Missiles can fail to follow their targets if their maneuvers reach a too high angle-of-attack. Maneuvering difficulties at high angles-of-attack are an outcome of significant force and moment fluctuations beyond the capabilities of the missile control surfaces. Moment and force fluctuations are caused by a combination of abrupt changes of circumferential orientation of forebody tip and vortex shedding from the missile slender body at high angles of attack. The outcome of these fluctuations is fluid-structure interaction between the maneuvering missile and its environment culminating with periodic and nonstationary self-excited oscillations due to a combination of galloping and vortex-induced vibrations. Stabilization schemes of undesired missile oscillations include feedback control of external control surfaces and of internal gyroscopic components.
In order to reduce the magnitude of self-excited oscillations in uniform flow, we investigate the nonlinear dynamics and stabilization performance of an elastically restrained rigid body augmented with an internal inertia wheel.
