International Journal of Energetic Materials and Chemical Propulsion
年間 6 号発行
ISSN 印刷: 2150-766X
ISSN オンライン: 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
巻 3,
発行 1-6, 1994,
pp. 624-633
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.600
要約
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.
1141 記事の閲覧数
15 記事のダウンロード
記事の統計
類似内容の記事:
最新号
近刊の記事
Effect of HMX Content on Thermal Safety Characteristics of Modified Double Base Propellants
40 Years with Chemical Propulsion – Research, Development and Application
Effects of Fluorinated and Non-Fluorinated Additives on Burning Rates of Boron-Teflon Blends for Solid Rocket Propulsion
Short Overview and Highlights of the History of the German Gel Propulsion Research and Technology Development Activities
Experimental study of boron carbide formation in combustion of boron-containing solid propellants
Electrochemical Burn Rate Acceleration
COMBUSTION OF ALUMINUM PARTICLES IN A STREAM OF STEAM