Nanothermite composites containing metallic fuel and inorganic oxidizer have unique combustion properties that make them potentially useful for microthruster applications. The properties can be further tuned by addition of other chemicals in the nanoscale as required for different applications. The tailored characteristics of such energetic materials include tunable reaction rate, pressure and temperature. The present research effort will be aimed at characterizing various nanothermite materials in prototype thruster motors. The objective is to gain understanding of thrust performance of different nanothermites in different thruster motor designs. This will determine the most efficient material and motor design to produce the shortest possible thrust duration with the largest possible total impulse. The chamber design parameters such as structural material and cross-sectional area will be investigated to determine its effect on performance. Additionally, the type of nanocomposites and how it is loaded into the motor will be tested. Besides the actual thruster design considerations, the overarching consideration is the specific application in which the thrusters will be used. This will determine the ultimate requirements of the thrust impulse. Our goal will be to identify the specific guidance application and determine exact performance requirements leading to the development of fabrication and integration strategy.
Keywords: Nanothermites, Tunable Combustion Properties, Specific Impulse, Fast Actuation, Thrust, Short Duration, Projectiles, Fabrication And Integration Technology
