21 were made during a static firing of an ATK GEM-60 SRM, which is used with a Delta IV orbital launch vehicle and has 827 kN (186,000 lb) average thrust (see Fig. 1).…”

Section: Solid Rocket Motor Static Firing Test Measurementmentioning

confidence: 99%