Combustion Stability in Small Thrusters

Compact, high energy storable propellant thrusters are needed for a wide variety of applications from sattelite control to space missions to missile defense systems. As the thrusters are made smaller, higher performing, with more intense energy release and are needed to operate in more extreme environments, combustion instability becomes a more difficult problem. This program brings to bear the most recent university work in linear and nonlinear instability modeling and takes that knowledge to practical application using data from a current highly tested small divert thruster to provide preliminary verification. The approach is to use linear and non linear studies of combustion gain combined with latest absorber damping technology to provide practical design criteria for these small energetic combustors. The results will include the preliminary design criteria and a proposal for a Phase II hot fire demonstration of the thruster design with this criteria.