Vibration of Missiles: Matric Formulation of the Problem Involving Free and Harmonically Forced Flexural Vibrations

Abstract

The free and harmonically forced flexural vibrations of missiles accelerating along initial trajectories are considered. A general matric formulation is given for the problem whereby the effects of variable inertial axial loads along the missile length, variable stiffness and material properties, variable mass, variable mass moment of inertia, variable shear stiffness, and variably distributed forcing functions are treated. The matric formulation of the problem is in standard eigenvalue form and no special coding will be required for organizations that currently are solving eigenvalue problems on electronic digital computers. The time required for an engineer to fill in the matrices of the basic matric equation governing the vibrations of a missile structure is quite small since only fundamental data are needed and almost all calculations are performed within the computer.

Citation

Cox, H.L. (1961), "Vibration of Missiles: Matric Formulation of the Problem Involving Free and Harmonically Forced Flexural Vibrations", Aircraft Engineering and Aerospace Technology, Vol. 33 No. 1, pp. 2-7. https://doi.org/10.1108/eb033352