Analysis of the Flutter Characteristics of the Advanced Kinetic Energy Missile (AdKEM) Control Surface

Abstract

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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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1990
Accession Number
ADA232377

Entities

People

  • Roger P. Berry
  • Stephen C. Cayson

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Actuators
  • Bending Moments
  • Classification
  • Coefficients
  • Computer Programs
  • Dynamic Pressure
  • Energy
  • Geometry
  • Kinetic Energy
  • Mach Number
  • Modulus Of Elasticity
  • Moment Of Inertia
  • Plastic Explosives
  • Resonant Frequency
  • Security
  • Steady State
  • Thickness

Fields of Study

  • Engineering
  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Control Systems Engineering.
  • Structural Dynamics.