Transient Coupling of Launch Vehicle Bending Responses with Aerodynamic Flow State Variations

摘要

Current analytic formulations for the self-sustained coupling of launch vehicle bending responses with aerody- namic flow state variations are restricted to prediction of the limit cycle state and associated stiffness and damping values. The theory is extended to include evolution of the structural response during transonic flight to the limit cycle state. The method of multiple scales is used to analyze the nonlinear equation of motion. The resulting an- alytic expressions agree well with histories from a rigorous numerical solution for the idealized force-response coupling relationship.