During the proposed Phase I research and development effort, the project team will demonstrate the feasibility of a solid propellant oxidizer alternative to Ammonium Perchlorate (AP). The candidate solid oxidizer will be formulated into a solid propellant that will demonstrate a greater density-specific impulse performance when compared to a typical AP/hydroxyl-terminated polybutadiene (HTPB)/aluminum composite propellant. A solid rocket motor design using the candidate propellant will be developed to meet Insensitive Munitions (IM) requirements set forth by 10 USC ยง 2389. The project team will conduct a hot-fire, feasibility demonstration of the technology. Approved for Public Release | 22-MDA-11215 (27 Jul 22)
