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

Wang, Weichen; Wei, Zhijun; Zhang, Qiao; Wang, Ningfei; Xiong, Yanting

doi:10.2514/6.2011-6140

Cited by 4 publications

(5 citation statements)

References 21 publications

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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%

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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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Section: Test Instrumentmentioning

confidence: 99%

“…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%

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

Kim

Yim²,

Baek

2015

Propellants Explo Pyrotec

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“…According to (6), if the radial densities of the integrated absorbance a 1 (r j ) and a 2 (r j ) of two transitions are retrieved, the radial temperature T (r j ) can be calculated by…”

Section: B Onion-peeling Deconvolutionmentioning

confidence: 99%

“…Furthermore, rocket exhaust plume is another typical and significant example of combustion application with axisymmetric temperature and concentration distributions. As the exhaust gases expand beyond the nozzle exit, fuel rich species in the combustion gas reacts with the oxygen in the air, which contributes to afterburning reactions with axisymmetric temperature and concentration distributions in the plume backflow region [6]- [8]. Therefore, it is necessary to reconstruct the axisymmetric temperature and concentration distributions of the flame, to describe and monitor the combustion stability and flame characteristics of the combustion progress.…”

Section: Introductionmentioning

confidence: 99%

Reconstruction of Axisymmetric Temperature and Gas Concentration Distributions by Combining Fan-Beam TDLAS With Onion-Peeling Deconvolution

Liu

Cao

et al. 2014

IEEE Trans. Instrum. Meas.

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Fan-beam tunable diode laser absorption spectroscopy (TDLAS) system was combined with onion-peeling deconvolution to reconstruct axisymmetric temperature and gas concentration distributions. The fan-beam TDLAS system consists of two tunable distributed feedback diode lasers at 7185.597 and 7444.36 cm −1 , a cylindrical lens and multiple photodiode detectors in a linear detector array. When a well-collimated laser beam penetrates through a cylindrical lens, a fan-beam laser was formed. Then, the fan-beam laser penetrates through the target region and is detected by the photodiode detectors in the detector array. After transforming the fan-beam geometry to equivalent parallel-beam geometry, axisymmetric temperature and gas concentration distributions can be reconstructed using the onion-peeling deconvolution. To obtain the reconstruction results with higher accuracy, a revised Tikhonov regularization method was adopted in the onion-peeling deconvolution. In this paper, numerical simulation and experimental verification were carried out to validate the feasibility of the proposed methods. The results show that the proposed methods can be used to on-line monitor the axisymmetric temperature and gas concentration distributions with higher accuracy and robustness in combustion diagnosis. IndexTerms-Axisymmetric temperature and gas concentration distributions, fan-beam tunable diode laser absorption spectroscopy (TDLAS), onion-peeling deconvolution, regularization method. 0018-9456Zhang Cao received the B.Sc. (Hons.) degree in automation and the M.Eng. and Ph.D. (Hons.) degrees in measurement technology and automatic devices from Tianjin University,

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“…15 The same questionable approach has also been used by some researches. [29][30][31] The aim of the present work is therefore to present a new numerical approach that is based on the FVM and suitable at the same time for accurate narrow-band simulations. The development of the method is evoked by great authors' interest in predictions of IR signatures from airborne vehicle exhaust plumes.…”

Section: Introductionmentioning

confidence: 99%

A Finite Volume Based Method for Narrow-Band Simulations of Thermal Radiation from Participating Media

Sventitskiy

Mundt

2014

11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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An approach is proposed to improve numerical modeling of directional thermal radiation originating from absorbing, emitting and scattering media. In this approach, the finite volume method for radiation transfer is applied on the narrow-band basis to evaluate the source function of the radiative transfer equation. The emission in a given direction is then predicted through integration of the transfer equation with evaluated source functions along lines-of-sight through the medium. The correlated-k model is coupled with the radiative transfer solvers to ensure accurate spectral modeling of gas radiative properties. The method performance is demonstrated by comparison with solutions obtained using the basic finite volume method with various directional discretizations. This comparison was done for infrared radiation from a participating medium contained in a three-dimensional enclosure. Nomenclature Latin symbolsA = area, m 2 a = coefficient in the discretization equation of transfer b = source term in the discretization equation of transfer v f = volume fraction I = intensity, W/(m 2 sr µm) k = absorption index, or absorption coefficient, m -1 L = number of control angles in a given direction M = number of control volumes, or number of species N = number of discrete directions, or number of quadrature points n  = refractive index n = face normal p = total pressure, atm S = source function, W/(m 2 sr µm) s  = direction of radiation propagation s = geometric path coordinate, m T = temperature, K V = volume, m 3 , , x y z = Cartesian coordinates, m x = mole fraction Greek symbols  = coefficient in Eq. (19)  = extinction coefficient, m -1  = emissivity  = zenith angle  = wavelength, µm s  = scattering coefficient, m -1 AIAA Aviation  = scattering phase function  = azimuth angle  = solid angle, sr  = quadrature weight Superscripts n = iteration index ' = directional value, or dummy variable  = vector quantity  = averaged quantity Subscripts 0 = boundary condition b = blackbody g = gas, or at a given k-distribution value , i j = angular directions, or quadrature point, or species index mix = mixture P = control volume center , , , , , E W N S B T = east, west, north, south, bottom, and top neighbours of P , , , , , e w n s b t = east, west, north, south, bottom, and top control volume faces p = particle ,   = in a given angular direction  = at a given wavelength

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

Cited by 4 publications

References 21 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

Reconstruction of Axisymmetric Temperature and Gas Concentration Distributions by Combining Fan-Beam TDLAS With Onion-Peeling Deconvolution

A Finite Volume Based Method for Narrow-Band Simulations of Thermal Radiation from Participating Media

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