New energetic ingredients for solid rocket propulsion

Two metallized solid rocket propellant formulations, based on either the standard AP/HTPB matrix commonly used in space propulsion or the new matrix ADN/GAP, were analyzed. The two formulations in terms of ideal thermochemistry and experimental combustion properties were compared. Thus, a dual-oxidizer system bound by an active binder and loaded with a dual metal fuel was proposed as optimum formulation for space exploration missions. For all configurations, only laboratory level testing was discussed. For motor applications, full-scale testing is needed to ensure a complete mastering of the process.