Analysis of the Flutter Characteristics of the Advanced Kinetic Energy Missile (AdKEM) Control Surface
Final technical rept. Oct 1989-Feb 1990
ARMY MISSILE COMMAND REDSTONE ARSENAL AL GUIDANCE AND CONTROL DIRECTORATE
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This report describes the analysis of the flutter characteristics of the control fin for the Advanced Kinetic Energy Missile ADKEM. First of all, the control fin stability equation is determined from the two-degree-of-freedom equations of motion for the fin. This equation is a function of the fin bending stiffness and the actuator dynamic stiffness, which are then found. The fin bending stiffness is found by assuming that there is a distributed load on the fin and solving for the bending moment and angular deflection using numerical integration. The actuator dynamic stiffness is solved for by applying a torque disturbance to the second order actuator equation of motion and calculating the resulting fin angular deflection. This data is then compared to the existing third order model and non-linear model data to check for validity.Knowing these values, the possibility of fin flutter may be determined.
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