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

Kim, Min Taek; Yim, Yoo Jin; Baek, Gookhyun

doi:10.1002/prep.201400213

Cited by 15 publications

(2 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Cai et al [6] discovered that the number of nozzles on the liquid-oxygen kerosene engine affected the radiance characteristics of the plume. Kim et al [7] experimental results show that the different sizes of the rocket motor of the same propellant, infrared radiance and the spectral characteristics of the combustion products are very similar, indicating a relationship between the infrared emission properties of tiny standard rocket motors and actual rocket motors. Zhang et al [8] determined that the nozzle radius of a Trident D5 solid rocket motor should be scaled to 0.1 to 1 times the full-size nozzle.…”

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

View full text Add to dashboard Cite

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%.

show abstract

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

View full text Add to dashboard Cite

show abstract

“…Thus, a major cost saving can be achieved. New technique which is the IR experimental approach has also been developed [12][13][14][15]. However, this approach is costly and require substantial time to be completed.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Solid Propellant Rocket Motor Nozzle via CFD Simulation

Mayas

Chen

Aziz

et al. 2020

ARFMTS

View full text Add to dashboard Cite

The current work predicts the combustion characteristics of a solid rocket motor especially the flow in the nozzle part. The simulation work is done using computational fluids dynamic (CFD) software. The volume mesh was built in one quarter of the nozzle to reduce time for calculation. The same nozzle is also created with different mesh sizes for grid dependency check. All the rocket parameter is obtained from the theoretical design of rocket motor based on basic nozzle design. The simulation result in CFD is compared to the theoretical calculations and it shows that the modelling of rocket nozzle results shows good agreement with the theoretical ones. Parametric study on the nozzle was conducted. The results show that the best nozzle configuration for the current design is when the throat length is set to 1mm.

show abstract

Light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis

Yang,

Ye,

Qiang

et al. 2024

Propellants Explo Pyrotec

View full text Add to dashboard Cite

The light transmittance measurement method, which is used to characterize smoke characteristic signal of solid rocket motor plume, can provide important reference for development and design of low smoke characteristic signal solid propellants and motors. The light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis is proposed in this paper. By using a 405 nm laser as the light source and a narrow‐band filter detection method, the influence of plume radiation on the measurement of light transmittance of solid rocket motor plume smoke can be minimized. Additionally, combined with the laser modulation spectrum analysis technology, the signal amplitude is selected by the laser modulation frequency to improve the signal‐to‐noise ratio of the signal. Compared with the laser constant current measuring mode, laser high‐frequency modulation measuring mode with spectrum analysis effectively improves the optical transmittance measurement accuracy. Based on this, a solid rocket motor plume smoke transmittance test system is developed to measure the plume smoke of standard test motors with different propellants and combustion chamber pressures. The results demonstrate that the system can effectively measure the light transmittance of the plume smoke. The light transmittance of solid rocket motor plume can be increased by reducing the aluminum content of solid propellant or increasing the pressure of the combustion chamber. Thus, this research provides an effective measuring tool for evaluating smoke concentration of solid rocket motor plume, which is beneficial to develop low smoke characteristic signal solid propellants and motors.

show abstract

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

Cited by 15 publications

References 14 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

Investigation of Solid Propellant Rocket Motor Nozzle via CFD Simulation

Light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis

Contact Info

Product

Resources

About