| 固体火箭发动机冷增压试验系统的设计与应用 |
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| 引用本文： | 唐国金,申志彬,宋先村,蒙上阳.固体火箭发动机冷增压试验系统的设计与应用[J].固体火箭技术,2011(4):423-425. |
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| 作者姓名： | 唐国金 申志彬 宋先村 蒙上阳 |
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| 作者单位： | 国防科技大学航天与材料工程学院;中国人民解放军63961部队; |
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| 基金项目： | 国防科技大学优秀研究生创新资助项目(B100103); “十二五”武器装备预先研究项目 |
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| 摘 要： | 针对固体火箭发动机药柱点火瞬态过程应变难以测量的工程难题,研制了固体火箭发动机冷增压试验系统.该系统利用高压气体对药柱内腔进行加压,模拟发动机点火增压过程,实现了药柱内表面应变的实时测量.利用该系统对某型号固体火箭发动机进行了冷增压试验,并将试验结果与数值仿真结果进行了对比,二者相对误差在8％以内.该试验系统操作方便,...
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| 关 键 词： | 固体火箭发动机 点火增压 冷增压 试验系统 |
Design and application of cold pressurization testing system for solid rocket motor |
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| TANG Guo-jin,SHEN Zhi-bin,SONG Xian-cun,MENG Shang-yang.Design and application of cold pressurization testing system for solid rocket motor[J].Journal of Solid Rocket Technology,2011(4):423-425. |
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| Authors: | TANG Guo-jin SHEN Zhi-bin SONG Xian-cun MENG Shang-yang |
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| Institution: | TANG Guo-jin1,SHEN Zhi-bin1,SONG Xian-cun1,MENG Shang-yang2(1.College of Aerospace and Materials Engineering,National University of Defense Technology,Changsha 410073,China,2.Chinese People Liberation Army 63961 Unit,Beijing 100012,China) |
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| Abstract: | In order to measure the strain of solid rocket motor(SRM) grain during ignition transient,SRM cold pressurization testing system was developed.The pressure gas was used to simulate the ignition pressurization process,and the real-time strains of grain on the inner surface were achieved by the system.The results of cold pressurization test and numerical simulation were compared,and the relative errors were within 8%.The test system feathers easy-to-use,stable function and accurate measurement. |
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| Keywords: | solid rocket motor ignition pressurization cold pressurization testing system |
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