Propulsion Related Missile Phenomena

This effort entails the modeling of a variety of propulsive related missile phenomena of interest to MDA with an emphasis on lower altitude (h< 70km) problems, as well as on continuum/non-continuum bridging to provide the correct initial conditions for DSMC solutions. Phenomena to be modeled include: post-shutdown fuel venting and motor/nozzle debris expulsion; transient control jet and shutdown/staging venting problems; fuel venting associated with laser puncture for lethality evaluation; contrail/extended plumes including secondary smoke formation; and depressed trajectory, hypersonic missile scramjet propelled plumes. Advanced multiphase (breakup, vaporization/condensation) and highly-specialized thermochemistry models will be utilized. Deliverables will include extended versions of the new MDA/AFRL RPFM rocket plume code that will be able to provide rapid engineering solutions to these propulsive phenomena (minutes on small clusters) using a GUI-based framework with self-contained gridding, grid adaptation, and thermochemical data banks. Also addressed in this Phase II effort is the interfacing required for high-altitude propulsive phenomena (via a cooperative effort with L. Bernstein/Spectral Sciences, Inc. to interface our continuum solutions with the SOCRATES-P DSMC solutions) and the interfacing required to provide requisite data sets for scene generation (via collaboration with D. Crow/Kinetics, Inc. to provide data sets for use with the FLITES code).