Influence of rocket engine exit parameters on flow and radiation characteristics of exhaust plume

被引：0
|
作者：
Bao X. [1 ,2 ,3 ]
Yu X. [1 ]
Mao H. [3 ]
Wang Z. [3 ]
Xu Y. [3 ]
机构：
[1] State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing
[2] School of Engineering Science, University of Chinese Academy of Sciences, Beijing
[3] Science and Technology on Optical Radiation Laboratory, Beijing Institute of Environmental Features, Beijing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 11期
关键词：
Exhaust plume flow; Flow field structure; Infrared radiation; Mechanism of chemical reaction; Rocket engine exit parameters;
D O I：
10.13224/j.cnki.jasp.2019.11.017
中图分类号：
学科分类号：
摘要：
Based on the detailed chemical reaction mechanism, the flow and radiation of the plume were studied by the method of computational fluid dynamics (CFD) + line-by-line integration and light of sight method. The effects of different chemical reaction mechanisms on flow and radiation were compared and analyzed. The validity of the model was verified by optical measurement data. On this basis, the influence of rocket exit parameters on plume flow and radiation was analyzed in detail. The results showed that: the temperature of the nozzle exit had little effect on the structure of the flow field, but had a significant effect on the afterburning; the increase of pressure at the nozzle exit had an effect on the wave structure of the Maher disk, but had little effect on the afterburning; the infrared radiation intensity of the plume increased with the increase of the temperature and pressure of the nozzle exit, and the infrared radiation intensity was positively related to the thrust of the engine. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.
引用
收藏
页码：2448 / 2457
页数：9
相关论文
共 18 条
  • [1] Raghunathan S., Kim H.D., Benard E., Et al., Plume interference effects on missile bodies, Journal of Spacecraft and Rockets, 40, 1, pp. 136-138, (2003)
  • [2] Simmons F.S., Rocket Exhaust Plume Phenomenology, (2000)
  • [3] Devir A., Lessin A., Comparison of calculated and measured radiation from a rocket motor plume, (2001)
  • [4] Jensen D.E., Webb B.C., Afterburning predictions for metal-modified propellant motor exhaust, AIAA Journal, 14, 7, pp. 947-954, (1976)
  • [5] Calhoon W.H., Kenzakowski D.C., Flowfield and radiation analysis of missile exhaust plumes using a turbulent chemistry interaction model, (2000)
  • [6] Calhoon W.H., Computational assessment of afterburning cessation mechanisms in fuel-rich rocket exhaust plumes, Journal of Propulsion and Power, 17, 1, pp. 111-119, (2001)
  • [7] Troyes J., Dubois I., Borie V., Et al., Mluti-phase reactive numerical simulation of a model solid rocket motor exhaust jet, (2006)
  • [8] Jang Y., Fu D., Numerical simulation for non-equilibrium chemically reacting fluid field of the solid rocket motor exhaust plume, Journal of Astronautics, 29, 2, pp. 615-620, (2008)
  • [9] Niu Q., Fu D., Li X., Numerical study on the plumes of solid rocket motor under various flight conditions, Journal of Aerospace Power, 30, 7, pp. 1745-1751, (2015)
  • [10] Dong S., Yu J., Li D., Et al., Numerical modeling of infrared radiation properties of exhaust plume by the discrete ordinates method in body-fitted coordinates, Journal of University of Shanghai for Science and Technology, 25, 2, pp. 159-162, (2003)
12