Theoretical performance analysis of Mg/CO2 powdered rocket engine

被引：0
|
作者：
Li, Fang [1 ]
Hu, Chun-Bo [1 ]
He, Guo-Qiang [1 ]
机构：
[1] National Key Laboratory of Combustion, Flow and Thermo-Structure, College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
来源：
Guti Huojian Jishu/Journal of Solid Rocket Technology | 2010年 / 33卷 / 04期
关键词：
Propulsion; -; Rockets;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
The theoretical performance of the powdered rocket engine is calculated theoretically in considering the specific impulse and the impact of factors. Compared with the traditional propulsion system, the powdered rocket engine has better specific impulse. In the calculation research of the performance of Mg and CO2, the rules of burning pressure, starting temperature and oxidizer-to-fuel ratio (by mass) were obtained.
引用
收藏
页码：414 / 418
相关论文
共 50 条
  • [11] Regenerative-Cooling Heat-Transfer Performance of Mg/CO2 Powder Rocket Engines for Mars Missions
    Zhu, Supeng
    Wei, Ronggang
    Hu, Chunbo
    Li, Chao
    INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, 2023, 24 (03) : 928 - 935
  • [12] Regenerative-Cooling Heat-Transfer Performance of Mg/CO2 Powder Rocket Engines for Mars Missions
    Supeng Zhu
    Ronggang Wei
    Chunbo Hu
    Chao Li
    International Journal of Aeronautical and Space Sciences, 2023, 24 : 928 - 935
  • [13] Theoretical analysis of performance of solid rocket scramjet
    Zhao X.
    Xia Z.
    Fang C.
    Ma L.
    Li C.
    Duan Y.
    Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica, 2023, 44 (05):
  • [14] Propulsive performance analysis of rotating detonation rocket engine
    Zhu Y.
    Wang K.
    Fan W.
    Tuijin Jishu/Journal of Propulsion Technology, 2024, 45 (02):
  • [15] PERFORMANCE ANALYSIS OF A ROTATING DETONATION WAVE ROCKET ENGINE
    ADAMSON, TC
    OLSSON, GR
    ASTRONAUTICA ACTA, 1967, 13 (04): : 405 - &
  • [16] The concept of a rocket engine using CO2/metal propellants for Mars sample return missions
    Gökalp, I
    Shafirovich, E
    THIRD INTERNATIONAL CONFERENCE ON SPACECRAFT PROPULSION, 2000, 465 : 219 - 227
  • [17] Performance of CO2 enrich CNG in direct injection engine
    Firmansyah
    Ayandotun, W. B.
    Zainal, E. Z.
    Aziz, A. A. R. A.
    Heika, M. R.
    3RD INTERNATIONAL CONFERENCE OF MECHANICAL ENGINEERING RESEARCH (ICMER 2015), 2015, 100
  • [18] Theoretical analysis and comparison on supercritical CO2 based combined cycles for waste heat recovery of engine
    Pan, Mingzhang
    Zhu, Yan
    Bian, Xingyan
    Liang, Youcai
    Lu, Fulu
    Ban, Zhibo
    ENERGY CONVERSION AND MANAGEMENT, 2020, 219
  • [19] Potential CO2 utilisation in Germany: An analysis of theoretical CO2 demand by 2030
    Schmid, Christopher
    Hahn, Alena
    JOURNAL OF CO2 UTILIZATION, 2021, 50
  • [20] Theoretical effects of aluminum gel propellant secondary atomization on rocket engine performance
    Mueller, DC
    Turns, SR
    JOURNAL OF PROPULSION AND POWER, 1996, 12 (03) : 591 - 597
12345