DEVELOPMENT OF LOW TEMPERATURE GAS GENERATOR TECHNOLOGY
Final rept. 3 Jan-14 Nov 1966
ROCKET RESEARCH CORP SEATTLE WA
Pagination or Media Count:
The objective of this program was to characterize monopropellant hydrazine-based monopropellants which, by the use of ammonia and ammonia-water diluents, are capable of producing clean, low temperature gases when passed through a catalytic decomposition chamber. During the course of the 12-month program, thermochemical calculations were performed on a large number of cases involving various compositions of hydrazine, ammonia, and water. The effect of varying the amount of ammonia dissociation was investigated in the above calculations. Based upon the results of the thermochemical calculations and preliminary physical property testing, seven different solutions composed of various concentrations of hydrazine, water andor ammonia were selected for further evaluation. The freezing points of the solutions were determined and the vapor pressures, densities, and viscosities were measured over a wide temperature range. A low temperature gas generator was designed to produce approximately 60 standard cubic feet of gas per minute and to operate at a nominal chamber pressure of 300 psi. This gas generator was fired with each of the seven monopropellants in order to determine their steady state performance characteristics. In addition, a 1 lbf gas generator thruster was fired in pulse mode operation at various pulse widths and duty cycles with each of the seven monopropellants. The complete test results are presented in tabular form.
- Physical Chemistry
- Hydraulic and Pneumatic Equipment
- Liquid Rocket Propellants