MIL-STD-1901A Compliant Igniter Energetic for Solid Rocket Motors

The Phase I program developed and tested several energetic compositions. These were compared to two baseline compositions, such as a double-base propellant and B/KNO3 with promising results. The comparisons were made through laboratory tests such as a)bomb calorimetry (in O2 and Ar) in terms of exothermicity per unit mass and volume, b)reaction rate (rise time) to a maximum temperature, c)pressure and total reaction time (i.e., energy envelope). These tests confirmed promise in terms of higher thermal output and pressure, adequate short rise time, low sensitivity, and better aging properties due to the absence of oxidizer in the composition. In the Phase II effort we propose a) expansion of Phase I results and completion of safety evaluation described in MIL-STD-1751A to demonstrate energetic compliance, b)design, fabricate and test a prototype ignition system (using the down-selected composition) to demonstrate performance requirements, c) produce and deliver igniter units to MDA for further testing if required, d) further testing in a small solid-propellant rocket motor and e) work with an identified automated pellet production company for future scale-up. Approved for Public Release | 20-MDA-10643 (3 Dec 20)