Project number
26053
Organization
Lockheed Martin
Offering
ENGR498-F2025-S2026
Maneuvering a projectile at hypersonic flight conditions (M = 5 – 8) at low altitude operation introduces many design challenges, such as high heat flux and large mechanical loads. 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 a free flying (unpowered) system for 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. The projectile will be launched at speed from an independent source. 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:
• Mach: 5 – 8
• Aerodynamically Stable and Thermally Survivable
• Optimized for Maximum Range and Affordable Manufacturing (Minimum Cost)
• Max length: 1.0 m
• Max Diameter: 0.1 m (including fins)
• Max mass: 10 kg
• Minimum Maneuverability: 15g turn
• Minimum Volume Efficiency (h= V2/3/Splanform) ≥ 0.12
To validate the design, students will use lower order aerodynamics and/or 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 their university with a 3D printed prototype.
Additionally, transient aerothermal analysis of the projectile and assessments of location and thermal requirements for a sensor window will be performed. Pending results of the Preliminary Design Review in the fall semester, the spring semester will either focus on a refined design for a gun launch or perform extended testing to characterize dynamic fin deployment.
The goal of this project is to explore the design space, identify an optimal set of system specifications that optimize a free flying (unpowered) system for 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. The projectile will be launched at speed from an independent source. 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:
• Mach: 5 – 8
• Aerodynamically Stable and Thermally Survivable
• Optimized for Maximum Range and Affordable Manufacturing (Minimum Cost)
• Max length: 1.0 m
• Max Diameter: 0.1 m (including fins)
• Max mass: 10 kg
• Minimum Maneuverability: 15g turn
• Minimum Volume Efficiency (h= V2/3/Splanform) ≥ 0.12
To validate the design, students will use lower order aerodynamics and/or 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 their university with a 3D printed prototype.
Additionally, transient aerothermal analysis of the projectile and assessments of location and thermal requirements for a sensor window will be performed. Pending results of the Preliminary Design Review in the fall semester, the spring semester will either focus on a refined design for a gun launch or perform extended testing to characterize dynamic fin deployment.