Time-Varying Aeroelastic Modeling and Analysis of a Rapidly Morphing Wing

Advanced rotational variable-swept missile wings require the ability to rapidly deploy, retract and reach designated position. Therefore, establishment of an effective time-varying aeroelastic model a rotating wing is prerequisite for performing transient response analysis during rapid morphing process. In this paper, finite element at fixed configuration combined with floating frame method describe small elastic deformations large rigid-body displacements wing, respectively. Combining structural dynamic supersonic piston theory, nonlinear undergoing process established. A real-time determination lifting surface discussed. Based on proposed equations motion, flutter characteristics different sweep angles are obtained. The influences actuator spring constant, damping ratio post-lock stages, as well velocity quadratic term in equations, responses system studied. simulation results show that greatly influenced by angle. Moreover, jumping phenomenon speed due switching modes found increase simulations demonstrate mainly occur stage, so much more attention needs be focused vibrations. addition, under given parameters, has little effect system. This study provides efficient predicting variable swept wing.