Accession Number : AD0022191


Title :   INVESTIGATION OF LIQUID ROCKET PROPELLANTS


Descriptive Note : Quarterly rept.


Corporate Author : AEROJET-GENERAL CORP AZUSA CA


Personal Author(s) : Enzer, T B ; Graefe, A F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/022191.pdf


Report Date : 08 Oct 1953


Pagination or Media Count : 42


Abstract : Thermal decomposition of MeNO2: Investigation of the effect of additives on the thermal decomposition of MeNO2 at relatively high pressures was continued. Studies were made to determine how additives that are known or postulated intermediates in the decomposition of MeNO2 affect the course of the reaction and to determine the reason that the addition of 5% or more of gaseous O to MeMO2 in a rocket motor lowers the characteristic length and the pressure required for stable operation. All the decomposition tests were conducted at 335 deg C, at pressures from 150 to 225 psia, and for various durations of heating. Rocket propellants: A successful approach to the problem of synthesizing alkyl derivatives of the higher hydronitrogens is in the careful oxidation of a trialkylhydrazine. An attempt was made to prepare a representative compound through the action of formaldehyde on trimethylhydrazine in order to determine the suitability of simple dihydrazines as high-energy fuels. Propellant compounds: A study was initiated to determine the feasibility of employing certain acetylide salts as propellant compounds that will depress the freezing point or vapor pressure of existing propellants without simultaneously lowering the specific impulses. By properly selecting the cation, salts that are both stable and possess relatively high energy could possibly be produced. Engine testing: High specific impulse of 272 lb-sec/lb and a characteristic velocity of 6720 fps were obtained in the 100-lb-thrust rocket motor. A summary of the data and curves of the experimental performance parameters are presented.


Descriptors :   *LIQUID ROCKET PROPELLANTS , CHEMICAL STABILITY , HIGH PRESSURE , HIGH ENERGY , FREEZING , OXIDATION , HEATING , LIQUID PROPELLANT ROCKET ENGINES , ADDITIVES , VAPOR PRESSURE , DECOMPOSITION , SPECIFIC IMPULSE , FORMALDEHYDE , TEST AND EVALUATION , PARAMETERS


Subject Categories : Liquid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE