III.N.17. Ducted Rocket Engine. By FY98, develop and demonstrate a ducted rocket engine for a medium surface-to-air missile to significantly increase the intercept envelope against aircraft, cruise missiles, and tactical ballistic missiles when compared to surface-to-air missiles using current solid rocket propulsion technology. Component technology development will focus on the design and testing of a minimum signature, insensitive munitions compatible booster, supersonic air inlets, and a solid fuel gas generator which provides for high impulse, minimum signature ramburner operation. In FY96, complete Heavyweight integration and initiate Flightweight propulsion system development. In FY97, complete Flightweight development and conduct ground testing. In FY98, complete ground testing and data reduction.
Supports: Battle Command, Depth and Simultaneous Attack, and Early Entry Lethality, and Survivability Battle Labs.
|STO Manager:||TSO:||TRADOC POC:|
|Michael Schexnayder||Mike Rithmire||LTC Dunham|