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液體火箭燃燒尾焰沖擊干擾效應(yīng)數(shù)值研究

Numerical study of impact and interference effect of liquid rocket combustion exhaust plume

  • 摘要: 火箭發(fā)射時(shí)其燃燒尾焰的沖擊干擾效應(yīng)對(duì)發(fā)射穩(wěn)定性和發(fā)射架、導(dǎo)流槽等地面設(shè)施有重要影響。文章采用壓力隱式算子分裂算法，通過(guò)求解Navier-Stokes方程，對(duì)氫氧液體火箭發(fā)動(dòng)機(jī)燃燒室內(nèi)燃燒過(guò)程與尾焰流場(chǎng)進(jìn)行了一體化數(shù)值計(jì)算，得到了火箭發(fā)射后尾焰與地面撞擊產(chǎn)生的沖擊流場(chǎng)。結(jié)果表明：尾焰流場(chǎng)計(jì)算模型、方法與結(jié)果合理；尾焰沖擊干擾效應(yīng)會(huì)大幅度提高地面附近的壓力和溫度；火箭尾焰撞擊地面后，高溫區(qū)出現(xiàn)在離地面一定距離的高溫層內(nèi)，此時(shí)地面附近為低速區(qū)；尾焰對(duì)其正下面的地面區(qū)域產(chǎn)生沖擊最大，主要干擾區(qū)域集中于半徑為15 m的圓形區(qū)域。

     

    Abstract: The impact and interference effect of the rocket combustion exhaust plume is an important issue related with the launching stability and the ground equipment, including the rocket launcher and the flow channel. Based on the PISO algorithm, numerical simulations of the combustion process and the plume flow field of a hydrogen-oxygen liquid rocket are carried out by solving the Navier-Stokes equation. The impact flow field when the exhaust plume is impacting the ground is obtained. The results show that the physical model, the numerical method and the flow field are reasonable. The pressure and the temperature increase greatly because of the impact and interference effect of the plume. During its impacting ground, in the plume, a high temperature zone appears with a high temperature level near the ground and with low velocities. The most important impact and interference effect shows in the ground area under the exhaust plume, and the main interference zone is in a circular area with a radius of 15 m.

     

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