SBIR-STTR Award

The proposed research will identify - and initiate the development of - key innovative technologies for assuring that dual-pulse solid rocket motors for future air supremacy missiles are capable of defeating highly maneuverable air targets. The proposed Knobley Technical Associates (KTA)team, by bringing more than 120 years of combined directly applicable experience in solid rocket pulse motor development and manufacture,assures focus on high payoff technologies. The investigative focus is on identifying the best combinations of ingredients, materials and components- and paths for needed developmental advances - to produce designs achieving major improvements in extending flight time, end game maneuverability and insensitive-munition-compliance, assuring future air supremacy. Key technologies to be evaluated are high-performance IM-compliant propellants including HTPE; lightweight high-pressure, high-temperature, high-stiffness (g-capability)composite cases/airframes; low-erosion lightweight nozzles; innovative pulse separation technologies; service-life-extending migration barriers; and efficiently-packaged LEEFI-based ignition trains. Phase I will produce two fully-integrated dual-pulse solid rocket motor designs featuring enabling materials and component technologies, and detailed Program Plans for component and full-scale dual-pulse motor demonstration and development, in Phase II. Driven by the uniquely-experienced KTA project team, these technologies will be both innovative and practical/affordable.

Keywords:
Air-Launch Dual-Pulse Air-Superiority Solid Rocket Motors, Insensitive Munitions, High Pressure High-Temperature High-G Composite Cases, Migration Bar

The Phase II Rocket Motor-Dual Pulse program is planned to advance technologies associated with rocket motor case materials and manufacturing, propellant grain designs with burn rate augmentation, insensitive munitions compliance, thermal barrier propellant grain segregation devices, high volumetric propellant loaded case assemblies and non-eroding nozzle systems. The program consists of a design phase in which one or more candidate 7-inch diameter high performance propulsion system defined during the Phase I studies will be subjected to detailed design and ballistic performance analyses. Analysis information will be provided to the Raytheon Company to have an analytical mission performance assessment of the candidate motor(s) completed for to air-to-air missile performance. Burn rate augmentation tests will be completed using aluminized HTPE insensitive munitions propellant and an array of candidate rate augmentation materials with goals of achieving a burn rate to meet thrust goals for Pulse 2 operation using a high volumetrically loaded propellant grain. Data from these tests will then be used to design and support manufacture and testing of a full scale pulse 2 propellant grain in which the gases are exhausted over pulse 1 case insulation materials and throttled thru a non-eroding throat nozzle. The program culminates in a 7-inch diameter dual pulse motor demonstration static test firing.

Keywords:
Pulse Motors, Energy Management, Solid Propellants, Composite Materials, Insensitive Munitions, Burn Rate Augmentation, Thermal Barriers, End Burning