Effect of secondary combustion on the multi-nozzle rocket base thermal environment

被引：0
|
作者：
Zhou Z. [1 ]
Li Y. [1 ]
Jiang P. [1 ]
Bao Y. [2 ]
机构：
[1] School of Aircraft Engineering, Nanchang Hangkong University, Nanchang
[2] Shanghai Institute of Aerospace System Engineering, Shanghai
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 06期
关键词：
frozen flow; multi-nozzle rocket; reaction flow; secondary combustion; thermal environment;
D O I：
10.13224/j.cnki.jasp.20210694
中图分类号：
学科分类号：
摘要：
During rocket launching, the secondary combustions between the fuel-rich exhaust gas and the oxygen of air were made, leading to a temperature rise. Based on three-dimensional compressible Navier-Stokes equation, hybrid RANS/LES turbulence model, DOM model, and finite-rate chemical kinetics, the reaction model of multi-nozzle rocket was established. And the validity of model was verified by comparing with the wind tunnel experimental data. Then, a comparison study between reaction and frozen flows of two-/four-nozzle rockets was developed. The results showed that the secondary combustion mainly occurred in the mixed layer. With the increase of the flight altitudes, the increase of the peak temperature caused by afterburning decreased, while the maximum was 10.16% and the minimum was 0.86%. At the same height, the afterburning effect was strengthened with increasing distance from nozzle exit. Comparing with two-nozzle rocket, the afterburning had less effect on the four-nozzle rocket base thermal environment. In addition, the peak heat flux of the rocket base increased first and then decreased with height. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
引用
收藏
相关论文
共 25 条
  • [1] LUO Tianpei, LIU Ruimin, LI Mao, Et al., Numerical investigations of water-spray cooling effect on test stand’s deflector based on DPM, Journal of Aerospace Power, 33, 2, pp. 497-507, (2018)
  • [2] FRY D，, MADZUNKOV S, Et al., Application of scaling methods to foster ground development of active shielding concepts for space exploration, Acta Astronautica, 178, pp. 296-307, (2021)
  • [3] ZHOU Zhitan, LIANG Xiaoyang, ZHAO Changfang, Et al., Investigations of base thermal environment on four-nozzle liquid launch vehicle at high altitude, Journal of Spacecraft and Rockets, 57, 1, pp. 49-57, (2020)
  • [4] YAN Zhijiang, SHEN Dan, WU Yansen, Et al., Research on the base heating environment of a multi-nozzle heavy launch vehicle, Missiles and Space Vehicles, 1, pp. 105-109, (2021)
  • [5] ZHANG Tao, SUN Bing, Simulation and design of thermal protection of rocket motor in certain detector, Journal of Aerospace Power, 25, 6, pp. 1407-1411, (2010)
  • [6] ZHOU Zhitan, DING Yifu, LE Guigao, Et al., Studies on thermal environment of liquid launch vehicle tail compartmentat high altitude, Journal of Astronautics, 40, 5, pp. 577-584, (2019)
  • [7] XIE Zheng, XIE Jian, CHANG Zhengyang, Et al., Numerical research on jet secondary combustion of rocket launch, Journal of Astronautics, 38, 5, pp. 542-549, (2017)
  • [8] ZHUKOV V P., The impact of methane oxidation kinetics on a rocket nozzle flow, Acta Astronautica, 161, pp. 524-530, (2019)
  • [9] GONZALEZ D R，, WALLMAN P，, SANFORD M，, Et al., Characterization of rocket-plume fluid-dynamic environment using numerical and experimental approaches, Journal of Spacecraft and Rockets, 50, 3, pp. 527-539, (2013)
  • [10] BAO Xingdong, YU Xilong, WANG Zhenhua, Et al., Numerical investigation on flow and radiation characteristics of solid rocket motor plume near the ground, Procedia Computer Science, 174, pp. 645-650, (2020)
123