Accession Number : ADP005917

Title :   Semiempirical Methods for Airbreathing Missiles,

Corporate Author : MCDONNELL DOUGLAS ASTRONAUTICS CO- ST LOUIS MO

Personal Author(s) : Williams, J. E. ; Krieger, R. J.

Report Date : APR 1988

Pagination or Media Count : 12

Abstract : A computer-aided design procedure is described for use in conceptual design for sizing and shaping supersonic non-circular missiles with turbojet or ramjet propulsion systems. The theoretical basis for the method, which uses a sensitivity derivative approach, is developed. Avionics, structures, payload, inlet, engine, fuel, aerodynamic and performance models are described. Inlet/engine sizing, external moldline shaping and interactive graphics design processes are presented. The synthesis procedure overcomes many of the major drawbacks of airbreathing missile synthesis. It has features such as: simple initial geometry setup for body, wings, tails and inlets; modeling of completely arbitrary missile shapes; non-circular subsystem packaging; non-circular and multiple inlet modeling; aerodynamic and performance shaping; low cost, short duration computer sessions; rapid convergence; and accurate aerodynamic predictions. Two example configuration shapings are provided to depict the sizing process.

Descriptors :   *GUIDED MISSILE COMPONENTS, *COMPUTER AIDED DESIGN, AERODYNAMIC CONFIGURATIONS, INTERACTIVE GRAPHICS, TURBOJET ENGINES, RAMJET ENGINES, SUPERSONIC FLIGHT, AVIONICS, STRUCTURAL COMPONENTS, PAYLOAD, INLETS, AERODYNAMIC CHARACTERISTICS, WINGS, TAIL ASSEMBLIES, FUEL CONSUMPTION, MATHEMATICAL PREDICTION, SIZES(DIMENSIONS), SHAPE.

Subject Categories : Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE