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| Landing Impact Analysis of a Rocket Launcher Based on Airbag Buffering |
| Received:April 11, 2019 Revised:May 28, 2019 |
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| DOI：10.7643/issn.1672-9242.2019.11.017 |
| KeyWord:rocket launcher buffer airbag impact finite element method numerical simulation |
| Author | Institution |
| LI Qiang |
School of Mechanical Engineering, Nanjing University of Science & Technology, Nanjing , China |
| YU Cun-gui |
School of Mechanical Engineering, Nanjing University of Science & Technology, Nanjing , China |
| QIN Yu-zheng |
School of Mechanical Engineering, Nanjing University of Science & Technology, Nanjing , China |
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| Abstract: |
| Objective To reduce rocket projectile impact landing acceleration. Methods Based on LS-DYNA transient dynamics analysis software and impact dynamics theory, the finite element model of rocket launcher-airbag system was established by using finite element software HYPERMESH. The explicit dynamics method was used to simulate the landing shock & buffer process of rocket launcher-airbag system. The rocket projectile's landing impact response was analyzed under normal landing conditions. The speed & acceleration curve of the airdrop equipment and the volume & pressure curves of the airbag were obtained. Results Under normal landing conditions, the maximum lateral acceleration of the rocket projectile was 122 m/s2, which was less than the safe lateral acceleration; the maximum longitudinal acceleration of the rocket projectile was 48.3 m/s2, which was less than the safe longitudinal acceleration; and the maximum axial force of the rocket projectile was 2640 N, which was less than the safe blocking force. Conclusion During the impact of the rocket launcher, the airbag buffering device absorbs most of the impact energy and plays an important role in buffering. The impact acceleration and blocking force of the rocket projectile are all within the safe range. It is feasible to analyze the landing impact process of rocket launchers by explicit dynamics. |
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