Solid Propellant Infrared Reduction At Launch (SPIRAL)

During the proposed Phase I research and development effort, the project team will use analysis and hot-fire testing to establish the feasibility of an approach to solid propellant formulation that greatly reduces the exhaust Infrared (IR) signature of the rocket motor while maintaining the thrust-to-mass-ratio of the existing, baseline solid propellant. The project team will formulate an array of propellant test specimen that show promise of infrared reduction by analysis. A technical analog of the currently deployed formulation will be used as a baseline. Infrared signatures will be measured during hot-fire testing of the baseline and the candidate formulations. The most promising candidate formulation will be used to develop a conceptual rocket motor design and the performance analyzed and reported. Approved for Public Release |21-MDA-10789 (21 Apr 21)