Long-Duration Proportional Thruster for Navy Hot-Gas Control System Navy SBIR FY2018.1 Sol No.: Navy SBIR FY2018.1 Topic No.: N181-091 Topic Title: Long-Duration Proportional Thruster for Navy Hot-Gas Control System Proposal No.: N181-091-0197 Firm: Valley Tech Systems, Inc. 160 Blue Ravine Road, Ste A Folsom, California 95630 Contact: Russell Carlson Phone: (707) 696-5354 Abstract: VTS proposes the development of a conceptual design for a proportional thruster used in an assembly that can replace the current IVA on the Navy SSP PBCS. The concept design will be matured through a process that includes an architecture trade study, model-based engineering (MBE), performance model showing pintle position and chamber pressure to provide the requisite thrust versus time profile, and key tests. The process is structured with the aim of reducing risk on a future Phase II development effort. We will identify the technical risks and develop mitigation plans that can be used to define Phase II scope. VTS will work with Navy SSP to establish all necessary technical requirements. VTS will leverage thermal-management design techniques developed on previous DOD proportional thruster contracts to achieve operation for 1,000 seconds with 3,000A� Fahrenheit gas temperature. The concept design will be evaluated for deign margins by performing preliminary thermos-structural analyses of the MBE-generated design. Benefits: The unique performance demands of the D5 integrated valve assembly will drive research and eventual design solutions that leverage into numerous adjacent applications within DoD, NASA, and commercial enterprise. There is a growing demand for long duration solid propellant hot gas proportional thruster designs that mimic the performance capability of classic liquid bi-propellant propulsion solutions, but alternatively feature non-toxicity, affordability, storability, field operability, and crew safety conscious solutions. Anticipated benefits include longer operating thruster designs that serve post boost applications for small launch vehicles, strategic deterrent post boost controls, missile defense interceptors, in space satellite/payload bus propulsion modules, hypersonic body steering, booster ACS & roll control, and planetary landing/ascent/rendezvous propulsion modules. The materials sciences developed under this SBIR will serve to extrapolate and in some cases extend the mission duty cycles of cited mission domains. Return