Laser Light Sheet Flow Visualization of the Space Launch System Booster Separation Test

Danehy, Paul M.; Wisser, Bradley M.; Fahringer, Timothy W.; Winski, Courtney S.; Falman, Bryan E.; Shea, Sean; Boyda, Matthew T.; Lowe, K. Todd

doi:10.2514/6.2019-2313

Cited by 1 publication

(1 citation statement)

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“…Other recent examples of subsonic rocket testing include evaluating the impact of thrust vectoring lateral jets on the aerodynamic characteristics of a missile (Ocokolić and Rašuo, 2012), iterative shape optimisation of missile wings (Ocokolić et al , 2017) and an investigation of the impact of nozzle configurations in the near wake of a generic rocket (Wolf et al , 2012). Supersonic tests have recently been used for an evaluation of booster characteristics of the SLS during separation using laser sheet visualisation (Danehy et al , 2019), as well as for determining aeroacoustic performance of modern launchers – VEGA (Imperatore et al , 2005; Camussi et al , 2020) and the SLS (Garbeff et al , 2019; Roozeboom et al , 2019; Steva et al , 2019) using a wide variety of techniques, including pressure-sensitive paint, steady and unsteady pressure sensors, shadowgraph and schlieren photography.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of the boosters impact on the rocket aerodynamic characteristics

Krzysiak

Cieśliński

Placek

et al. 2022

AEAT

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Purpose The purpose of this study is to determine the impact of two parallel boosters fixed to the ILR 33 AMBER 2 K core rocket stage on its aerodynamic characteristics in the subsonic and transonic regimes and for M = 2.3. Design/methodology/approach Wind tunnel tests of the rocket model were carried out in a trisonic wind tunnel using a six-component internal balance. Three rocket model configurations were investigated. Findings The results of the presented studies showed that the presence of boosters causes a significant increase in the total rocket drag, which depends on both the Mach number and the rocket flight phase. Experimental tests of the rocket model allowed to determine the difference in drag coefficient between active and passive flight versus Mach number. It was found that, in the case of a deviation from the rocket’s flight direction, the aerodynamic coefficients strongly depend on the location of the boosters in relation to the direction of the deviation. Practical implications Studies of the rocket model aerodynamic characteristics allow the assessment of the influence of parallel boosters on rocket performance, which is important when the decision of a rocket staging type is taken. Originality/value The presented wind tunnel test results of the rocket model equipped with the two parallel boosters are an original contribution to the rocket research results presented in the literature.

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