Kinematic characteristics of longitudinal double folding wings

Abstract

A folding wing is a tactical missile launching device that needs to be miniaturised to facilitate storage, transportation, and launching; save missile and transportation space; and improve the combat capability of weapon systems. This study investigates the aeroelastic characteristics of the secondary longitudinal folding wing during the unfolding process. First, the Lagrange equation is used to establish the structural dynamics model of the folding wing, the kinematics characteristics during the deformation process are analysed, and the unfolding movement of the folding wing is obtained using the dynamic equations in the process. Then, the generalised unsteady aerodynamic force is calculated using the dipole grid method, and the multi-body dynamics equation of the folding wing is obtained. The initial angular velocity required for the deployment of the folding wing is analysed through structural model simulation, and the influence of the initial angular velocity on the opening process is studied. Finally, aeroelastic flutter analysis is performed on the folding wing, and the physical model of the folding wing verified experimentally. Results show that the type of aeroelastic response is sensitive to the initial conditions and the way the folding wing opens.

Dynamics simulation of folding wing UAVs launched from a high-altitude balloon platform

“…The aircraft traditional dynamic modeling method does not consider structural changes of the UAV during flight. So it needs modeling methods in the multi-body dynamics discipline field, including the Newton-Euler method, Lagrange mechanics method, 18 Kane method, 19 or Natural Coordinate method. 20 Lei Tong 21 built a multi-body dynamic model of an asymmetric variable-sweep morphing aircraft and explored the idea of aircraft roll control by using an asymmetric wing sweep angle.…”