Numerical Investigations of Aeroelastic Divergence Parameter of Unguided Launch Vehicles

摘要

The present study focuses on the numerical investigations of stability margin for long, slender and relatively flexible unguided launch vehicles while avoiding the aeroelastic divergence conditions. The aerodynamic loads of the complete configuration are computed by using the modified three-dimensional low order panel method. The feasibility of using the transfer matrix method to estimate the natural frequencies and mode shapes for the launch vehicle is explored theoretically. Based on the vibration characteristics, the total dynamic response of the system has been evaluated when a sharp edged gust is encountered during the flight. The static aeroelastic characteristics, the divergence speed of a given launch vehicle have been studied by variation of the initial angle-of-attack and dynamic pressure. Computational analysis and discussion along with pertinent conclusions are presented.