Development and Testing of Nitrous Oxide/Propane Rocket Engine
- Paper number
IAC-13,C4,3,1,x17082
- Author
Dr. Wang Dong, Xi'an Aerospace Propulsion Institute, China
- Coauthor
Prof. Liang Guozhu, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Mr. Zhou Jun, Xi'an Aerospace Propulsion Institute, China
- Year
2013
- Abstract
A new rocket test stand facility, built at Beihang University, equipped with palletized propellant feed systems, 500-1500N thrust stand, and data acquisition systems, was constructed to test a nitrous oxide/propane(N2O/C3H8) rocket engine. A unique rocket ignition concept using N2O/C3H8 torch igniter was explored and influence of various mass mixing ratio were summarized. The hot test study for N2O/C3H8 principle engine is described. The N2O/C3H8 engine can be ignited quickly by igniter and work stably when the mixing ratio between 1.38 and 6.81. Meanwhile, the combustor equilibrium pressure varies in the scales of 0.257-0.514MPa, and the maximum average thrust is 140N. The experimental specific impulse improves obviously with the rise of mixing ratio, which increases from 1300m/s (mixing ratio is 3) to 1895.7m/s (mixing ratio is 6.56). The hot test results show that the intermediate frequency combustion instability (900-1000Hz) occurs at starting phase and low frequency combustion instability (65-80Hz) occurs at stable working phase.
- Abstract document
- Manuscript document
(absent)