Low Cost Hypersonic Projectile for Missile Defense

Modern missile defense threats that penetrate the upper layer of defenses require short timeline intercepts by armed projectiles maneuvering at hypersonic flight conditions (M = 5 - 7) during low altitude (<15km) operations. The interceptor itself is a low cost projectile that is the separable second stage of a missile that will be ground launched using a booster capable of attaining hypersonic speeds within 1-2 seconds. To provide a low cost system (< $$250k/unit) the projectile will not have an on-board seeker and will be command guided to the target by a ground-based tracking radar. This ground launch hypersonic booster approach introduces many design challenges, such as high heat flux and large mechanical loads and high G shock during system launch. Through modern simulation and design tools, it may be possible to design highly maneuverable hypersonic systems for low altitude operation that can be economically manufactured using modern fabrication technologies, such as additive manufacturing. The goal of this project is to explore the design space, identify an optimal set of system specifications that optimize an unpowered system for maximum range and affordable manufacturability - and then design a concept that optimally achieves the specifications. The project will entail geometry/configuration definition using a CAD system, discipline analysis such as aerodynamics, aerothermal, structural sizing, mass properties, stability & control, and conclude with vehicle sizing to meet mission requirements. Hence, on board propulsion is not required. Also, it can be assumed that flight control can be achieved through aerodynamic surfaces, reaction control jets, or a combination thereof. The requirements for the design include:

o Mach: 5 - 7
o Aerodynamically Stable and Thermally and Shock Survivable
o Optimized for Maximum Range and Affordable Manufacturing (Minimum Cost) using DTUPC guidelines
o Max length: TBD
o Max Diameter: < 0.1 m (including fins)
o Max mass: TBD
o Minimum Maneuverability: TBD g's
o RF & Antenna Specs: Provided by Sponsor

To validate the design, students will use lower order aerodynamics and CFD analysis to assess aerodynamic forces and moments predicted using engineering methods and will verify mission performance using flight trajectory analysis and optimization with inputs derived from discipline analyses. The team will perform wind tunnel tests at the university with a 3D printed prototype.