Computer Science – Sound
Scientific paper
Jan 1993
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993aiaa.meetr....l&link_type=abstract
AIAA, Aerospace Sciences Meeting and Exhibit, 31st, Reno, NV, Jan. 11-14, 1993, 19 p.
Computer Science
Sound
Rocket Engine Noise, Rocket Test Facilities, Shock Tubes, Sound Pressure, Sound Waves, National Aerospace Plane Program, Nozzle Geometry, Titan 4 Launch Vehicle
Scientific paper
The design and development of a new acoustic progressive wave tube facility was required to test the Titan IV rocket engine. Because of the large 6 feet diameter of the nozzle closure, circular shape, high over-all sound pressure level (OASPL), and high sound pressure levels (SPLs) above 1000 Hz, the acoustic environmental tests required consideration of a custom built facility. This paper describes a new oscillating supersonic shock generator (OSSG) for developing the high OASPL, for developing the high SPLs at above 1000 Hz, and for use with a conventional acoustic modulator. Also, the new OSSG permits impedance matching to the test volume annulus via the special geometry of the annular space between the elliptical containment domes upstream of the test volume annulus. A test annulus gap that is too small causes the test article to vibrate with a severe damping imposed by the pumping of trapped air in the annulus, and too large a gap reduces the OASPL. Consideration is given to tuning the axial and circumferential resonance frequencies of the annulus test space so that there is no coincidence with the principal resonant modes of the test structure. Also consideration is given to establishing the reverberant versus propagating modes of the test annulus.
Bocksruker Ron
Lieberman Paul
Pilgram Mark
Vallance Charles
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