国际能源材料和化学驱动期刊
每年出版 6 期
ISSN 打印: 2150-766X
ISSN 在线: 2150-7678
IF:
0.7
5-Year IF:
0.7
Immediacy Index:
0.1
Eigenfactor:
0.00016
JCI:
0.18
SJR:
0.313
SNIP:
0.6
CiteScore™::
1.6
H-Index:
16
Indexed in
STUDY ON THE SUBATMOSPHERIC BURNING RATE CHARACTERISTICS OF COMPOSITE PROPELLANTS
卷 3,
册 1-6, 1994,
pp. 624-633
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.600
摘要
The Institute of Space and Astronautical Science (ISAS) is undertaking development of its newest satellite launcher, M-V. HTPB-based highly aluminized composite propellents have been developed, and the subatmospheric burning rate characteristics of these propellents were investigated to properly anticipate the thrust decay behavior into the residual thrust region of each stage motor. A simple but unique method was employed in the measurements. The size of the propellent specimen was quite small; 8 mm long and 8 mm in diameter. Ignition was detected by a photo-transistor, and burnout by an ion probe or a fine thermocoupie.
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