Model-Based Optimization Method for Torsion Spring Design

The folding and unfolding dimensions of folding wings are crucial to the storage volume and flight performance of aircraft. To address the challenge of torsion spring parameter optimization in foldable wing UAV deployment mechanisms, this paper proposes a model-based optimization design method. By establishing a dynamic model of the wing structure and torsion spring mechanical response, combined with genetic algorithms for global parameter optimization, an optimization framework is developed with the objective of minimizing deployment completion impact. A C +  + automated torsion spring calculation program is implemented as the core solver module. Finite element simulation verification demonstrates that the optimized torsion spring reduces the final angular velocity by 16% while maintaining deployment functionality, significantly lowering impact loads. The model prediction results show an average relative error of 1.6% compared to simulation data. This method improves design efficiency and provides a systematic solution for folding mechanism parameter optimization.