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首页> 外文期刊>Journal of Spacecraft and Rockets >Experimental and Numerical Simulation Study of Liquid-Propellant Draining from Rocket Tanks
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Experimental and Numerical Simulation Study of Liquid-Propellant Draining from Rocket Tanks

机译：火箭坦克液体推进剂排放实验与数值模拟研究

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AN UNDERSTANDING of the process by which liquidnpropellant drains from a rocket tank is important for propellantnmanagement, because residual propellant in the tank affects launchncapability. Turbopump rocket engines must cut off before thenpressurant gas enters the pump by means of gas ingestion or gasnblow-through to prevent overrotation and possible critical launchnfailure. Thus, some amount of propellant always remains in the tank.nSeveral types of propellant management devices can be placednnear the tank outlet; the configuration of the devices depends uponnlaunch system requirements [1–4]. To better understand how tondesign these devices, we need to study the propellant-drainingnprocess. However, for such studies, large-scale or inflexible devices,nsuch as full-scale propellant tanks with cryogenic propellant undernhigh-acceleration or low-gravity conditions, are clearly impractical.nNumerical procedures based on findings from small-scale experi-nments are muchmore desirable. Recently, with progress in computerntechnology and simulation techniques, a few numerical invesReceived 4 December 2009; revision received 27 May 2010; accepted fornpublication 2 June 2010. Copyright © 2010 by the American Institute ofnAeronautics and Astronautics, Inc. All rights reserved. Copies of this papernmay be made for personal or internal use, on condition that the copier pay then$10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 RosewoodnDrive, Danvers, MA 01923; include the code 0022-4650/10 and $10.00 inncorrespondence with the CCC.
机译：了解液体推进剂从火箭箱中排出的过程对推进剂的管理很重要，因为坦克中残留的推进剂会影响发射能力。涡轮泵火箭发动机必须先切断，然后增压气体通过进气或吹气进入泵，以防止过度旋转和可能的严重启动故障。因此，一定数量的推进剂始终残留在油箱中。n几种类型的推进剂管理装置可以放置在油箱出口附近；设备的配置取决于启动系统的要求[1-​​4]。为了更好地了解如何设计这些设备，我们需要研究推进剂排放过程。但是，对于此类研究，显然不切实际，例如在高加速度或低重力条件下使用带有低温推进剂的全尺寸推进剂罐等带有低温推进剂的大型推进剂罐。理想的。最近，随着计算机技术和仿真技术的进步，一些数值研究已于2009年12月4日收到。 2010年5月27日收到修订本；于2010年6月2日被接受。2011年美国航空航天学会版权所有。保留所有权利。可以将本文件的副本用于个人或内部使用，但前提是复印机须向版权许可中心（Inc.，222 RosewoodnDrive，Danvers，MA 01923）支付每本10美元的费用。包括代码0022-4650 / 10和与CCC无关的$ 10.00美元。

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