Summary

Description

<p>The proposed effort will explore the feasibility and effectiveness of utilizing an electrically driven thermal shield for use as part of rocket plume deflectors. To accomplish this, a small scale prototype deflector cover will be designed and tested. The overall reduction in thermal conduction will then be observed using high speed thermal imagining. The goal is to achieve a ten percent reduction; however, any thermal reduction would be considered a valuable success. The fundamental principles from a small scale system could then be used to economically scaled up for deployment within full-size rocket propulsion system.</p>