Nanocomposite Metal-Based Ingredients for Use as Solid Propellant Burn Rate Modifiers

Phase I program showed feasibility of the reactive nanocomposite materials as burn rate modifiers for aluminized propellants. The compatibility of nanocomposite materials with propellant components was established. The increases in burning efficiency and burning rate of aluminum were achieved. Aluminum agglomeration was alleviated and the practically achieved energy density of propellants was increased. The pressure exponent was reduced as a result of a higher achieved burn rate and better combustion efficiency. The current results are based on laboratory evaluations including window bomb and strand burner studies. The proposed Phase II program includes performance testing in the rocket motor configuration. The work will be aimed to identify specific propellant applications for which the proposed burn rate modifiers can be developed in a shortest time; develop a scalable manufacturing process of nanocomposites which does not include handling of sensitive materials; optimize and tailor properties and compositions of the produced nanocomposite powders according to the identified application; and prepare and provide to industry partner sufficient amounts of materials for incorporating into propellant formulations and safety evaluations. Six nanocomposite modifier compositions will be selected and evaluated in 1-lb propellant mixtures. One nanocomposite composition will be downselected for tests in different scale laboratory rocket motors.