Исследование динамической устойчивости модели крыла в потоке воздуха

Abstract

Investigating the aircraft structure elements for compliance with dynamic stability is one of the most important ways to study their dynamic properties. The paper considers possibility of the wing model dynamic loss of stability (flutter type) in the form of a flat rod of variable geometry close to the real wing geometry in the airflow. Internal force factors manifested under the frontal aerodynamic force influence, as well as increment in the lift and aerodynamic moment arising during possible small model oscillations are taken into account from the oncoming airflow side. Due to these external forces increment, the so-called energy pumping from the airflow side occurs, and the problem becomes non-conservative. Behavior of the first three complex eigenvalues of small oscillations was numerically studied, and the critical flow velocities, at which the model could lose dynamic stability, were determined for various parameters of the external aerodynamic forces.