Heated Helium to Simulate Surface Pressure Fluctuations Created by Rocket Motor Plumes

Panda, Jayanta; Burnside, Nathan; Fong, Robert; Ross, James C.; James, G. H.; Fogt, Vincent A.

doi:10.2514/1.j051485

Cited by 5 publications

(2 citation statements)

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“…It is known that the afterburning in the plume produces increased low-frequency content. 3 The video frames in Figure 2 show marked extent of afterburning in the high-thrust condition, and a lack thereof in the low-thrust burn, which perhaps explains the difference seen in the low-frequency end.…”

Section: Discussion Of Experimental Resultsmentioning

confidence: 93%

“…Due to their high exhaust velocities and temperatures, various rocket motors used for multiple purposes on a space vehicle generate extremely high levels of fluctuating pressure. [1][2][3] The high acoustic loads in the near field, if not suppressed with design or treatment, can lead to structural damage to the electronic and navigational components and unacceptable vibration levels for various systems and sub-systems. In addition to the lift-off and ascent stages of a nominal flight, high acoustic levels are also associated with launch abort system (LAS) motors used in manned space vehicles such as Apollo and the new Orion Crew Vehicle.…”

Section: Introductionmentioning

confidence: 99%

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Measurements of unsteady pressure fluctuations in the near-field of a solid rocket motor plume

Horne

Burnside

Panda

et al. 2016

International Journal of Aeroacoustics

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Near-plume fluctuating pressures were measured during five static burns of a two-stage solid rocket motor. An array of 11 water-cooled dynamic pressure sensors was used for the near-field survey, and a condenser microphone was used to monitor the far-field acoustic fluctuations. During the initial high-thrust phase of the burn, the plume was nearly ideally expanded, while in the following low-thrust phase, it was highly over-expanded and showed the presence of clear shock patterns. This paper presents time histories and spectra measured for the two thrust conditions. Spectra from very close to the plume show high levels of low-frequency fluctuations which are known to produce significant vibro-acoustic response of the spacecraft structures. The far-field microphone signal was dominated by mixing noise with little evidence of contribution from shock-associated noise, even for the over-expanded condition. The work was performed in support of an effort to improve predictions of the acoustic environment of a manned spacecraft, such as NASA's Orion Crew Vehicle, during pad abort scenarios.

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Section: Discussion Of Experimental Resultsmentioning

confidence: 93%

Section: Introductionmentioning

confidence: 99%