Design and analysis efforts were conducted to define in detail a configuration capable of meeting the stringent performance, structural, and mass properties requirements. A propellant characterization program was conducted to define required propellant processing controls. Component tests were conducted to characterize, develop, and demonstrate the filament-wrapped motor tube, igniter, nozzle, insulator, end plug, nozzle closure, and grain end configurations. Adequacy of the resultant design was demonstrated by 25 successful heavywall motor tests and 31 successful flightweight motor tests. The program culminated in fabrication of a complete prototype MMA and successful test of all 56 motors.