Effect of Free-Stream Mach Number on the Base Thermal Environment of Launch Vehicle

  • WANG Xu ,
  • XU Xu ,
  • YU Jiaqi ,
  • YANG Qingchun
展开
  • 1. School of Astronautics, Beihang University, Beijing 100191, China
    2. Shenyuan Honors College, Beihang University, Beijing 100191, China

网络出版日期: 2024-11-05

基金资助

This work was supported by the Outstanding Research Project of Shen Yuan Honors College, Academic Excellence Foundation of BUAA for PhD Students and National Key Laboratory of aerospace liquid propulsion. The authors would also like to thank Xiaoyan YANG for her continued support during this study.

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2024

Effect of Free-Stream Mach Number on the Base Thermal Environment of Launch Vehicle

  • WANG Xu ,
  • XU Xu ,
  • YU Jiaqi ,
  • YANG Qingchun
Expand
  • 1. School of Astronautics, Beihang University, Beijing 100191, China
    2. Shenyuan Honors College, Beihang University, Beijing 100191, China

Online published: 2024-11-05

Supported by

This work was supported by the Outstanding Research Project of Shen Yuan Honors College, Academic Excellence Foundation of BUAA for PhD Students and National Key Laboratory of aerospace liquid propulsion. The authors would also like to thank Xiaoyan YANG for her continued support during this study.

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2024

摘要

运载火箭飞行过程中由于喷管欠膨胀射流相互挤压所形成的高温逆流会对火箭底部造成强滞止对流加热,这将严重影响运载火箭飞行安全。因此运载火箭热环境研究一直以来都是热防护研究中的热点。双喷管发动机布局由于其独特的结构特征,在飞行过程中运载火箭更容易受到底部高温气体循环区的影响。特别是在跨音速阶段,火箭底部流场结构的显著变化会对回流区产生强烈影响。本文主要研究了双喷管发动机布局运载火箭在飞行马赫数为0.6到3.0范围内的底部热环境。研究结果表明,在跨音速阶段,自由流马赫数对火箭底部的热环境有显著影响。当马赫数从0.6增加到1.0时,火箭底部的对流热流密度提升至原来7.7倍。该现象主要是由于当飞行速度超过音速时,超音速来流自由剪切层与羽流剪切层相互作用造成的羽流诱导激波所致。激波与剪切层之间的相互作用加剧了回流区及底部自由流与高温逆流拐点处的湍流强度,从而导致更强的高温逆流。此外,还分析了在低海拔下火箭底部加热的原因,发现其机制不同于高海拔下由羽流相互作用引起的高温逆流滞止加热。

本文引用格式

WANG Xu , XU Xu , YU Jiaqi , YANG Qingchun . Effect of Free-Stream Mach Number on the Base Thermal Environment of Launch Vehicle[J]. 热科学学报, 2024 , 33(6) : 2426 -2436 . DOI: 10.1007/s11630-024-2044-7

Abstract

Convective heating of the rocket base caused by high-temperature reverse flow has long been a focus of thermal protection research. With distinctive structural characteristics, the base thermal environment of a twin-nozzle engine proves more susceptible to the recirculation region than its multi-nozzle counterparts. During the transonic stage, significant alterations in the flow field structure at the rocket base strongly influence the recirculation region. This study investigated the thermal environment of the rocket base with a twin-nozzle configuration in freestream at Mach numbers of 0.6 to 3.0. Results indicate that the freestream Mach number significantly affects the thermal environment at the rocket base during the transonic stage. The increase of Mach number from 0.6 to 1.0 causes the convective heating of the rocket base to increase by 7.7 times. This phenomenon arises due to the plume-induced shock wave caused by the impact of the supersonic free shear layer and plume shear layer while the flight speed exceeds the sound speed. The interaction between the shock wave and the shear layer amplifies turbulence in the recirculation region and at the inflection point, resulting in a stronger high-temperature reverse flow. In addition, the cause of low-altitude base heating was analyzed, and it was found that the mechanism is different from the high-temperature countercurrent effect caused by plume interaction.

