Abstract
The coupled equations of motion that govern the static and dynamic aeroelastic stability of spinning, flexible missiles are derived. A Lagrangian approach is employed which results in nonlinear coupling between the elastic deflections and the rigid-body motion parameters. Various approximations inherent in reducing the equations to a linear set are indicated. Firstorder aerodynamics are formulated for application to a hypersonic missile. Some numerical examples are given that reveal a destabilizing influence of structural damping at certain roll rates for a particular missile configuration.
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