A Novel Radiative Heat Flux Measurement Technique for Combustion Products Flowing in Solid Rocket Motors

Martin, Heath T.; Houim, Ryan W.; Ferrara, Peter J.; Degges, Matthew J.; Cortopassi, Andrew C.; Boyer, J. Eric; Kuo, Kenneth K.

doi:10.1615/intjenergeticmaterialschemprop.2013001451

Cited by 5 publications

(2 citation statements)

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“…Rocket chamber is protected from high temperature of combustion gases by thermal insulators. Convection is the dominant mode of heat transfer for non-metallized solid propellants to the thermal insulators whereas convective and radiative mode contribute simultaneously for heat transfer to the thermal insulator from composite propellant combustion (Martin et al 2013). However, as the burning time of rocket increases, the thin layer of thermal insulators is inadequate to control and restrict the rise in chamber wall temperature.…”

Section: Introductionmentioning

confidence: 99%

“…In rocket propulsion, heat flux generated by the combustion of the propellant varies from 200 to 2500 × 10 4 W/m 2 (Twichell and Keller Jr 1976). Radiative heat flux incident on thermal insulator and propellant condensed surface are well characterized and demonstrated (Martin et al 2013). Total heat flux (convective and radiation) measurement inside the rocket motor and its plume leads to information about heat energy generated by the propellant.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant

Kalal

Ropia

Shekhar

et al. 2019

J.Aerosp. Technol. Manag.

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Thermal insulation inside the rocket motor experience severe pressure and temperature conditions. Experimental determination of heat fl ux imparted to thermal insulator inside the rocket motor during the static fi ring is a challenging task. This paper reports experimental determination of heat fl ux for double base propellant (DBP) in small rocket motor. It includes development of experimental rocket motor, adaptation of water-cooled heat fl ux sensor on rocket motor, required instrumentation for heat fl ux time recording and analysis of data. Data are recorded in real time for double base propellant combustion up to the pressure level ~3.6 MPa. Average heat fl ux imparted to the rocket motor casing is found in the range of 230-300 × 10 4 W/m 2 . Heat fl ux inside the rocket motor varies nearly linear with pressure. A correlation between the heat fl ux and pressure is also established for measured pressure range.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%