Parametric study on the dynamic aeroelastic analysis of a two-stage axially deploying telescopic wing

In this paper, the flutter instability of a conventional two-stage axially moving telescopic UAV wing is investigated. To aim, and to be as close possible reality, effects temporal variation mass length, due movement stages their overlapping, along with morphing speed are considered for first time. The bending-torsional dynamics modeled by modifying Euler–Bernoulli beam theory take into account variations length. Furthermore, aerodynamic loads simulated using Peters' unsteady model. governing aeroelastic equations discretized finite element approach, length-based stability analysis proposed investigate aeroelasticity wing. obtained results compared those available in literature, good agreement observed. It found that more sensitive fixed part parameters than part. Also, it shown critical length speed. Therefore, selecting properly, system can significantly improved.