留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

H2O2/HTPB固液火箭发动机燃料配方正交优化设计

曾鹏 田辉 李新田 蔡国飙

曾鹏, 田辉, 李新田, 蔡国飙. H2O2/HTPB固液火箭发动机燃料配方正交优化设计[J]. 航空动力学报, 2013, 28(5): 1180-1186.
引用本文: 曾鹏, 田辉, 李新田, 蔡国飙. H2O2/HTPB固液火箭发动机燃料配方正交优化设计[J]. 航空动力学报, 2013, 28(5): 1180-1186.
ZENG Peng, TIAN Hui, LI Xin-tian, CAI Guo-biao. Orthogonal optimal design of solid fuel formulation for H2O2/HTPB hybrid rocket motor[J]. Journal of Aerospace Power, 2013, 28(5): 1180-1186.
Citation: ZENG Peng, TIAN Hui, LI Xin-tian, CAI Guo-biao. Orthogonal optimal design of solid fuel formulation for H2O2/HTPB hybrid rocket motor[J]. Journal of Aerospace Power, 2013, 28(5): 1180-1186.

H2O2/HTPB固液火箭发动机燃料配方正交优化设计

Orthogonal optimal design of solid fuel formulation for H2O2/HTPB hybrid rocket motor

  • 摘要: 采用随机轨道法计算了H2O2/HTPB固液火箭发动机的喷管两相流,并采用试验结果验证了数值计算的准确性.研究了不同凝相质量分数和粒子平均直径对喷管性能的影响,结果表明:随着凝相质量分数和粒子平均直径的增加,喷管效率逐渐降低.对固体燃料中的Al,Mg,AP和B等组分的质量分数进行了正交试验设计,研究分析了不同燃料组分对喷管两相流和发动机性能的影响,并对固体燃料配方进行了正交优化设计.结果表明:凝相组分质量分数随Al,Mg的质量分数增大而增加,AP和B的质量分数对凝相质量分数影响较小;添加Al,Mg,AP和B等物质对发动机的最佳理论比冲影响不大,但可以有效提高最佳理论密度比冲;添加Al和Mg等金属颗粒会增加喷管损失,降低实际比冲和实际密度比冲,添加AP和B对比冲效率影响不大.

     

  • [1] Zilliac G.Hybrid rocket propulsion:past,present,and future[R].NASA Ames Research Center,2010.
    [2] Karabeyoglu A.Hybrid rocket propulsion for future space launch[R].Palo Alto,US:Space Propulsion Group Inc,2008.
    [3] 杨玉新,胡春波,何国强,等.固液混合火箭发动机中的关键技术及其发展[J].宇航学报,2008,29(5):1616-1621. YANG Yuxin,HU Chunbo,HE Guoqiang,et al.Key technique of hybrid rocket motor and its development[J].Journal of Astronautics,2008,29(5):1616-1621.(in Chinese)
    [4] Davydenko N A,Gollender R G,Gubertov A M,et al.Hybrid rocket engines:the benefits and prospects[J].Aerospace Science And Technology,2007,11(1):55-60.
    [5] 胡建新,夏智勋,张钢锤.固液火箭发动机在空间发射上的应用前景[J].导弹与航天运载技术,2002(3):18-22. HU Jianxin,XIA Zhixun,ZHANG Gangchui.The opportunity for hybrid rocket motor in commercial space applications[J].Missiles and Space Vehicles,2002(3):18-22.(in Chinese)
    [6] 单建胜,雷宁.固液混合发动机的研制及其应用[J].固体火箭技术,1997,20(3):13-20. SHAN Jiansheng,LEI Ning.The development and applications of solid-liquid hybrid rocket motors[J].Journal of Solid Rocket Technology,1997,20(3):13-20.(in Chinese)
    [7] 田辉,蔡国飙,孙再庸.N2O/HTPB固液火箭发动机喷管两相流计算[J].航空动力学报,2008,23(6):1146-4450. TIAN Hui,CAI Guobiao,SUN Zaiyong.Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor[J].Journal of Aerospace Power,2008,23(6):1146-4450.(in Chinese)
    [8] 田辉,蔡国飙,王慧玉,等.固液混合火箭发动机喷管流动计算[J].航空动力学报,2005,20(1):142-146. TIAN Hui,CAI Guobiao,WANG Huiyu,et al.Nozzle flow computation of classical hybrid rocket motors[J].Journal of Aerospace Power,2005,20(1):142-146.(in Chinese)
    [9] Chiaverini M J,Kuo K K,Peretz A,et al.Regression-rate and heat-transfer correlations for hybrid rocket combustion[J].Journal of Propulsion and Power,2001,17(1):99-110.
    [10] Chiaverini M J,Serin N,Johnson D K,et al.Regression rate behavior of hybrid rocket solid fuels[J].Journal of Propulsion and Power,2000,16(1):125-132.
    [11] Chiaverini M J,Harting G C,Kuo K K.Pyrolysis behavior of hybrid-rocket solid fuels under rapid heating conditions[J].Journal of Propulsion and Power,1999,15(6):888-895.
    [12] George P,Krishnan S,Varkey P M,et al.Fuel regression rate in hydroxyl-terminated-polybutadiene/gaseous-oxygen hybrid rocket motors[J].Journal of Propulsion and Power,2001,17(1):35-42.
    [13] Frederick R A,Jr Whitehead J J,Knox L R,et al.Regression rates study of mixed hybrid propellants[J].Journal of Propulsion and Power,2007,23(1):175-180.
    [14] Peretz A,Einav O,Hashmonay B A,et al.Development of a laboratory-scale system for hybrid rocket motor testing[J].Journal of Propulsion and Power,2011,27(1):190-196.
    [15] Risha G A,Ulas A,Boyer E,et al.Combustion of HTPB-based solid fuels containing nano-sized energetic powder in a hybrid rocket motor[R].AIAA 2001-3535,2001.
    [16] Risha G A,Boyer E,Wehrman R B,et al.Performance comparison of HTPB-based solid fuels containing nano-sized energetic powder in a cylindrical hybrid rocket motor[R].AIAA 2002-3576,2002.
    [17] Risha G A,Evans B J,Boyer E,et al.Nano-sized aluminum and boron-based solid fuel characterization in a hybrid rocket engine[R].AIAA 2003-4593,2003.
    [18] Risha G A.Enhancement of hybrid rocket combustion performance using nano-sized energetic particles[D].Central County,US:The Pennsylvania State University,2003.
    [19] Evans B,Boyer E,Kuo K K.Hybrid rocket investigations at Penn State University's high pressure combustion laboratory overview and recent results[R].AIAA 2009-5349,2009.
  • 加载中
计量
  • 文章访问数:  1800
  • HTML浏览量:  215
  • PDF量:  999
  • 被引次数: 0
出版历程
  • 收稿日期:  2012-07-20
  • 刊出日期:  2013-05-28

目录

    /

    返回文章
    返回