This three-day short course covers the fundamentals of missile design, development, and system engineering.
The course provides a system-level, integrated method for
missile aerodynamic configuration/propulsion design and
analysis. It addresses the broad range
of alternatives in meeting cost and
performance risk requirements. The
methods presented are generally
simple closed-form analytical
expressions that are physics-based, to
provide insight into the primary driving
parameters. Configuration sizing
examples are presented for rocketpowered,
ramjet-powered, and turbo-jet
powered baseline missiles. Typical
values of missile parameters and the
characteristics of current operational
missiles are discussed as well as the enabling subsystems and
technologies for missiles and the current/projected
state-of-the-art. Daily roundtable discussion. Sixty six videos illustrate missile development activities
and missile performance. Attendees will vote on the relative emphasis of the
material to be presented. Attendees receive course notes as
well as the textbook, Tactical Missile Design, 2nd edition.
Eugene L. Fleeman 47 years of government, industry, and academia, and consulting experience in missile design and in the development of missile systems and missile technologies. Formerly a manager of missile programs at Air Force Research Laboratory, Rockwell International, Boeing, and Georgia Tech, he is an international lecturer on missiles and the author of over 100 publications, including the AIAA textbook, Tactical Missile Design. 2nd Ed.
Development process for missile systems and missile technologies.
Design, build, and fly small air powered rocket.
Who Should Attend
The course is oriented toward the needs of missile engineers, system engineanalysts, program managers, and others working in the area of military systems and technology development. Attendees will gain an understanding of missile design, missile technologies, launch platform integration, missile system measures of merit, and the missile system development process.
Course Outline:
Introduction/Key Drivers in the Missile Design-Integration Process: Overview of missile design process. Examples of system-of-systems integration. Unique characteristics of missiles. Key aerodynamic 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. Attendees vote on course emphasis.
Aerodynamic Considerations in Missile Design-Integration: Optimizing missile aerodynamics. Shapes for low observables. Missile configuration layout (body, wing, tail) options. Selecting flight control alternatives. Wing and tail sizing. Predicting normal force, drag, pitching moment, stability, control effectiveness, lift-to-drag ratio, and hinge moment. Maneuver law alternatives.
Propulsion Considerations in Missile Design-Integration: Turbojet, ramjet, scramjet, ducted rocket, and 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. Motor case and nozzle materials.
Weight Considerations in Missile Design-Integration: How to size subsystems to meet flight performance requirements. Structural design criteria factor of safety. Structure concepts and manufacturing processes. Selecting airframe materials. Loads prediction. Weight prediction. Airframe and motor case design. Aerodynamic heating prediction and insulation trades. Dome material alternatives and sizing. Power supply and actuator alternatives and sizing.
Flight Performance Considerations in Missile Design-Integration: 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, and homing flight.
Measures of Merit and Launch Platform Integration: Achieving robustness in adverse weather. Seeker, navigation, data link, and sensor alternatives. Seeker range prediction. Counter-countermeasures. Warhead/fuzing alternatives and lethality prediction. Approaches to minimize collateral damage. Fusing alternatives and requirements for fuze angle and time delay. Alternative guidance laws. Proportional guidance accuracy prediction. Time constant contributors and prediction. Maneuverability design criteria. 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. Internal vs. external carriage. Shipping, storage, carriage, launch, and separation environment considerations. Launch platform interfaces. Cold and solar environment temperature prediction.
Sizing Examples and Sizing Tools: Trade-offs for extended range rocket. Sizing for enhanced maneuverability. Developing a harmonized missile. 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. Computer aided sizing tools for conceptual design. Soda straw rocket design-build-fly competition. House of quality process. Design of experiment process.
Missile Development Process: Design validation/technology development process. Developing a technology roadmap. History of transformational technologies. Funding emphasis. Alternative proposal win strategies. New missile follow-on projections. Examples of development tests and facilities. Example of technology demonstration flight envelope. Examples of technology development. New technologies for missiles.
Summary and Lessons Learned.
Tuition:
Tuition for this three-day course is $1795 per person at one of our scheduled public courses. Onsite pricing is available. Please call us at 410-956-8805 or send an email to ati@aticourses.com.
