|Table of Contents|

Calculation and analysis of thermodynamic performance for nitrous oxide bipropellant engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2012年01期
Page:
44-50
Research Field:
研究与设计
Publishing date:

Info

Title:
Calculation and analysis of thermodynamic performance for nitrous oxide bipropellant engine
Author(s):
WANG Dong;  LIANG Guo-zhu
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
Keywords:
green propellantnitrous oxidebipropellant engineperformance analysis
PACS:
V434-34
DOI:
-
Abstract:
The physical properties of green propellants N2O, H2, CH3OH, C2H5OH, CH4, C2H6, C2H4, C2H2, C3H8 and C3H6 were compared. The thermodynamic performance of nine nitrous oxide bipropellants were calculated and analyzed completely with the minimum free energy method. N2O/H2 has the best specific impulse because of the lowest combustion gas average molar mass. N2O/C2H2 possesses the highest adiabatic combustion temperature which can reach 3 823 K owing to the high standard formation enthalpy of C2H2. The combustion gas of hydrocarbon fuel bipropellant contains carbon particles while its excess-oxidizer coefficient ?琢<0.4, and the carbon content which can reach 35% 40% at nozzle exit increases sharply with the ?琢 decrease. The theoretical equilibrium specific impulse of N2O/C3H8 and N2O/C3H6 under work condition of pc : pe=70 atm:1atm are 2 639 m/s and 2 656 m/s, and these two bipropellants possess attractive space application properties and highly thermodynamic performance.

References:

[1]李东, 马佳． 为什么要发展新一代运载火箭[J]． 太空探索, 2005, 22(2): 7-9．
[2]GIBBON D, PAUL M. Energetic green propulsion for small spacecraft, AIAA 2001-3247[R]. USA: AIAA, 2001.
[3]MAISONNEUVE Yves. Green propellants perspectives for future missions, AIAA 2008-5028 [R]. USA:AIAA, 2008.
[4]ZAKIROV V A. Investigation into nitrous oxide propulsion option for small satellite applications [D]. UK: Univ. of Surrey, 2001.
[5]ZAKIROV V, RICHARDSON G, SWEETING M, et al. Surrey research update on N2O catalytic decomposition for space applications, AIAA2001-3922[R]. USA: AIAA, 2001.
[6]ILIAKOS N T, TYLL J S. Development and testing of a nitrous oxide/propane rocket engine, AIAA 2001-3258[R]. USA: AIAA, 2001.
[7]KOPICZ C F, Jr., HERDY Roger. Nitrous oxide/propane rocket test results, AIAA 2000-3222[R]. USA: AIAA, 2000.
[8]ZAKIROV V, RICHARDSON G, SWEETING M, et al. Surrey research update on N2O catalytic decomposition for space applications, AIAA2001-3922[R]. USA: AIAA, 2001.
[9]贾月, 张浩． 氧化亚氮无毒推进剂催化分解研究[J]． 火箭推进, 2008, 34(3): 58-62．
[10]CAI G, SUN W, FANG J, et al. Initial results of BUAA nitrous oxide micro-thruster research[C]// Proceedings for the 58th International Astronautics Congress. Hyderabad, India: IAC, 2007: 5950-5956.
[11]贺芳, 方涛． 新型绿色液体推进剂研究进展[J]． 火炸药学报, 2006, 29(4): 54-57．
[12]姚允斌, 解涛． 物理化学手册[M]． 上海: 上海科学技术出版社, 1985．

Memo

Memo:
-
Last Update: 1900-01-01