Accession Number : AD0111376
Title : Microrocket Studies: Application to Low-Temperature Rocket Performance.
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE HYDROGEN PEROXIDE LABS
Personal Author(s) : Darling, Bradford ; Wolf, Saul
Report Date : 10 DEC 1953
Pagination or Media Count : 27
Abstract : This paper presents an evaluation of the micro-rocket as an experimental tool in liquid rocket research with specific application to hydrogen peroxide-hydrazine systems. Apparatus and equipment were microcounter-parts of full scale thrust motor systems except for the injectors and feed system. Two or three orifice injectors were used in the micro-rocket motors in contrast to the many pairs of orifices found in large scale motors. Feed was accomplished by positive displacement, permitting constant flow rates independent of pressure variations in the reaction motor. Combinations of combustion chamber lengths from 1 1/2 to 4 inches and diameters from 0.144 to 0.179 inches were tested with various injectors. The ratio of experimental chamber pressure to that theoretically obtained for complete combustion was selected as the criterion of combustion efficiency. Overall performance was judged by comparing experimental specific impulse with the value calculated for a perfect motor operating with complete combustion over the same pressure range. Based on these criteria and on smoothness of operation, the performance approximated that commonly obtained in large-scale reaction motors of equal residence time, provided a good system of injection was used.
Descriptors : *LIQUID ROCKET PROPELLANTS, TEST EQUIPMENT.
Distribution Statement : APPROVED FOR PUBLIC RELEASE