Fast Pattern Recognizer for Real Time Pattern Recognition

Not Available As a result of its hybrid rocket/turbojet nature, Air-Turbo-Rocket (ATR) propulsion offers the airframe manufacturer 3-4 times the specific impulse of a SRM with 2-3 times the specific thrust of a turbojet under identical operating conditions, Quantum cost reduction is possible by optimizing the trade-off associated with propellant selection, trubomachinery specific speed combination and combustion mixture ratio. Phase I will focus on the utility of an ATR over competing propulsion systems in current DARPA missile and global reach scramjet boost operation initiatives. Propulsion vehicle designs to be considered during Phase I will include hydrogen regenerative and bi-propellant (LOX/RP-1) ATRs for scramjet boost as well as ultra low cost solid propellant fueled ATRs for AFSS, LCCMD and MALD missile systems. The starting point for each ATR propulsion concept will be synthesized from CFDRC's high performance solid propellant ATR demonstrator engine currently being tested at the U.S. Army AMCOM. CFDRC will use an advanced version of its proven Global Engine Mission Analysis (GEMA) software package to conceptualize ATR engine concepts suitable for installation into each vehicle. Preliminary vehicle/propulsion/trajectory simulations of each DARPA initiative will be completed. Whenever necessary, CFDRC will interact with ATR propulsion team members Boeing, Raytheon, Lockheed Martin, Atlantic Research Corporation, Allison and Sundstrand to identify critical vehicle installation issues and/or component technologies requiring further consideration during Phase II. The objective of Phase II will be to ground test an affordable flight configured ATR propulsion system and thereby evince the ATR as an optimum thrust to weight air breathing propulsion system with minimum propellant fraction and cost (both acquisition and recurring operational).