真空应用电火花点火的氢氧发动机设计与试验

吴靖; 张国舟; 蔡国飙

doi:10.13224/j.cnki.jasp.2014.02.020

真空应用电火花点火的氢氧发动机设计与试验

doi: 10.13224/j.cnki.jasp.2014.02.020

北京航空航天大学宇航学院, 北京 100191

计量
- 文章访问数: 1605
- HTML浏览量: 2
- PDF量: 1126
- 被引次数: 0
出版历程
- 收稿日期: 2012-12-13
- 刊出日期: 2014-02-28

Design and experiment of gaseous hydrogen/oxygen engine igniting with electric spark igniting in vacuum

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为研究某大推力氢氧发动机真空羽流效应，设计采用火炬点火方式的60N缩比氢氧发动机.通过球头密封声速喷嘴组件控制流量，使真空下每个声速喷嘴组件减少3个密封面.进行真空点火方案设计，从理论上证明电火花点火的可行性.设计试验系统并进行地面及真空环境下的热试车，试车结果表明：燃烧室压力达到额定压力为0.6MPa时，发动机热防护结构良好，试验系统设计合理，真空电火花点火方案可行，为进行真空羽流效应研究奠定基础.
- 氢氧 /
- 缩比发动机 /
- 真空 /
- 电火花点火 /
- 球头密封声速喷嘴
Abstract: In order to investigate the vacuum plume effects of a large-thrust hydrogen/oxygen engine, a shrink ratio gaseous hydrogen/oxygen engine of 60N-thrust with torch igniting method was designed. The mass flow rate was controlled by a sonic nozzle with ball-end seal, such that 3 sealing faces were reduced in every assembly compared to the traditional one. The vacuum igniting scheme was designed, and the feasibility of igniting with electric spark was confirmed in theory. The experiment system was devised and the heat test run was conducted in both ground and vacuum conditions. The results show that when the chamber pressure reaches nominal 0.6MPa, the thermal protective structure of the engine works well, the experiment system is reasonable, and the scheme of igniting with electric spark in vacuum is feasible, laying a solid foundation for the vacuum plume effect investigation.
- hydrogen/oxygen /
- shrink ratio engine /
- vacuum /
- electric spark igniting /
- sonic nozzle with ball-end seal

HTML

参考文献(15)

[1]	蔡国飙, 祖国君, 王慧玉, 等.羽流问题研究概况[J].推进技术, 1995, 15(4):50-54. CAI Guobiao, ZU Guojun, WANG Huiyu, et al.The sketchy situation of study on plume[J].Journal of Propulsion Technology, 1995, 15(4):50-54.(in Chinese)
[2]	徐义华, 胡春波, 张胜敏, 等.固体火箭发动机羽流红外辐射特性研究[J].固体火箭技术, 2010, 33(2):176-181. XU Yihua, HU Chunbo, ZHANG Shengmin, et al.Study on infrared radiative characters of the SRM plume[J].Journal of Solid Rocket Technology, 2010, 33(2):176-181.(in Chinese)
[3]	肖泽娟, 程惠尔, 李鹏, 等.模拟空间环境下小发动机羽流压力场[J].推进技术, 2007, 28(6):633-636. XIAO Zejuan, CHENG Huier, LI Peng, et al.Pressure of a small nozzle plume flow in simulated space environment[J].Journal of Propulsion Technology, 2007, 28(6):633-636.(in Chinese)
[4]	Farhangi S, Yu T, Rojas L, et al.Gas-gas injector technology for full flow stage combustion cycle application[R].AIAA 99-2757, 1999.
[5]	Archambault M R, Talley D, Peroomian O.Computational analysis of a single-element shear-coaxial GH2_GO2 engine[R].AIAA 2002-1088, 2002.
[6]	CAI Guobiao, WANG Xiaowei, JIN Ping, et al.Experimental and numerical investigation of large mass flow rate gas-gas injectors[R].AIAA 2008-4562, 2008.
[7]	杜正刚, 高玉闪, 李茂, 等.同轴双剪切气-气喷嘴试验研究[J].推进技术, 2010, 31(2):170-173. DU Zhenggang, GAO Yushan, LI Mao, et al.Experimental investigation on dual shear coaxial gas-gas injector[J].Journal of Propulsion Technology, 2010, 31(2):170-173.(in Chinese)
[8]	李茂, 高玉闪, 陈泽, 等.气氢/气氧富燃预燃室设计与试验[J].航空动力学报, 2011, 26(6):1426-1430. LI Mao, GAO Yushan, CHEN Ze, et al.Design and experiment for a GH2/GO2 fuel-rich preburner[J].Journal of Aerospace Power, 2011, 26(6):1426-1430.(in Chinese)
[9]	王新月.气体动力学基础[M].西安:西北工业大学出版社, 2006.
[10]	梁国柱, 马彬, 张国舟, 等.气动谐振管点火技术研究[J].推进技术, 2001, 22(4):286-289. LIANG Guozhu, MA Bin, ZHANG Guozhou, et al.Investigation on gas dynamic resonance tube ignition method[J].Journal of Propulsion Technology, 2001, 22(4):286-289.(in Chinese)
[11]	梁国柱, 马彬, 程显辰, 等.气动谐振管加热效应初步实验[J].推进技术, 2002, 23(1):52-56. LIANG Guozhu, MA Bin, CHENG Xianchen, et al.Preliminary experimental investigation on gas dynamic resonance tube heating effect[J].Journal of Propulsion Technology, 2002, 23(1):52-56.(in Chinese)
[12]	宋雅娜, 俞南嘉, 马彬, 等.基于气动谐振点火器的氢氧变轨火箭发动机地面点火试验[J].航空动力学报, 2005, 20(3):523-528. SONG Yana, YU Nanjia, MA Bin, et al.Ground ignition test of an orbit maneuver H2/O2 thruster based on gas dynamic resonance igniter[J].Journal of Aerospace Power, 2005, 20(3):523-528.(in Chinese)
[13]	俞南嘉, 张国舟, 马彬, 等.应用气动谐振点火的氢氧小发动机试验[J].推进技术, 2010, 31(2):134-138. YU Nanjia, ZHANG Guozhou, MA Bin, et al.Experimental investigation for hydrogen/oxygen engine using gas dynamic resonance ignition technique[J].Journal of Propulsion Technology, 2010, 31(2):134-138.(in Chinese)
[14]	侯清润, 茅卫红, 陈宜保.气体放电实验与帕邢定律[J].物理实验, 2004, 24(1):3-4. HOU Qingrun, MAO Weihong, CHEN Yibao.Gas discharge experiment and Paschen's law[J].Physics Experimention, 2004, 24(1):3-4.(in Chinese)
[15]	王文龙, 周建平, 蔡国飙.羽流效应地面模拟试验系统关键技术发展[J].航空动力学报, 2012, 27(4):900-906. WANG Wenlong, ZHOU Jianping, CAI Guobiao.Development of vacuum plume effects ground simulation experimental system key technology[J].Journal of Aerospace Power, 2012, 27(4):900-906.(in Chinese)