Overview of the Space Launch System Transonic Buffet Environment Test Program

Piatak, David J.; Sekula, Martin K.; Rausch, Russ D.; Florance, James R.; Ivanco, Thomas G.

doi:10.2514/6.2015-0557

Cited by 20 publications

(6 citation statements)

References 6 publications

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“…The inflow Mach number is 0.8, and the attack angle is 0°. The Reynolds number based on the diameter of the cylinder is 2.66×10 6 . The distance of the first grid line to the wall is 10 -5 which corresponds to a y + less than 1.0.…”

Section: Numerical Fairing Modelmentioning

confidence: 99%

“…When buffet occurs on a launch vehicle, the fluctuating pressure loads can excite vehicle bending modes and local shell/panel modes, even lead to launch failures (Rainey 1965). The buffet environment is typically most extreme in the transonic regime as the vehicle approaches the speed of sound (Piatak et al 2012(Piatak et al , 2015. At this point in the trajectory, shocks form on the vehicle and interact with other phenomena at locations where changes in the vehicles geometry occur, as Figure 1 shows.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Empirical Predication of Fluctuating Pressure Environments Around a Rocket Fairing

Zhao¹,

Rong²,

Qin³

et al. 2017

dtetr

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Section: Numerical Fairing Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Empirical Predication of Fluctuating Pressure Environments Around a Rocket Fairing

Zhao¹,

Rong²,

Qin³

et al. 2017

dtetr

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“…Additional model variations were tested to determine C their effectiveness as buffet and acoustic mitigation options (BMOs and AMOs). The potential need for these mitigation options arose from buffet and aeroacoustic pressure level magnitudes in the area of the solid rocket booster (SRB) forward attach point observed during the 2012 SLS Transonic Buffet Environment Test Program 3 .…”

Section: Introductionmentioning

confidence: 99%

“…Aerospace Engineer, Aerosciences Branch, EV33 2. Aerospace Engineer, Aerosciences Branch, Jacobs ESSSA Group 3. Aerospace Engineer, Fluid Dynamics Branch, ER42.…”

mentioning

confidence: 99%

Overview of the Space Launch System Ascent Aeroacoustic Environment Test Program

Herron

Crosby

Reed

2016

54th AIAA Aerospace Sciences Meeting

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Characterization of accurate flight vehicle unsteady aerodynamics is critical for component and secondary structure vibroacoustic design. The Aerosciences Branch at the National Aeronautics and Space Administration (NASA) Marshall Space Flight Center has conducted a test at the NASA Ames Research Center (ARC) Unitary Plan Wind Tunnels (UPWT) to determine such ascent aeroacoustic environments for the Space Launch System (SLS). Surface static pressure measurements were also collected to aid in determination of local environments for venting, CFD substantiation, and calibration of the flush air data system located on the launch abort system. Additionally, this test supported a NASA Engineering and Safety Center study of alternate booster nose caps. Testing occurred during two test campaigns: August -September 2013 and December 2013 -January 2014. Four primary model configurations were tested for ascent aeroacoustic environment definition.The SLS Block 1 vehicle was represented by a 2.5% full stack model and a 4% truncated model. Preliminary Block 1B payload and manned configurations were also tested, using 2.5% full stack and 4% truncated models respectively. This test utilized the 11 x 11 foot transonic and 9 x 7 foot supersonic tunnel sections at the ARC UPWT to collect data from Mach 0.7 through 2.5 at various total angles of attack. SLS Block 1 design environments were developed primarily using these data. SLS Block 1B preliminary environments have also been prepared using these data. This paper discusses the test and analysis methodology utilized, with a focus on the unsteady data collection and processing.

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“…[6][7][8][9] Efforts to develop BFFs for the SLS configuration have been underway since 2011 and there have been two primary test programs conducted to obtain unsteady buffet pressures. [10][11] Buffet tests in 2012 identified high fluctuating pressure environments on the core and booster downstream of the booster forward attachment near Mach 0.92. Coupled loads analysis revealed that when preliminary BFFs developed from these environments were applied to the vehicle structure, buffet loads were largely the source of exceedances of structural and vibratory limits on the SLS vehicle.…”

mentioning

confidence: 99%

Sensitivity of Space Launch System Buffet Forcing Functions to Buffet Mitigation Options

Piatak

Sekula

Rausch

2016

54th AIAA Aerospace Sciences Meeting

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Overview of the Space Launch System Transonic Buffet Environment Test Program

Cited by 20 publications

References 6 publications

Empirical Predication of Fluctuating Pressure Environments Around a Rocket Fairing

Empirical Predication of Fluctuating Pressure Environments Around a Rocket Fairing

Overview of the Space Launch System Ascent Aeroacoustic Environment Test Program

Sensitivity of Space Launch System Buffet Forcing Functions to Buffet Mitigation Options

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