DEPENDENCE OF BURNING RATE OF A COMPOSITE PROPELLANT ON CHEMICAL STRUCTURE OF FUEL

被引:0
|
作者
ROMODANO.LD
PEPEKIN, VI
APIN, AY
POKHIL, PF
机构
关键词
D O I
暂无
中图分类号
O414.1 [热力学];
学科分类号
摘要
引用
收藏
页码:365 / 369
页数:5
相关论文
共 50 条
  • [41] EFFECTIVE BURNING-RATE INHIBITORS IN AP/AL/HTPB COMPOSITE SOLID PROPELLANT
    Zhang, Wei
    Bao, Tong
    Zhou, Xing
    Song, Zhi-bing
    Hu, Fan
    29TH INTERNATIONAL SYMPOSIUM ON BALLISTICS, VOLS 1 AND 2, 2016, : 851 - 857
  • [42] Correlations of Uncertainties of Composite Propellant Strand Burner Burning Rate Measurement for Quality Control
    Liu, Tai-Kang
    PROPELLANTS EXPLOSIVES PYROTECHNICS, 2011, 36 (02) : 131 - 139
  • [43] Prediction of Burning Characteristics of Dihydroxyglyoxime Composite Propellant
    Jang, Jesun
    Kwon, Sejin
    JOURNAL OF PROPULSION AND POWER, 2023, 39 (05) : 743 - 753
  • [44] Method for measuring the porous structure of propellant of ultra-high burning rate
    Wang, Boxi
    Tuijin Jishu/Journal of Propulsion Technology, 1996, 17 (05): : 72 - 75
  • [45] BURNING RATE OF AN H-ATOM PROPELLANT
    PALMER, HB
    ARS JOURNAL, 1959, 29 (05): : 365 - 366
  • [46] EFFECT OF CHEMICAL-KINETICS ON BURNING RATE OF A PROPELLANT SLAB IN A TURBULENT OXIDIZER FLOW
    KUSTOV, YA
    RYBANIN, SS
    COMBUSTION EXPLOSION AND SHOCK WAVES, 1972, 6 (01) : 50 - &
  • [47] Study on low burning rate NEPE propellant
    Li, X.
    Liu, Y.
    Yao, W.
    Tan, H.
    Huozhayao Xuebao/Chinese Journal of Explosives and Propellants, 2001, 24 (03): : 1 - 3
  • [48] Comparative study on ignition delay time and burning rate of modified double-base propellant and fuel-rich propellant
    Li, Lian-bo
    Chen, Tao
    Li, Wei-xuan
    Yu, Rong-fu
    ANAIS DA ACADEMIA BRASILEIRA DE CIENCIAS, 2023, 95
  • [49] Bifurcations of propellant burning rate at oscillatory pressure
    Novozhilov, Boris V.
    PROPELLANTS EXPLOSIVES PYROTECHNICS, 2006, 31 (03) : 209 - 215
  • [50] Approach to decreasing the burning rate of NEPE propellant
    Wu, Fang
    Wang, Shi-Ying
    Pang, Ai-Min
    Guti Huojian Jishu/Journal of Solid Rocket Technology, 2002, 25 (02):