The folding wing deployment mechanisms of aircraft are constrained by weight and space limitations, necessitating fewer actuators, multiple outputs, compact designs, and high efficiency. However, existing folding wing mechanisms often overlook the impact of performance in configuration design. Additionally, they struggle to achieve the synchronous unfolding of multiple wings using a single drive. This paper presents a design methodology for multi-wing deployment mechanisms based on configuration topology and multiple performance indicators. Specifically, seventeen configurations of multi-wing deployment mechanisms are developed based on functional requirements, along with expression methods for performance indicators, including compactness, mechanism stiffness, dynamic sensitivity, motion transmission, and joint transmission efficiency. The optimal configuration for the multi-wing deployment mechanism is identified utilizing the fuzzy comprehensive evaluation. Moreover, the transmission efficiency of multiple configurations is calculated across different scale parameters. Simulation analyses and prototype experiments are conducted to validate the design. The results indicate that the transmission efficiency of the optimized configuration consistently exceeds that of the other configurations. Maximum efficiencies surpass those of the other configurations by 2.4% and 5.7%. Importantly, this study introduces a quantitative expression method for multiple performance indicators at the configuration design stage. This approach enables the integration of various performance metrics with configuration designs. Overall, this research provides a novel approach for the innovative design of multi-wing deployment mechanisms in aircraft. Additionally, considering performance in the selection of mechanism configurations during engineering design offers valuable insights and potential applications.

The rapid deployment of folding wings is characterized by high-energy impacts, which require an immediate and effective response from the locking mechanism. This locking process involves complex interactions, such as collisions and rebounds, and the effectiveness of the locking mechanism directly influences the reliability of the folding wing’s performance. However, current research lacks a theoretical exploration of the relationship between the locking mechanism and the locking velocity of folding wings, leading to occasional failures. This study aims to establish a theoretical model that connects the locking mechanism to the locking velocity of folding wings, thereby enhancing locking reliability. By analyzing the relative motion between the folding wing and the locking mechanism, a constraint model for the maximum locking velocity is developed. The study examines the effects of various parameters and the installation position of the locking mechanism on the locking velocity of folding wings. Simulations and prototype experiments validate the model, introducing a novel investigation into the issue of high-velocity rebounds in folding wings, which can cause the locking pin to retract. The study identifies the velocity range for reliable locking of high-velocity folding wings, revealing that both spring preload and the installation position of the locking mechanism significantly affect maximum locking velocity. Based on these findings, design recommendations are proposed to enhance the reliability of high-velocity folding wing locking, providing valuable insights for engineering applications and advancing theoretical research on high-velocity mechanism locking.