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Introduction/Key Drivers in the Missile Design and System Engineering Process:
Overview of missile design and system engineering process. Examples of system-of-systems integration. Unique characteristics of missiles. Key configuration sizing parameters. Missile conceptual design synthesis process. Examples of processes to establish mission requirements. Projected capability in command, control, communication, computers, intelligence, surveillance, reconnaissance (C4ISR). Example of Pareto analysis.
Aerodynamic Considerations in Missile Propulsion Design and System Engineering:
Optimizing the missile configuration geometry. Shapes for low observables. Missile configuration layout (body, wing, tail) integration with the propulsion system. Aerodynamic flight control versus propulsion thrust vector and reaction jet flight control. Aerodynamic maneuver versus propulsion divert maneuver. Inlet alternatives for bank-to-turn maneuvering.
Propulsion Considerations in Missile Design and System Engineering:
Turbojet, ramjet, scramjet, ducted rocket, and solid propellant rocket propulsion comparisons. Turbojet engine design considerations, prediction and sizing. Selecting ramjet engine, booster, and inlet alternatives. Ramjet performance prediction and sizing. High density fuels. Solid propellant alternatives. Propellant grain cross section trade-offs. Effective thrust magnitude control. Reducing propellant observables. Rocket motor performance prediction and sizing. Rocket motor aging and lifetime prediction. Motor case and nozzle materials. Ducted rocket design considerations and tradeoffs.
Weight Considerations in Missile Propulsion Design and System Engineering:
How to size the propulsion system to meet flight performance requirements. Structural design criteria factor of safety. Structure concepts and manufacturing processes. Selecting structure materials. Loads prediction. Weight prediction and motor case design. Aerodynamic heating prediction and insulation trades. Power supply and flight control actuator alternatives and sizing.
Flight Performance Considerations in Missile Propulsion Design and System Engineering:
Flight envelope limitations. Aerodynamic sizing-equations of motion. Accuracy of simplified equations of motion. Maximizing flight performance. Benefits of flight trajectory shaping. Flight performance prediction of boost, climb, cruise, coast, steady descent, ballistic, maneuvering, divert, and homing flight.
Measures of Merit and Launch Platform Integration:
Optimum cruise conditions for air-breathing propulsion. Electromagnetic compatibility. Warhead alternatives and lethality prediction. Approaches to minimize collateral damage. Radar cross section and infrared signature prediction. Survivability considerations. Insensitive munitions. Enhanced reliability. Cost drivers of schedule, weight, learning curve, and parts count. EMD and production cost prediction. Designing within launch platform constraints. Standard launchers. Internal vs. external carriage. Shipping, storage, carriage, launch, and separation environment considerations. Launch platform interfaces. Cold and solar environment temperature prediction.
Propulsion Sizing Examples:
Trade-offs for extended range rocket. Lofted range prediction. Ramjet missile sizing for range robustness. Ramjet fuel alternatives. Ramjet velocity control. Correction of turbojet thrust and specific impulse. Turbojet missile sizing for maximum range. Turbojet engine rotational speed.
Missile Propulsion Development Process:
Design validation/technology development process. Developing a technology roadmap. History of transformational technologies. Funding emphasis. Cost, risk, and performance tradeoffs. New missile follow-on projections. Examples of development tests and facilities. Example of technology demonstration flight envelope. Example of propulsion technology development.
Summary and Lessons Learned
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