Non-spinning Missile Dynamic Assessment Using Nonlinearity Index Theory

Abstract

This paper introduces the nonlinearity index theory for missile flight mechanics analysis. Further, the nonlinearity of a longitudinal and lateral-directional nonspinning missile simulation model is analyzed over the entire flight envelope. The aerodynamic coefficient envelope is flight speed, angle of attack and angle of sideslip region. Nonlinearity index theory provides a new methodology for measuring the strength of nonlinearity and is applied to the aerodynamic angles and Mach number envelope. This analysis provides new ideas and insights to missile dynamic assessment and controller design.