Multi-Disciplinary Design of a Supersonic, Long-Range, Air-Superiority Missile Through Parametric Design Space Exploration and Physics-Based Modeling

The conceptual level design of a next-generation air superiority missile system is presented. The proposed missile will provide the USAF and USN with increased capabilities to combat cruise missiles and enemy aircraft beyond visual range. Considerations are made for platform integration onto F-15E, F-16C/D/E/F, F/A-18E/F, and F-35A/C fighter aircraft, including internal carriage compatibility where applicable. The simultaneous requirements of drastically increased range over existing assets and reduced carriage envelope imposed by internal weapons bays present an exceedingly complex and coupled design problem. One critical design consideration is the propulsion system (and propellant type) which largely dictates overall missile performance and geometry. It is shown that the demanding range and velocity requirements of air superiority missiles coupled with the stringent size restrictions render solid rocket motor propulsion (commonly employed in current and legacy air-to-air missiles) inadequate as a standalone propulsion method. Furthermore, the highly combinatorial nature of the design space yields an intractable number of combinations to be analyzed. To address this problem, a systematic method for evaluation and down selection is required. Advanced multi attribute decision making techniques are employed to efficiently explore the design space. The Technique for Order Preference by Similarity to Ideal Solution (TOPSIS) is found to be suited for design space studies of this nature, as it allows comparison of alternatives based on a combination of quantitative data, qualitative data, and expert opinion. This down selection process is applied to propulsion system selection in the context of missile system design, resulting in three favorable propulsion methods: liquid fueled ramjets, variable flow ducted rockets (VFDR), and solid fueled ramjets. The selected propulsion systems are then analyzed parametrically in tandem with other design considerations through a physics based modeling and simulation environment to assess overall system performance. A final performance-based design evaluation is conducted to determine the preferable missile configuration. A final ramjet-powered missile is proposed which meets or exceeds all posed requirements, notably having a maximum range of 220 nmi, weight of 533 lb, and max velocity of Mach 5.2, while conforming to the internal weapons bay constraints of the F-35A/C.