COMBINED ROCKET AND SCRAMJET INTEGRATION FOR A LAUNCH VEHICLE

A preliminary design level optimization based trade study of integrated air-breathing propulsive assist for a rocket powered vertical launch vehicle is presented. The conceptual design for the proposed air-breathing thrust augmenter is an annular ramjet/scramjet integrated into a LOX-RP rocket core. The air-breathing engine makes use of the same tankage and turbopump hardware as the rocket engine for supplying fuel. Preliminary design level modeling of performance for candidate designs is achieved using an Euler solver for the aerodynamics and air-breathing propulsion components, a standard momentum approach for estimating rocket thrust, a semiempirical approach for the mass properties and a 7-8 order Runge Kutta integrator for solving the equations of motion for a six degree of freedom simulation of the flight. The optimizer is a binary encoded genetic algorithm with a proven track record for addressing complex flight vehicle design problems..

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