Evaluation of computation codes for rocket plume's infrared signature by using measurements on a small scale aluminized composite propellant motor

Boischot, A.; Roblin, Antoine; Hespel, Laurent; Dubois, I.; Prévot, Pierre; Smithson, T. L.

doi:10.1117/12.667242

Cited by 4 publications

(3 citation statements)

References 15 publications

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“…However,c onducting experimentals tudies using real rocket motorh as many constraints such as al arge-scale test site, high experimental cost and difficulty in IR irradiance measurement, which have limited the number of studies.I nstead,e xperiments using flame, lab-scale rocket motors and standard rocket motors were conducted to simulater eal rocketm otors [7,10,12,13].I tw ould thus be of interest to determine the relationship between real rocket motors and standardr ocketm otors.…”

Section: Introductionmentioning

confidence: 99%

Comparative Study on Infrared Irradiance Emitted from Standard and Real Rocket Motor Plumes

Kim

Yim²,

Baek

2015

Propellants Explo Pyrotec

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The infrared irradiance signature from exhaust plume is essential for the design of solid rocket motors. To overcome the difficulty of conducting experiments using real rocket motors, experimental studies were carried out to compare standard rocket motors and real rocket motors of the same propellant. The static firing tests on standard and real rocket motors of NEPE and HTPB propellants were conducted. Despite different rocket motor size and methodology of spectro‐radiometric measurement, the spectral characteristics of the infrared irradiance signature for both rocket motors were quite similar. The standard and real rocket motors of HTPB propellant showed similar tendency of steady infrared irradiance emission throughout the combustion, whereas both rocket motors of NEPE propellant showed a rapid emission in the midstream of combustion. The total infrared irradiance of NEPE was about 55 % less than that of HTPB propellant for both standard and real rocket motor experiments. Additionally, the relative amounts of chemical products produced during propellant combustion came out to be similar for both rocket motors. The experimental results indicated that the spectral characteristics of infrared irradiance and combustion products were quite similar for different sized rocket motors of same propellant and that a correlation of infrared irradiance signature exists between small‐sized standard rocket motors and real rocket motors. Thus, the spectral characteristics of real rocket motors could be reasonably estimated from the results of standard rocket motors.

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Section: Introductionmentioning

confidence: 99%

Comparative Study on Infrared Irradiance Emitted from Standard and Real Rocket Motor Plumes

Kim

Yim²,

Baek

2015

Propellants Explo Pyrotec

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show abstract

“…For example, a system of acquiring and analyzing visible and near-infrared signatures of rocket plume was developed by Châteauneuf and Dubois [2]. Boischot et al [3] investigated the physical properties of the particles in rocket plume and their impact on the infrared signature. Nelson [4] considered the influence of alumina on the rocket plumes infrared signatures in the wavenumber range from 2000 to 5000 cm-1 with standard procedure.…”

Section: Introductionmentioning

confidence: 99%

“…The calculation of flow field is difficult, since the plume is complex turbulent flow of high-velocity and high-temperature gas containing shocks and expansion wave. There are some standard programs to compute the plume flow, such as GASP (General Aerodynamic Simulation Program) [2] and SPF (Standard Plume Flowfield) [3]. Cai [4] and Baek [5] solved the rocket plume flow with the finite-volume method (FVM).…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Infrared Signature Emitted by Liquid Rocket Plume Using Wide Band K-Distribution Model

Yin

Liu

2012

AMR

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A new wide band k-distribution model has been developed and used to investigate infrared radiation signatures of liquid rocket plume in some detectors’ working spectrum regions, in which the temperature and the gas molar concentration fields are solved using engineering empirical formulations. Based on the line parameters in HITEMP database, absorption coefficient variables of water vapor and carbon dioxide corresponding to 12-point Gauss-Lobatto quadrature points are derived and expressed as a simple formulation. The absorption coefficient variables of mixture are obtained by summing the absorption coefficient variables of individual gas species under the hypothesis that the k-distributions are statistically uncorrelated. Its validity for the numerical prediction of liquid rocket plume radiation is verified by comparison with line-by-line approach (LBL). Compared with line-by-line calculations, the maximum relative errors of the new band model are less than 10 % in the detectors’ working spectrum regions, while the computational time of the new band model is less than 1/1000 of LBL. The effects of fly parameter on infrared radiation signatures of liquid rocket plume are studied using the new model. The results showed that the integral radiation intensities of liquid rocket plume increase with the nozzle exit temperature, Mach number and the ratio of nozzle exit pressure to atmospheric pressure. The radiation intensity variation trend for liquid rocket plume with altitude is different for different detectors’ working spectrum regions.

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Infrared signature of NEPE, HTPB rocket plume under varying flight conditions and motor size

Kim¹,

Kim

et al. 2021

Infrared Physics & Technology

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Evaluation of computation codes for rocket plume's infrared signature by using measurements on a small scale aluminized composite propellant motor

Cited by 4 publications

References 15 publications

Comparative Study on Infrared Irradiance Emitted from Standard and Real Rocket Motor Plumes

Comparative Study on Infrared Irradiance Emitted from Standard and Real Rocket Motor Plumes

Numerical Simulation of Infrared Signature Emitted by Liquid Rocket Plume Using Wide Band K-Distribution Model

Infrared signature of NEPE, HTPB rocket plume under varying flight conditions and motor size

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