The objectives of the proposed research effort define the three principal program tasks: (Task 1) Identify a design approach to constructing an experimental ejector; (Task 2) Analytically quantify the potential improvement in specific impulse and thrust capability that might be derived from that novel rocket ejector subsystem design applied to rocket based combined cycle (RBCC) engines; and (Task 3) Design an experimental program that will validate the findings of the Phase I work in a USAF Phase II SBIR program. The proposed effort is innovative, i.e., new, unique and original, in that the performance capability of the proposed ejector subsystem design applied to RBCC engines has not heretofore been subjected to investigation in sufficient depth to quantitatively establish its potential benefits or the practicality of its application in RBCC engines. The anticipated benefits are that proposed work will establish the technical feasibility of an RBCC engine ejector subsystem design that will significantly reduce the propellant mass required for acceleration of RBCC engine propelled airbreathing capable vehicles from M=0 to effective ramjet operating speeds.
Keywords: COMBINED CYCLE ENGINES EJECTORS MISSILES TANSATMOSPHERIC VEHICLES BOOSTERS ROCKET ENGINES ETO
