TY - JOUR
T1 - Performance comparison of pulse detonation rocket engine and liquid rocket engine with small thrust
AU - Mu, Yang
AU - Fan, Wei
AU - Yan, Yu
AU - Yan, Chuan Jun
PY - 2011/12
Y1 - 2011/12
N2 - In order to find out the performance advantage of pulse detonation rocket engine over a rocket engine, the primary objective of this research is to compare the thrust and the specific impulse of PDRE based on constant-volume cycle model with a rocket engine with small thrust. The results show that at vacuum conditions, with the increasing of initial temperature, the specific impulse increase not obviously. If the propellants are same and the sizes are similar, the thrust of PDRE is 3.0~6.8 times more than that of a liquid rocket engine's, while the specific impulses are equivalent.
AB - In order to find out the performance advantage of pulse detonation rocket engine over a rocket engine, the primary objective of this research is to compare the thrust and the specific impulse of PDRE based on constant-volume cycle model with a rocket engine with small thrust. The results show that at vacuum conditions, with the increasing of initial temperature, the specific impulse increase not obviously. If the propellants are same and the sizes are similar, the thrust of PDRE is 3.0~6.8 times more than that of a liquid rocket engine's, while the specific impulses are equivalent.
KW - A liquid rocket engine with small thrust
KW - Constant-volume cycle model
KW - Performance
KW - Pulse detonation rocket engine (PDRE)
UR - http://www.scopus.com/inward/record.url?scp=84855718739&partnerID=8YFLogxK
M3 - 文章
AN - SCOPUS:84855718739
SN - 0258-1825
VL - 29
SP - 697
EP - 701
JO - Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica
JF - Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica
IS - 6
ER -