An improved SHDOM coupled with CFD for simulating infrared radiation signatures of rocket plumes

Zhang, Danmen; Liu, Bai; Wang, Yankun; Lv, Qiang; Zhang, Tianjiao

doi:10.1016/j.infrared.2022.104054

Cited by 12 publications

(4 citation statements)

References 23 publications

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“…Previous studies demonstrated a strong correlation between the detection angle and radiation signatures [20,[22][23][24][25][26][27]. Nelson [23] presented data showing that the radiance at a detection angle of 90 ° and in the 2-5 μm band was 61.4 times brighter than that at a detection angle of 0 °.…”

Section: Introductionmentioning

confidence: 99%

Research on the Modeling Technique of Infrared Radiation Scaling Law for Rocket Engine Exhaust Plumes

Sun,

Niu,

Zhu

et al. 2024

Preprint

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The complexity of the rocket motor exhaust plume radiation phenomenon, along with the influence of numerous parameters and implicit propagation, makes the theoretical simulation calculations expensive. This hinders design optimization, parameter identification, and other studies. Hence, it is crucial to establish the direct correlation between thrust, velocity, altitude, detection angle, and plume radiation in engineering. The paper proposes a scaling law modeling approach for predicting plume infrared radiation from liquid oxygen (LOX)/kerosene rocket engines to solve the difficulties of quick prediction and lack of explicit models. An explicit scaling law model with four parameters is developed by utilizing the e-exponential scaling law to relate plume radiance to flight velocity, the power scaling law to relate plume radiance to vacuum thrust, and the sinusoidal scaling law to relate plume radiance to detection angle. This model employs a decoupled modeling approach for plume radiance, flight altitude, flight velocity, vacuum thrust, and detection angle. A fast prediction method for the LOX/kerosene rocket engine plume in the altitude range of 11~61 km is achieved. The theoretical simulation test shows the relative error of the velocity-scaling law in predicting the radiance of the RD-180 template engine during the Atlas III flight trajectory is less than 20%. The radiance of the RD-170 and RD-191 rocket engines is predicted using the thrust-scaling law based on the radiance of the RD-180 template engine exhaust plume. The radiance of the exhaust plume from the RD-170 and RD-191 rocket motors is estimated using the thrust-scaling law with an accuracy of under 15%. Subsequently, the radiance of these two motors at detection angles between 10° and 170° is predicted using the angle-scaling with a relative error of less than 35%.

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Section: Introductionmentioning

confidence: 99%

Research on the Modeling Technique of Infrared Radiation Scaling Law for Rocket Engine Exhaust Plumes

Sun,

Niu,

Zhu

et al. 2024

Preprint

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“…Li et al [9] established a numerical simulation method for chemical reaction reignition of solid rocket motor exhaust plume and a numerical calculation method for line-of-sight optical radiation transmission, and carried out a computational analysis of the flow and radiation characteristics of the exhaust plume under different flight conditions, and the results showed that the reignition effect caused the temperature rise of the exhaust plume can reach 1000 K, and made the radiation intensity of the exhaust plume spectral band enhanced by more than 10 times. Zhang et al [10,11] studied the influence of alumina cluster particles on the infrared and ultraviolet spectral radiation characteristics of aircraft exhaust plume by using the Spherical Harmonics Discrete Ordinate Method (SHDOM). Zhang et al [12] analyzed the influence of alumina particles in the non-uniform exhaust plume on the infrared radiation characteristics of the exhaust plume with the finite volume method (FVM).…”

Section: Introductionmentioning

confidence: 99%

Study of spectral radiation characteristics of solid rocket plume based on an improved SHDOM

Chen,

Li,

Qiang

2023

Third International Computing Imaging Conference (CITA 2023)

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In order to conduct an in-depth study of the spectral radiation characteristics of two-phase flow exhaust plume, this paper proposes a solution algorithm for calculating the spectral radiation characteristics of the two-phase flow exhaust plume based on the traditional spherical harmonic discrete coordinate method and compares the simulation results with the experimental data of the Black Brant sounding rocket exhaust plume. The results show that the infrared spectral radiation characteristics and intensity of the two-phase flow exhaust plume of the rocket simulated in this paper are consistent with the experimental measurements of DRDC, which verifies that the improved spherical harmonic discrete coordinate method is effective and reliable in simulating and calculating the spectral radiation characteristics of the two-phase flow exhaust plume.

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“…In spite of this, the current research on plume polarization mainly focuses on experimental studies and lacks relevant theoretical models and analyses [9] . Compared with the more mature atmospheric polarization radiation transfer model, there is strong self-radiation in the gas-solid two-phase plume, so the calculation model must consider its own radiation scattering process [10,11] . Based on the current research progress, we established a set of polarization radiation transmission model of solid rocket plume considering its own radiation, mainly considering the polarization scattering process of Al2O3 particles in the radiation transmission process [12] .…”

Section: Introductionmentioning

confidence: 99%

Simulation and analysis of solid rocket plume infrared polarization

zhang,

Gao,

Sun

et al. 2023

Third International Computing Imaging Conference (CITA 2023)

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With the improvement of stealth and penetration ability of high-speed targets, it is more and more difficult to capture and recognize high-speed targets by relying on traditional optical characteristic signals. It is urgent to expand the characteristic optical elements as an effective complement to the existing detection means. As an optical element, polarization greatly expands the optical information dimension and has high application value in the field of target detection and recognition. This paper presents a method for calculating polarization radiation transmission of rocket plume based on Monte Carlo method. The correctness of the algorithm is verified by an example of L13. The detection wavelength of 1.55 um was selected, and the polarization characteristics of the solid rocket plume at different viewing angles and the imaging characteristics at different viewing angles were calculated using this method. The imaging results show that the characteristics of the polarization degree can reflect the profile of the plume at different observation angles. The point source results show that the polarization degree of the plume is very small in the case of point source radiation, and the polarization Angle changes obviously with the change of the relative detection azimuth, which is helpful to analyze the plume orientation and other information in the case of point source detection.

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An improved SHDOM coupled with CFD for simulating infrared radiation signatures of rocket plumes

Cited by 12 publications

References 23 publications

Research on the Modeling Technique of Infrared Radiation Scaling Law for Rocket Engine Exhaust Plumes

Research on the Modeling Technique of Infrared Radiation Scaling Law for Rocket Engine Exhaust Plumes

Study of spectral radiation characteristics of solid rocket plume based on an improved SHDOM

Simulation and analysis of solid rocket plume infrared polarization

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