Studying on Burning Rate of Propellant under Diverse Parameters

被引：0
|
作者：
Chu, Hung-Ta [1 ]
机构：
[1] Chung Shan Inst Sci & Technol, POB 90008-21-4, Pingtung 947, Taiwan
来源：
WORLD CONGRESS ON ENGINEERING AND COMPUTER SCIENCE, WCECS 2012, VOL II | 2012年
关键词：
AP; burning rate;
D O I：
暂无
中图分类号：
TP39 [计算机的应用];
学科分类号：
081203 ; 0835 ;
摘要：
An experimental investigation on the burning rates and mechanical properties of HTPB propellants with Fe2O3 and AP is carried out at pressure in the range from 10 to 14 MPa and universal tester. The content of Fe2O3 and the oxidizer particle size distribution have a considerable effect on the burning rate of the propellant.
引用
收藏
页码：749 / 751
页数：3
相关论文
共 50 条
  • [21] Burning rate measurement of solid propellant using ultrasound - Approach and initial experiments
    Song, SJ
    Jeon, JH
    Kim, HJ
    Kim, IC
    Yoo, JC
    Jung, JY
    REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION, VOLS 25A AND 25B, 2006, 820 : 1229 - 1236
  • [22] Effect of aluminum particle size on agglomeration size and burning rate of composite propellant
    Fukuchi, Apollo B.
    JOURNAL OF THERMAL SCIENCE AND TECHNOLOGY, 2022, 17 (01):
  • [23] Study of the enhanced burning rate during the plasma-propellant interaction process
    Wang, Qian
    Yang, Weihong
    Hang, Yuhua
    Fan, Hao
    Li, Xingwen
    JOURNAL OF PHYSICS D-APPLIED PHYSICS, 2019, 52 (33)
  • [24] Calculation of pressure in a solid-propellant rocket motor with the use of a real dependence of the solid propellant burning rate on pressure
    Lipanov, A. M.
    COMBUSTION EXPLOSION AND SHOCK WAVES, 2017, 53 (05) : 569 - 573
  • [25] Calculation of pressure in a solid-propellant rocket motor with the use of a real dependence of the solid propellant burning rate on pressure
    A. M. Lipanov
    Combustion, Explosion, and Shock Waves, 2017, 53 : 569 - 573
  • [26] Methodical problems of solid-propellant burning-rate measurements using microwaves
    V. E. Zarko
    D. V. Vdovin
    V. V. Perov
    Combustion, Explosion and Shock Waves, 2000, 36 : 62 - 71
  • [27] Burning rate and pressure deflagration limit (PDL) characteristics of a GAP/AP propellant system
    Hori, K
    Kohno, M
    Volpi, A
    Zanotti, C
    Kato, K
    Miyazaki, S
    COMBUSTION OF ENERGETIC MATERIALS, 2002, : 513 - 522
  • [28] Study the effect factor on the burning rate of propellant used in cable bridge plug system
    Wenfang, Zheng
    Feng, Sha
    Jin, Yu
    Ya, Wang
    Renming, Pan
    Xiangyang, Lin
    THEORY AND PRACTICE OF ENERGETIC MATERIALS, VOL VII, 2007, : 538 - 542
  • [29] Study on the action temperature of catalysts to solid propellant burning rate using embedded thermocouple
    Wang, NF
    Wang, LA
    COMBUSTION OF ENERGETIC MATERIALS, 2002, : 244 - 250
  • [30] Effect of voids inside AP particles on burning rate of AP/HTPB composite propellant
    Kohga, Makoto
    PROPELLANTS EXPLOSIVES PYROTECHNICS, 2008, 33 (04) : 249 - 254
12345