Accession Number : AD0507296

Title :   Development of Thermally Stable Liquid Fuels.

Descriptive Note : Final rept. 15 Dec 67-31 Jul 69,

Corporate Author : ESSO RESEARCH AND ENGINEERING CO LINDEN N J GOVERNMENT RESEARCH LAB

Personal Author(s) : Nixon,James ; Muenker,A. H. ; Outten,E. F. ; Brois,Stanley J.

Report Date : JAN 1970

Pagination or Media Count : 139

Abstract : New fuels must be developed to meet future Air Force missions which impose severe thermal stresses. They must be thermally stable at 400 F (less than 1% decomposition after one hour), have a density impulse with N2O4 equal to or greater than that of hydrazine, and good physical properties over the temperature range -65 to 400 F. This report covers the work carried out in three phases to develop such fuels. Phase I involved a literature survey, synthesis, theoretical performance calculations, thermal and physical evaluations of the thermally stable fuels. Four candidate fuels were selected which met all the above requirements, three of which are commercially available. The physical properties, long-term thermal stability, and compatibility of these fuels with metals and elastomers were evaluated in Phase II of the program. In Phase III, three of the candidate fuels were evaluated with N2O4 in a rocket motor. One of these fuels was found to be competitive with 50:50 hydrazine-UDMH, the reference fuel used in these combustion performance studies. (Author)

Descriptors :   (*LIQUID ROCKET FUELS, THERMAL STABILITY), LIQUID ROCKET OXIDIZERS, LIQUID ROCKET PROPELLANTS, THERMAL SHOCK, THERMAL STRESSES, HYDRAZINE, DIMETHYL HYDRAZINE (1-1), STORABLE ROCKET PROPELLANTS, SPECIFIC IMPULSE, NITROGEN OXIDES, TETROXIDES, LIQUID PROPELLANT ROCKET ENGINES (U) HIGH TEMPERATURE

Subject Categories : Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE