航天推进技术研究院主办
[1]张魏静,刘占一,刘计武,等.液体火箭发动机组件热真空虚拟试验技术[J].火箭推进,2021,47(04):64-70.
ZHANG Weijing,LIU Zhanyi,LIU Jiwu,et al.Virtual thermal vacuum test technology of liquid-propellant rocket engine components[J].Journal of Rocket Propulsion,2021,47(04):64-70.
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ZHANG Weijing,LIU Zhanyi,LIU Jiwu,et al.Virtual thermal vacuum test technology of liquid-propellant rocket engine components[J].Journal of Rocket Propulsion,2021,47(04):64-70.
液体火箭发动机组件热真空虚拟试验技术
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
47
期数:
2021年04期
页码:
64-70
栏目:
研究与设计
出版日期:
2021-08-31
- Title:
- Virtual thermal vacuum test technology of liquid-propellant rocket engine components
- 文章编号:
- 1672-9374(2021)04-0064-07
- Keywords:
- liquid-propellant rocket engine virtual test optical tracking method radiation heat-transfer
- 分类号:
- V434.3
- 文献标志码:
- A
- 摘要:
- 相比真实热真空试验,虚拟热真空试验能够有效降低研制成本,缩短研制周期。针对液体火箭发动机组件开展热真空虚拟试验技术研究,基于Sinda-fluint热分析软件建立了由真空舱、热沉、石英灯阵和具体发动机组件构成的热真空虚拟试验平台。热真空虚拟试验中存在大量的面面辐射换热,计算消耗极大,针对该问题采用蒙特卡洛光学追踪法进行处理。针对石英灯阵,分析了其热源特征,简化为高温平板模型并开展了验证试验,结果表明了模型的准确性。最后以某型发动机的流量调节装置为例,同步开展了实际热真空实验和虚拟热真空试验,通过对比测点温度变化曲线,发现在整个测试过程中,虚拟试验和实测值的最高温度偏差在10%以内,验证了虚拟试验平台的有效性。
- Abstract:
- Compared to the real thermal vacuum test,the virtual thermal vacuum test is able to reduce cost and time effectively during the product development.The investigation on virtual thermal vacuum test for liquid-propellant rocket engine components is carried out, and the virtual thermal vacuum environment test platform,which consists of vacuum chamber,heat sink,quartz lamp array and liquid-propellant rocket engine components,is built up based on the Sinda-fluint thermal analysis software.There is a great deal of surface-to-surface radiation heat-transfer in the virtual test,which is bound to consume massive computing resource.This problem is processed based on Monte Carlo optical tracking method.As to the quartz lamp array,its heat source characteristics are analyzed,and it is simplified as a high temperature plate.A proof test is carried out and the results show the accuracy of the model.Finally,taking a flow adjuster of a liquid-propellant rocket engine as an example,both the actual and the virtual thermal vacuum experiments are carried out simultaneously.According to the temperature variation during the whole test,the maximum temperature variation between the virtual test and the experimental results is less than 10% during the whole test process,which verifies the effectiveness of the virtual test platform.
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备注/Memo
收稿日期:2021-02-10
基金项目:民用航天技术预先研究项目(D020306)
作者简介:张魏静(1981—),女,硕士,高级工程师,研究领域为液体火箭发动机传热。
更新日期/Last Update:
1900-01-01