Deployment Impact Analysis of a Certain Type of Folding Wing Deployment Mechanism

Pengfei Zhang; Yanbin Qin

doi:10.54097/f31pre98

Authors

Pengfei Zhang
Yanbin Qin

DOI:

https://doi.org/10.54097/f31pre98

Keywords:

Folding Wing, Collision, Buffering, Dynamic Simulation

Abstract

The instantaneous impact problem of the folding wing when it is fully deployed is theoretically analyzed by using the impact theory in theoretical mechanics. The dynamic process simulation analysis of the contact impact part of the fully deployed folding wing is carried out by Ansys software. The impact force function is adopted to describe the impact effect between the shock absorber pad and the projectile wing, and the determination method of the force function parameters is given. The analysis results show that the modeling method in this paper is suitable for theoretically and numerically simulating the impact characteristics of the folding wing during full deployment. For the designed working condition with a maximum spring force of 525 N, through analyzing the dynamic characteristics of the projectile wing and the buffer pad within the 8 mm impact stroke, the impact time is obtained as 0.1 s, the peak impact stress is 7.7 MPa, and the peak impact force is 770 N, which is less than the design upper limit of 5000 N and meets the safety requirements for the peak impact stress.

Downloads

Download data is not yet available.

References

[1] Yang B Y. Measuring the Deployment Time of Folding Wings Using an Accelerometer[J]. Aerospace Shanghai,1993, (05): 25-26. DOI:10.19328/j.cnki.1006-1630.1993.05.005.

[2] Lv T G, Zhang X W, Li Y W, et al. Research on Motion Characteristics of Longitudinal Double-Folding Wings[J]. Aero Weaponry, 2023, 30(05): 127-134. DOI:10. 12132/ ISSN. 1673-5048.2023.0074.

[3] Song H X, Jin L. Dynamic Modeling and Stability Control of Folding-Wing Aircraft[J]. Acta Mechanica Sinica, 2020, 52 (06): 1548-1559.

[4] Xie Y M, Cheng X F, Zhang H W. Development of an Automatic Tension Measuring Device for Folding Wings[J]. Aerospace Technology, 2001, (02): 39-42.

[5] Zhen W Q, Ji Y Q, Shi Y G. Dynamic Simulation and Experimental Research on Deployment Process of Missile Folding Wings[J]. Acta Armamentarii, 2016, 37(08): 1409-1414.

[6] Guo X L, Pei J H, Yang Z Q, et al. Research on Deployment Kinematic Characteristics of UAV Folding Wings[J]. Journal of Nanjing University of Aeronautics and Astronautics , 2006, (04): 438-441.DOI:10.16356/j.1005-2615.2006. 04.009.

[7] Deng H L, Hu M, Chen W H, et al. Dynamic Simulation and Experimental Analysis of Folding Wing Deployment Mechanism Based on SimMechanics[J]. China Sciencepaper, 2015, 10(22): 2619-2623.

[8] Hangyue Z, Yanchu Y .Dynamic analysis of wing deployment of high altitude balloon launched small size folding-wing UAV1[J].MATEC Web of Conferences,2018, 19805004. DOI: 10.1051/matecconf/201819805004.

[9] Li L, Ren C X, Zhang D. Dynamic Simulation and Optimization of Folding Wing Mechanism Deployment[J]. Structure & Environment Engineering, 2007, (01): 17-21.

[10] Chen L Q. Analytical Mechanics Content in Theoretical Mechanics: Practice of Theoretical Mechanics Course [C]//Chinese Society of Theoretical and Applied Mechanics. Abstracts of the Chinese Mechanics Congress 2025 (Volume 1). Department of Mechanics, School of Mechanics and Engineering Science, Shanghai University, 2025: 31. DOI: 10. 26914/c.cnkihy.2025.058750.

[11] Chen L, Wang T, Sun Q X. Design and Analysis of a Spring Locking Mechanism for Folding Wings[C]//Jiangxi Society of Aeronautics, Structural and Strength Branch of Chinese Society of Aeronautics, Shaanxi Society of Aeronautics. Proceedings of the 2013 China Society of Aeronautics Structural Strength Academic Exchange Conference. Hongdu Aviation Industry Group, 2013: 7.

[12] Zhang Q, Nie H, Zhang M, et al. Dynamic Analysis of UAV Folding Wing Deployment[J]. Mechanical Design and Manufacturing Engineering, 2015, 44(02): 12-16.

[13] Nie W C, Cai W J, Zhang Y Q, et al. LS-DYNA-based Dynamic Analysis Method for Folding Wings[J]. Journal of Underwater Unmanned Systems, 2018, 26(04): 298-303.