A theoretical method for analyzing the aeroelastic divergence behavior of unguided, slender-body, multistage launch vehicle is presented. A rigorous matrix recurrence solution to the system equations based on a finite-difference approach yields the stability boundary at which aeroelastic divergence would occur. The stability criterion for acceptable design is reviewed and results of comparative analytical studies are illustrated. Secondary influences on aeroelastic divergence, such as thrust and aerodynamic crossflow, are incorporated and results of studies to ascertain the significance of these secondary influences are included. Example input data are presented and discussed along with illustrated output results. Comprehensive parameter studies are included to indicate corrective measures that may be used to avoid aeroelastic divergence.
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