A critical aspect of space platform maneuverability is the performance of rapid orbital changes. The standard type of steady-state chemical rocket, optimized for firing in the vacuum of space, is regarded as the base-line type of propulsion engine against which any new concept should be measured. In the present study of intermittently firing chemical rocket-type engines, such standard type rockets are taken as the reference. There are still open questions as to whether the specific impulse or propellant flow economy of a chemical propulsion rocket-like system might be improved by some modification of the combustion-and-outflow cycle. The concept of intermittent combustion-and-outflow represents an interesting alternative. The terminology used to describe such an intermittent process has been confusing in the past, with terms like detonative propulsion, explosive propulsion and pulsejet propulsion all having been used. One of the tasks of this project is necessarily to clarify the differences implied in these terms. This final report contains solutions to sample problems addressing combustion and outflow in chemical rockets (quasisteady analysis), and a recommended approach for non-steady optimization of thruster geometry. (edc)


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