This project will develop a computer simulation that, by modeling the transient operation of the propulsion system, will calculate contaminant properties at the nozzle-exit plane. The intended user for the simulator is the engineer with a background in propulsion. User interface and output management is provided by an expert system. Existing transient codes will be modified, improved, and integrated; a unique feature is that the chamber phenomena are simulated from rarefied regime to steady-state conditions. The simulator can also be employed to develop stability rating criteria and transient performance specifications. Phase I will establish the operational aspects of the simulator and the feasibility of the approach will be demonstrated with two sample cases. In Phase II, the code will be upgraded to simulate three-dimensional two-phase flow, and experimental work will be conducted to verify injector flow dynamics. The transient burning of propellant droplets will be verified in a small vertical shock tube facility.
Potential Commercial Applications: A likely commercial application is in the design, qualification, and selection of bipropellant engines for communication satellites. Future modifications of the code may be extended to simulate air-breathing engines (piston and turbine).STATUS: Phase I Only
