Title: Articulated Smart Projectile Stability and Maneuverability

Date: Wednesday, February 28th, 2024

Time: 3:00pm – 5:00pm EST

Location: Virtual

Virtual Link: https://teams.microsoft.com/l/meetup-join/19%3ameeting_NzFiYjdhZTUtMjU3OC00YzdjLTg1NDctOTY3MmQyZTk4ZmZj%40thread.v2/0?context=%7b%22Tid%22%3a%22482198bb-ae7b-4b25-8b7a-6d7f32faa083%22%2c%22Oid%22%3a%22107f23a6-ae6b-4b39-898b-f39b26e08182%22%7d

Cason Butler

Robotics Ph.D. Student

School of Aerospace Engineering

Georgia Institute of Technology

Committee:

Dr. Mark Costello (Advisor) – School of Aerospace Engineering, Georgia Institute of Technology

Dr. Jonathan Rogers – School of Aerospace Engineering, Georgia Institute of Technology

Dr. Anirban Mazumdar – School of Mechanical Engineering, Georgia Institute of Technology

Dr. Ari Glezer – School of Mechanical Engineering, Georgia Institute of Technology

Dr. Benjamin Dickinson – Munitions Directorate, Air Force Research Laboratory

Abstract:

Smart projectiles typically achieve passive flight stability through fin or spin stabilization. Fin-stabilized projectiles are designed to place the center of pressure behind the center of mass, creating a stabilizing restoring moment. Spin-stabilized projectiles rely on a high spin rate to induce gyroscopic stability. These passive stabilization methods come with downsides, such as parasitic fin drag. An alternative method to achieve flight stability and maneuver capability is active deformation of the nose of the projectile. Large normal forces and pitching moments can be generated as a function of the projectile-nose aerodynamic angle of attack. By dynamically deforming the nose, closed-loop flight stability and significant maneuver capability can be achieved, without fins or spin. The thesis proposed explores moveable-nose actuation for use on a projectile. The main aims of the thesis are threefold. Firstly, analyze the ability of a moveable nose to actively stabilize slowly-spinning projectiles with fin area reduction. Secondly, explore the maneuverability limits of an articulated-nose projectile. Finally, determine optimal articulated configurations and control strategies to expand the projectile trajectory footprint. These aims will be supported by multibody flight dynamic models and related linear models combined with associated flight control logic.