Plasma Processes, LLC — Department of Defense SBIR Phase I: MDA14-002

Description

Plasma Processes non-eroding throat liner technology for aluminized propellants has been significantly matured since 1999. An upcoming full-scale test will demonstrate that the technology is sufficient for transition consideration. However, there remain gaps in the technology that must be addressed prior to transition. The objective of this effort is to address these obstacles in order to expedite technology adoption by a prime and/or con-sideration for an Engineering and Manufacturing Development program. Specifically, the Phase I will involve initial thermo-structural analysis to qualify baseline throat liner designs for an unclassified/sanitized upper stage solid rocket motor environment. This design activity will also in-clude a mass reduction study that will focus on balancing manufacturability, structural integrity during handling and operation, and lowest possible mass of the tungsten based throat liner. The Phase I will also focus on defining a specific manufacturing plan for down-selected upper stage solid rocket motor throat liner designs. The Phase I will conclude with preliminary manufacturing trials of baseline and reduced mass throat liner designs. A Phase II will concentrate on optimizing the manufacturing process defined in Phase I; improving manufacturing attrition rate; maturing the mechanical property database; detailed analysis of an actual upper stage solid rocket motor environment using a higher fidelity property database; and r hot fire testing in a relevant upper stage solid rocket motor environment. Approved for Public Release 14-MDA-8047 (14 Nov 14)