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.
Semiempirical Methods for Airbreathing Missiles
1988
12 pages
Report
No indication
English
Missile Technology , Jet & Gas Turbine Engines , Guided missile components , Computer aided design , Turbojet engines , Ramjet engines , Aerodynamic characteristics , Aerodynamic configurations , Interactive graphics , Supersonic flight , Avionics , Structural components , Payload , Inlets , Wings , Tail assemblies , Fuel consumption , Mathematical prediction , Sizes(Dimensions) , Shape , Reprints , Air breathing missiles , Noncircular missiles , Semiempirical methods , NATO Furnished , Component Reports
Conceptual study of hypersonic airbreathing missiles
AIAA | 1978
|Conceptual study of hypersonic airbreathing missiles
NTRS | 1978
|