Tactical Missile Air Turbo Rocket Propulsion System Critical Components Definition Study

The air turbo rocket (ATR) offers significant potential in terms of cost/performance ratio for tactical missiles. The high specific impulse of the ATR significantly increases range over solid rockets, while maintaining critical missile weight and launch system geometry constraints. The higher thrust levels of the ATR improve acceleration capability and rapid thrust control over a simular size turbojet. The program has two major tasks. Task 1 will develop an ATR cycle computer code, and be executable on an IBM PC or compatible microcomputer. The cycle code will then be utilized to develop an ATR conceptual design. Rocket propellents will be evaluated and used in a mission analysis. The cycle code will be integrated into a two-dimensional trajectory simulation code. A parametric mission analysis will be conducted, varying ATR propulsion design parameters, and propulsion system size. Cycle parameters critical to achieving the mission goals will be identified. A design will be selected and mission performance variations determined for alternative propellants. An optimum design will then be selected and recommended. Task 2 encompasses the detailed design of the flightweight ATR propulsion system. A heavyweight test component will be designed and fabricated.