## 5 Conclusions and Prospects  
This study proposed a force-thermal follow-up loading method for multi-stage telescopic wings and investigated the dynamic multi-point distribution equivalence method for transferring aerodynamic loads to predefined loading points during dynamic processes. Comparison with the traditional equal-area distribution method demonstrated the significant advantage of the proposed method in accurately fitting wingtip deformation trajectories, achieving a full-process fitting accuracy with R\({}^{2}>\)0.9. The research indicates that the proposed force-thermal follow-up loading method not only effectively achieves static loading, constant force-thermal follow-up loading, and time-varying force-thermal follow-up loading, but also exhibits good scalability, making it applicable to loading experiments for multi-dimensional morphing wings, such as telescopic folding and telescopic swept wings. The theoretical model of the follow-up force loading system for multi-stage telescopic wings was derived in this study. Based on this model, simulation models of the follow-up force loading control system and mechanical system were established. Simulations verified that the system's response capability reached within 0.4 s with an error margin of less than 1%, providing a theoretical foundation for the design and application of future loading systems. A force-thermal follow-up loading platform for multi-stage telescopic wings was developed and utilized to conduct ground simulation experiments. Experimental results showed that the loading system achieved a response speed within 0.4 s, with a load-following error maintained within 10%. Additionally, a comparison of the experimental results of wingtip deflection deformation and driving force during the telescoping process revealed consistent trends with the simulation results, further validating the feasibility and effectiveness of the designed force-thermal follow-up loading platform and its simulation analysis. \begin{table}
\begin{tabular}{c c c c} \hline \hline  & **Force Load** & **Thermal Load** & **Force–Thermal Load** \\ \hline RMSE (N) & 1143.70 & 2058.56 & 2442.13 \\ R\({}^{2}\) & 0.9508 & 0.9061 & 0.9217 \\ \hline \hline \end{tabular}
\end{table} 
Table 9: Driving force error. This study proposes and validates the effectiveness of the dynamic multi-point row equivalence method in force-thermal follow-up loading experiments for multi-stage telescopic wings. However, to further enhance the applicability and accuracy of this method, the following research directions should be explored in the future: (1) optimization of the loading method: improving the arrangement of loading points and load distribution strategies based on experimental and simulation feedback to enhance load simulation accuracy. (2) Experimental studies under complex conditions: conducting comprehensive experiments under broader flight conditions, such as high-speed aerodynamic loads and non-uniform temperature fields, to improve the engineering applicability of the method. (3) Multi-physics coupling simulations: establishing high-precision simulation models that incorporate aero-structural and thermodynamic coupling for more accurate representations of actual flight conditions. (4) Expansion of engineering applications: promoting the application of this method in the structural optimization of morphing aircraft, thereby improving the engineering practicality of multi-stage telescopic wings. These future studies will further refine the dynamic multi-point row equivalence method, enhance the accuracy of force-thermal follow-up loading experiments, and provide a solid theoretical and experimental foundation for the engineering application of high-performance morphing wings. Conceptualization, S.L. ; methodology, S.L. ; software, S.L. ; validation, S.L. ; formal analysis, S.L. ; investigation, S.L. ; resources, S.L. ; data curation, S.L. ; writing--original draft preparation, S.L. ; writing--review and editing, S.L., H.L. and C.L. ; visualization, S.L. ; supervision, H.X., H.G. and J.T.