MODELING OF THE FLIGHT OF A HIGH-SPEED ELASTIC MISSILE WITH LATTICED CONTROL SURFACES

A structural mathematical model for the analysis of processes of loading, deformation, and motion of a missile with latticed control surfaces is described. The model is based on the method of specified shapes and numerical methods of continuum mechanics. It permits one to analyze the processes occurring in missiles moving at subsonic and supersonic speeds. We present an effective technique for calculating the total linear aerodynamic and aeroelastic characteristics of the missile. This technique is based on the method of discrete vortices and involves the identification of interference coefficients for the members of the aerodynamic configuration. The potentials of the mathematical model are illustrated by the solution of an example problem.