Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

摘要

To create highly maneuverable projectiles, some physical control mechanism is needed that is capable of altering the projectile trajectory in a desired manner. The work reported here considers a small flow control device, termed a microspoiler system, located between the rear stabilizing fins of a projectile. Such a mechanism relies on the boundary-layer shock interaction between the projectile body, rear stabilizing fins, and microspoilers to provide a multiplicative effect on controllable forces and moments. To investigate performance of the microspoiler control mechanism, projectile trajectories with microspoilers were generated both computationally using a coupled CFD and rigid-body dynamic simulation and experimentally from spark range testing. Using this computational and experimental trajectory information, aerodynamic coefficients both with and without microspoilers were estimated and found to be in good agreement where the major effect of the microspoiler system is the addition of trim forces and moments along with a slight increase in axial forces. Additionally, control authority of a basic finned projectile equipped with an active microspoiler system is investigated for a typical direct-fire shooting scenario.