Radiation in a hypersonic shock layer generated around a projectile

Komurasaki, Kimiya; Kasahara, Jiro; Yano, Shujiro; Fujiwara, Toshi

doi:10.1007/bf01419003

Cited by 1 publication

(1 citation statement)

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“…[8][9][10] Some testing uses streamwise viewing with mirrors instead of fibers. 11,12 Another study used windowless and purged apertures to extract the optical emission, 13 which works well for the deep ultraviolet (UV) spectrum.…”

Section: Previous Workmentioning

confidence: 99%

Fiber-Based Measurement of Bow-Shock Spectra for Reentry Flight Testing

Schott

Herring

Munk

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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We demonstrated a fiber-based approach for obtaining optical spectra of a glowing bow shock in a high-enthalpy air flow. The work was performed in a ground test with the NASA Ames Aerodynamic Heating Facility (AHF) that is used for atmospheric reentry simulation. The method uses a commercial fiber optic that is embedded in the nose of an ablating bluntbody model and provides a line-of-sight view in the streamwise direction -directly upstream into the hot post-shock gas flow. Both phenolic impregnated carbon ablator (PICA) and phenolic carbon (PhenCarb 28) materials were used as thermal protection systems. Results show that the fibers survive the intense heat and operate sufficiently well during the first several seconds of a typical AHF run (20 MJ/kg). This approach allowed the acquisition of optical spectra, enabling a Boltzmann-based electronic excitation temperature measurement from Cu atom impurities (averaged over a line-of-sight through the gas cap, with a 0.04 sec integration time). Nomenclature I. Backgroundadiometry and spectroradiometry instrumentation for measuring bow shock emission ahead of blunt-body atmospheric entry vehicles was successfully demonstrated in well-known NASA flight experiments in the 1960s as part of the Apollo program. In the Fire I and Fire II flight tests, 1, 2 each entry vehicle had a stacked series of three "clean" beryllium forebody heat shields, two of which were jettisoned successively during reentry. Each heat shield had its own fused quartz window at the stagnation point that provided viewing of the bow shock. The total 1 AST, Flight Systems Remote Sensing Branch, B1202/MS 468 2

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