RESEARCH AND DEVELOPMENT ON THE BASIC DESIGN OF STORABLE HIGH-ENERGY PROPELLANT SYSTEMS AND COMPONENTS
BELL AEROSYSTEMS CO BUFFALO NY
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Studies were made of nitrogen tetroxide N2O4, unsymmetrical dimethylhydrazine UDMH, and hydrazine N2H4 . Pertinent physical property data is presented for each propellant. Data concerning g propellant decomposition ca ed by such contaminants as aluminum and stainless steel chips, lint, constituents of air and hot pressurizing gases is included. High temperature, low temperature, and cycling temperature tests were conducted with each propellant in tanks made of type 347 stainless steel, 6061-T6 aluminum, PH 15-7 Mo stainless steel and C 120 AV titanium. Three explosions were encountered with N2H4 in stainless steel tanks 347 stainless steel a d PH 15-7 Mo stainless steel at temperatures above 290 F. Other than slight decomposition, no problems were encountered with UDMH STORED AT TEMPERATURES UP TO F. If N2O4 is maintained ed in the anhydrous state and high vapor pressure can be tolerated, no problems will be expected with N2O4 stored in type 347 stainless steel, PH 15-7 o stainless steel, and 6061-T6 aluminum tanks up to 270 F.
- Liquid Rocket Propellants