Comparison of calculated and measured radiation from a rocket motor plume

Devir, Adam D.; Lessin, Alex; Cohen, Yoram; Yaniv, Sara; Kanelbaum, Y.; Avital, G.; Gamss, L.; Macales, J.; Trieman, B.; Lev, M.; e, al

doi:10.2514/6.2001-358

Cited by 18 publications

(8 citation statements)

References 4 publications

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“…The temperature distribution and the extent of the afterburning of the plume are different for the propellants of different energy characteristics, and there is also great difference in the infrared radiative of the plume among the propellants. 4. The influence of the radiation source term on the temperature of the plume flow field was studied, and the results show that when the radiation energy emitted out of the fluid cell is larger than the received radiation energy from the circumambient fluid cells, the temperature of the fluid cell will decline with coupling solution.…”

Section: Figure 12 Distribution Of the Radiative Illumination In Evementioning

confidence: 99%

“…Harwell [2] used the infrared radiation detector to test the radiation intensity of the monitor in the plume field. Deimling [3] used the spectrometer to test the infrared radiation spectral characteristics from 1.2 micro to 14 micron of 3 different types of solid propellants Devir [4] used the FTIR and FLIR to test the infrared radiation intensity from 1.5 micron to 5.5 micron and the infrared radiation images for a small solid rocket motor.…”

Section: Introductionmentioning

confidence: 99%

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Infrared Radiation Signature of Exhaust Plume from Solid Propellants of Different Energy Characteristics

Wang¹,

Wei²,

Zhang³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The infrared radiation signature of the plume from the solid propellants of different energy characteristics is not the same. Three kinds of double-base propellants of different energy characteristics were chosen to test the infrared spectral radiance from 1000 cm -1 to 4500 cm -1 of their plume. The radiative spectrum was obtained in the tests. The experimental results indicate that the infrared radiation of the plume is basically determined by the energy characteristic of the propellant. The radiative transfer calculation models for the exhaust plume from the solid propellants were established By inducing the chemistry reaction source term and the radiation source term into the energy equation, the plume field and the radiative transfer were solved in a coupling way. The calculated results were consistent with the experimental data, so the reliability of the calculation models was conformed. The temperature distribution and the extent of the afterburning of the plume are distinct for the propellants of different energy characteristics, therefore the radiation of the plume varied with the propellants. The temperature of the fluid cell in the plume will increase or decrease to some extent by the influence of the radiation source term. NomenclatureI λ = spectral radiance I = radiation intensity E = radiative illumination/energy of the fluid θ = zenith angle φ = azimuth angle ρ = density of the fluid T = temperature of the fluid v = velocity of the fluid p = pressure of the fluid 1 Ph. D Student, 2 S c = chemistry source term S r = radiation source term

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Section: Figure 12 Distribution Of the Radiative Illumination In Evementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Infrared Radiation Signature of Exhaust Plume from Solid Propellants of Different Energy Characteristics

Wang¹,

Wei²,

Zhang³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…AF T-IR spectro-radiometer of type ABB MR304LN was used to measure the IR irradiance signature emitted from exhaust plume.I tf eatured simultaneous data acquisition from the IR detectors of MCT and InSb detectors which covered the spectral rangef rom 2 mmt o1 5mm [ 15].T he FOV (field of view) of the spectro-radiometer was 75 mrad and the spectral resolution was set to 4cm À1 .F igure 3s hows the placemento ft he spectro-radiometer for the test. The spectro-radiometer was set differently for standardr ocket and real rocketm otors referring to previous studies [7,[9][10][11]. For standardr ocket motor tests, the spectro-radiometer was 3.17 mawayfrom the axis line of the plumeatadetection angle of 68.58.T he targeted plume spot was 1.31 m from the nozzle exit.…”

Section: Test Instrumentmentioning

confidence: 99%

“…Blanc [9] used as pectrometer to measure the IR irradiance spectral characteristics of solid rocket motors of composite and double-base propellants. Devir [10] usedaF ourier-transform infrared (FT-IR) spectrometert om easure the IR irradiance intensity of as mall solid rocket motor. Wang [11] also used aF T-IR spectrometer to measure the IR irradiance signature of three kinds of double-base propellants.…”

Section: Introductionmentioning

confidence: 99%

“…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%

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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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Infrared Irradiance Reduction in Minimum Smoke Propellants by Addition of Potassium Salt

Yim

Park

Lee

et al. 2014

Propellants Explo Pyrotec

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One of the plume characteristics of minimum smoke propellant is the infrared (IR) radiation signature, which may be useful for detection of rocket. The IR irradiance is known to be reduced by afterburning suppression in rocket plume by addition of potassium salt in propellant. The minimum smoke propellant with nitrate ester polyether (NEPE) binder system and nitramine oxidizers was researched for the afterburning and IR irradiance difference according to the content of potassium salt as afterburning suppressant in propellant formulation. The propellants were formulated to satisfy the level of AGARD smoke class AA and potassium sulfate was selected as afterburning inhibitor suitable for NEPE propellant. The afterburning flame length and mid‐range IR intensity were measured, while conducting static firing tests of 6 inch (15.24 cm) standard rocket motors loaded with minimum smoke propellants of the different contents of potassium sulfate. The total IR irradiance of HMX/RDX propellant with 1.1 % potassium sulfate was reduced to about 23 % compared to the propellant without afterburning suppressant due to the inhibition of afterburning. Also, the total IR irradiance of the HNIW (30 %)/RDX propellant was found to be almost three times more than that of the HMX/RDX propellant although the content of potassium sulfate was the same of 1.1 % in both propellants.

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Comparison of calculated and measured radiation from a rocket motor plume

Cited by 18 publications

References 4 publications

Infrared Radiation Signature of Exhaust Plume from Solid Propellants of Different Energy Characteristics

Infrared Radiation Signature of Exhaust Plume from Solid Propellants of Different Energy Characteristics

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

Infrared Irradiance Reduction in Minimum Smoke Propellants by Addition of Potassium Salt

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