Dynamic Analysis Method of Folding Wing Based on LS-DYNA

The folding wing has a short deployment time and a large impact load, and it has high requirement for positioning, locking and buffering devices of the wing deployment mechanism. The commonly used modular design method needs to simplify the structure, thus it cannot fully reflect the real system characteristics. This paper establishes a mathematical model of folding wing based on the simplified plane motion, and then establishes a finite element model by the LS-DYNA software, in which the influences of structural elasticity and friction are considered. The folding wing’s dynamics and structural strength are simulated comprehensively. The results show that the present method can simulate the shearing process of the positioning pin, the locking action and the unfolding process of the wing. As a result, the data of motion parameters are obtained, and the phenomenon of overshoot and vibration of the folding wing caused by large impact load and the structural elasticity after the wing fully deploys is observed. Therefore, the engineering design of the folding wing must satisfy the requirement of rapid deployment movement, and need to increase the structural strength to suppress the overshoot and vibration. This study may provide a reference for engineering design of the folding wing deployment mechanism.