参考文献

[1] Zhang L., Ju X., Cui N., Ascent control of heavy-lift launch vehicle with guaranteed predefined performance. Aerospace Science and Technology, 2021, 110: 106511.
[2] Pu P., Jiang Y., Analyzing the impact of nitrogen ejection on suppression of rocket base heating. Aerospace Science and Technology, 2020, 107: 106275.
[3] Dufrene A., Space launch system base heating test:  Experimental operations & results. San Diego, USA, AIAA, 2016, Article ID: 2016-0546. DOI: 10.2514/6.2016-0546
[4] Nallasamy R., Kandula M., Duncil L., Schallhorn P., Numerical simulation of the base flow and heat transfer characteristics of a four-nozzle clustered rocket engine. 40th Thermophysics Conference, Seattle, USA, 2008, AIAA, Article ID: 2008-4128. DOI: 10.2514/6.2008-4128
[5] Goethert E.B., Base flow characteristics of missiles with cluster-rocket exhausts. Institute of Aeronautical Science, 1960, 20(3): 60–89.
[6] Lim H.D., New T.H., Mariani R., Cui Y.D., Effects of bevelled nozzles on standoff shocks in supersonic impinging jets. Aerospace Science and Technology, 2019, 94: 105371. 
[7] Raje P.V, Sinha K., Three-dimensional simulation of rocket nozzles with multi-jet interaction using shock-unsteadiness model. AIAA Aviation 2019 Forum, Texas, USA, 2019, AIAA, Article ID: 2019-3322. DOI: 10.2514/6.2019-3322
[8] Knox K.S, Mehta M, Dufrene A.T, Seaford C.M., Space launch system base heating test: Environments and base flow physics. 54th AIAA Aerospace Sciences Meeting, California, USA, 2016, AIAA 2016-0547. DOI: 10.2514/6.2016-0547
[9] Mehta M., Danehy P.M, Inman J., Gaddy D.E, Dufrene A., Optical diagnostic imaging of multi-rocket plume-induced base flow environments. 47th AIAA Fluid Dynamics Conference, Colorado, USA, 2017, AIAA 2017-3465. DOI: 10.2514/6.2017-3465
[10] Musial N.T.W., Base flow characteristics for several four-clustered rocket configurations at Mach numbers from 2.0 to 3.5. 1961, Patent number: NASA-TND-1093.
[11] Mehta M., Seaford C.M, Kirchner R.D, Dufrene A.T., Space launch system core-stage rocket engine development for shock-tunnel testing. Journal of Spacecraft and Rockets, 2017, 55: 382–402. 
[12] Parker R.A., Carr Z.R., Dufrene A.T., Mehta M., Space launch system base heating test: tunable diode laser absorption spectroscopy. 54th AIAA Aerospace Sciences Meeting, California, USA, 2016, AIAA, Article ID: 2016-0548. DOI: 10.2514/6.2016-0548
[13] Zhou Z., Liang X., Zhao C., Le G., Ding Y., Investigations of base thermal environment on four-nozzle liquid launch vehicle at high altitude. Journal of Spacecraft and Rockets, 2019, 57: 49–57. 
[14] Negishi H., Yamanishi N., Arita M., Namura E., Ohkubo S., Numerical analysis of plume heating environment for H-IIA launch vehicle during powered ascent. 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, USA, 2007, AIAA, Article ID: 2007-5505. DOI: 10.2514/6.2007-5505
[15] Wang X., Xu X., Yang Q.C., Base thermal environment on multinozzle rocket configurations. Journal of Spacecraft and Rockets, 2022, 59(6): 1966–1975.
[16] Patel D., Antares liquid rocket engine convective base heating: AJ-26 to RD-181. AIAA Modeling and Simulation Technologies Conference, Washington, D.C., USA, 2016, AIAA, Article ID: 2016-4415. DOI: 10.2514/6.2016-4415
[17] Su H., Xu S., He W., Shen D., Research on the base heating environment of new launch vehicle. Missiles and Space Vehicles, 2021, 05: 20–24, 49.
[18] Yan Z.J., Shen D., Wu Y., Pu P.Y., Gong Y., Research on the base heating environment of a multi-nozzle heavy launch vehicle. Missiles and Space Vehicles, 2021, 01: 105–109, 114. (in Chinese)
[19] Chandra M.S., Chakraborty D., Plume interaction and base flow analysis of a twin engine flight vehicle. Journal of the Institution of Engineers (India): Series C, 2017, 98: 379–385.
[20] Pu P., Jiang Y., Assessing turbulence models on the simulation of launch vehicle base heating. International Journal of Aerospace Engineering, 2019, pp: 1–14. DOI: 10.1155/2019/4240980
[21] Zhou Z.T., Wang X., Lu C., Le G., Numerical analysis on thermal environment of liquid rocket with afterburning under different altitudes. Applied Thermal Engineering, 2020, 178: 115584. 
[22] Yi J., Yanli M., Weichen W., Li W., Inhibition effect of water injection on afterburning of rocket motor exhaust plume. Chinese Journal of Aeronautics, 2010, 23: 653–659. 
[23] Pergament H.S., Calcote H.F., Thermal and chemi-ionization processes in afterburning rocket exhausts. Symposium (International) on Combustion, 1967, 11: 597–611.
[24] Yang Y., Yuan Y., Ding Z., Yang J., Analysis of plume flow field and base heating environment of multi-engine cluster rocket. Journal of Astronautics, 2021, 42: 1446–1452.
[25] Houshang B., Numerical investigation of twin-nozzle rocket plume phenomenology. Journal of Propulsion and Power, 2000, 16: 178–186.
文章导航

/