TY - GEN
T1 - Coaxial hydrogen/oxygen gas-dynamic resonance ignition technology for rocket repetitive starting
AU - Zhang, Guo Zhou
AU - Song, Ya Na
AU - Yu, Nan Jia
AU - Tong, Xiao Yan
AU - Ma, Bin
PY - 2007
Y1 - 2007
N2 - Gas-dynamic resonance ignition is a new technology prospective in repetitive starting of future space vehicle. Based on the investigation of structural and operational reliability for some schemes of hydrogen and oxygen resonance ignition, a novel type of coaxial hydrogen/oxygen resonance ignition scheme was advised. By means of more than 1000 times of gas-dynamic resonance heating mechanism tests, basic techniques of coaxial hydrogen/oxygen resonance ignition have been successfully investigated, including the characterization of resonance gas, verification of annular injector nozzle resonating performance, and the optimization of ignition device configuration etc. Firing tests on a basic hydrogen/oxygen resonance ignition tester have verified its ignition reliability and feasibility. Based on this basic coaxial hydrogen/oxygen resonance ignition tester, two types of coaxial hydrogen/oxygen resonance ignition devices have been developed that could be applied to the simultaneous ignitions of multi-combustor in aerospike nozzle engine, namely a multi-tube coaxial hydrogen/oxygen resonance igniter and a multi small coaxial hydrogen/oxygen resonance igniters assemblage. Firing tests on both devices have been qualified of reliable repetitive simultaneous ignition capacity for hydrogen/oxygen aerospike nozzle engine's repeated starting, of which the latter has better feasibility.
AB - Gas-dynamic resonance ignition is a new technology prospective in repetitive starting of future space vehicle. Based on the investigation of structural and operational reliability for some schemes of hydrogen and oxygen resonance ignition, a novel type of coaxial hydrogen/oxygen resonance ignition scheme was advised. By means of more than 1000 times of gas-dynamic resonance heating mechanism tests, basic techniques of coaxial hydrogen/oxygen resonance ignition have been successfully investigated, including the characterization of resonance gas, verification of annular injector nozzle resonating performance, and the optimization of ignition device configuration etc. Firing tests on a basic hydrogen/oxygen resonance ignition tester have verified its ignition reliability and feasibility. Based on this basic coaxial hydrogen/oxygen resonance ignition tester, two types of coaxial hydrogen/oxygen resonance ignition devices have been developed that could be applied to the simultaneous ignitions of multi-combustor in aerospike nozzle engine, namely a multi-tube coaxial hydrogen/oxygen resonance igniter and a multi small coaxial hydrogen/oxygen resonance igniters assemblage. Firing tests on both devices have been qualified of reliable repetitive simultaneous ignition capacity for hydrogen/oxygen aerospike nozzle engine's repeated starting, of which the latter has better feasibility.
UR - https://www.scopus.com/pages/publications/40549116313
M3 - 会议稿件
AN - SCOPUS:40549116313
SN - 1563479079
SN - 9781563479076
SN - 1563479079
SN - 9781563479076
T3 - A Collection of Technical Papers - AIAA Space 2007 Conference
SP - 1758
EP - 1774
BT - A Collection of Technical Papers - AIAA Space 2007 Conference
T2 - AIAA Space 2007 Conference
Y2 - 18 September 2007 through 20 September 2007
ER -